RU2421702C1 - Method of aerodynamic testing of aircraft model (versions) and unit to this end - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: in compliance with first versions, aircraft model is blown with altitude tunnel airflow to simulate air flow rate via engines and power plant reversal jets. Hot gas is fed into reversal cambers of engine nacelle models to measure flow temperature therein. Ingress of reversal jets into engine nacelle model channel is defined from airflow temperature increase. In compliance with second version, flow total pressure in engine nacelle is measured in blowing aircraft model, and relative amplitude of inlet flow total pressure pulsations is calculated to define ingress of reversal jets into engine nacelle model channel. Proposed unit comprises runway simulation screen that may turn about vertical axis, aircraft model with receivers of inlet flow parameter transducers. Besides, proposed unit comprises appropriate appliance to set air flow rate from engine nacelles and gas source. ^ EFFECT: detecting ingress of reversal jets into air jet engine intake nozzles in thrust reversal and simulation of aircraft motion on runway. ^ 14 cl, 21 dwg

Description

The invention relates to the field of aerodynamic tests, in particular, to installations for studying the thrust reversal mode of an aircraft powerplant while the aircraft is moving along the runway. In this case, one of the important tasks to be solved when testing a power plant operating in the thrust reverse mode is to fix the reversal jets of the power plant getting into the inlet nozzles of the jet engines and determine the operating conditions of the power plant under which this happens, since the reversing jets are hit engine into the inlet nozzle can lead to abnormal modes of operation of the power plant.

A number of technical solutions are known related to the study of the interaction of engine jets with the incoming air flow and the aircraft (see, for example, A.N. Radzig. Experimental Hydroaeromechanics. Moscow Aviation Institute, 2004, pp. 37-39) in which the flow around an aircraft is simulated in combination with the simulation of flows flowing out of an air-jet engine nozzle. During aerodynamic tests in accordance with these methods, a model of a nacelle equipped with a through channel for air flow can be used. The cross sections of the channel of the nacelle are selected so that the relative air flow at the inlet corresponds to the natural one in the design mode. When modeling the interaction of the engine jets in accordance with these methods, the problems of studying the interaction of the reversible jets of the power plant with the incoming air flow are not solved, and the problem of fixing the ingress of the reverse jets of the engine into the inlet nozzle of the jet engine under the conditions of the aircraft moving along the takeoff landing strip when the engines are in this mode.

From the description of the invention according to USSR author's certificate No. 402316 (MKI ⁵ G01M 9/00, decl. 01.24.1972, publ. 11/20/2004) there is a known method of testing a model of a power plant in which the model of a nacelle suspended on a pylon is placed above the screen -imulator of the runway. During the tests, the model is blown with air flow, at which air is sucked out of the inlet nozzle of the nacelle model and air is supplied to the outlet nozzle of the nacelle model. In this method, in addition, the runway simulator is rotated relative to the model of the nacelle. This test method is aimed at studying the operation of the power plant during movement along the runway and the ingress of foreign objects into the inlet nozzle of the jet engine and does not solve the problems of simulating the movement of an aircraft in combination with simulating the operation of the power plant in thrust reversal mode.

Devices for the implementation of the aerodynamic test methods described above (see A.N. Radzig. Experimental hydroaeromechanics. Ed. MAI, Moscow, 2004, pp. 37-39, Fig. 2.9) include models of nacelles connected to a model of an airframe apparatus or, as shown in Fig. 2.9, with a pylon and a model of the wing console. At the same time, models of nacelles can be equipped with a through channel for air flow, means for modeling the dual-circuit engine (for example, an ejector), or flow conditions at the exit of the nacelle model. The gas source is placed inside the model of the aircraft glider. The device devices do not allow modeling reverse engine jets and investigate the conditions of their entry into the inlet nozzle of an air-jet engine when the aircraft moves along the runway.

A device is known for testing in a wind tunnel models of aircraft with an inlet air intake and an internal flow channel with an output throttle nozzle and simulation of a jet engine outflow (Technique for the experimental determination of drag of an aircraft-air intake system. Express information, Aircraft, 1975, No. 25, p. 25-37).

Known stand for aerodynamic testing, containing an aerodynamic nozzle, a pressure chamber with a suction exhauster in the highway. An air intake with a bench diffuser and a test engine with elements of an aircraft, for example, with a wing and a cooling channel, are placed in a pressure chamber. A two-position damper or partition is installed in the channel. The channel is connected by a pipe to an additional suction system. During operation, the air accelerates in the aerodynamic nozzle and blows around the air intake with the elements of the aircraft. One part of the air after braking in the air intake enters the engine, and the other into the bench diffuser and, after mixing with the exhaust gases from the engine, is sucked from the pressure chamber along the main line by exhausters (USSR Author Certificate SU 334500, MKI ⁵ G01M 9/00, published 01.01. 1972).

The listed devices also do not provide a solution to the problem of simulating the movement of an aircraft along the runway in combination with simulating the operation of the power plant in thrust reverse mode.

The closest analogue to the claimed test methods is the first version of the aerodynamic test method, known from the patent of the Russian Federation No. 2349888 (IPC G01M 9/00, declared. 12.28.2006, published on 03.20.2009). During aerodynamic tests in accordance with this method, a model of the nacelle of an aircraft equipped with a through channel for air flow is used. A model of a nacelle is placed in an installation for blowing it with a stream of air above a runway screen simulator. Blowing is carried out in different directions of the air flow relative to the model of the nacelle. When blowing, the air flow is passed through the through channels of the models of nacelles, it is sucked out from the through channels and it is taken outside the working part of the installation. In the process of blowing, in accordance with this test method, the ingestion of solid particles lifted from the surface of the runway simulator screen into the engine nacelle model along with the air flow through the air intake inlet nozzle is recorded.

Using in this method in the test process only the model of the nacelle without the model of the glider of the aircraft moves the test results away from the real nature of the flow around the aircraft. In addition, in the process of testing the reverse jets of the power plant are not simulated when driving along the runway. This method of aerodynamic testing, solving the problem of modeling the vortex formation process in front of the inlet nozzle of the engine nacelle model and the qualitative and quantitative analysis of the ingress of foreign objects into the jet engine while working on the runway, does not solve the problem of modeling the movement of an aircraft along the runway lane during operation of the power plant in the mode of reverse thrust and the task of fixing the ingress of reverse jets into the jet engine.

The closest analogue of the claimed installation for aerodynamic testing is the first version of the installation for implementing the method of aerodynamic testing, known from the patent of the Russian Federation No. 2349888 (IPC G01M 9/00, declared. 28.12.2009, published. 03.20.2009).

In a known solution, an aerodynamic test installation comprises a runway simulator screen, a nacelle model mounted above a runway simulator screen, which is provided with a through channel for air flow, a rarefaction system connected by an air duct to the exit of the through channel of the nacelle model and equipped with means of exhausting air from the engine nacelles. The screen simulator of the runway is made in a planned projection in the form of a circle.

The screen simulator of the runway and the model of the nacelle placed above it on a stand-alone base from it in the claimed solution are fixed motionless. Before installation for aerodynamic testing, a means was placed for blowing the model of a nacelle with an air stream (wind turbine), made with the possibility of rotation relative to the vertical axis of the runway simulator screen, which provides blowing of the model at various angles.

The model of the nacelle is made of two shells (external and internal), which provide a simulation of the separation of the air flow in the through channel along the contours of the jet engine. The front part of the model of the nacelle, in addition, is made with contours that simulate the contours of a real engine and is equipped with a cook. In addition, the model of the nacelle is equipped with means for fixing hits of foreign objects raised by the free stream from the runway, and means of observing the trajectories of their movement inside the nacelle.

The considered device for aerodynamic testing allows modeling of the ingress of foreign objects into the jet engine while moving along the runway, but does not make it possible to solve the problem of simulating the reversal jets of the power plant entering the engine inlet nozzle. So the nature of the flow of air flow blowing around the nacelle differs from the nature of the flow around the model of the aircraft, which contains, in addition to the model of the nacelle, a glider model. The internal structure of the nacelle model also does not allow the modeling of reversible jets and fixation of their falling into the inlet nozzle of the nacelle model.

The objective of the invention is to develop methods and devices for simulating the movement of an aircraft along the runway under conditions close to field conditions, when the power plant is in thrust reversal mode.

The technical result is the possibility of fixing the reversal jets of the power plant of the aircraft in the inlet nozzle of the jet engine under different thrust reversal modes in combination with simulating the movement of the aircraft along the runway at different gliding angles in the speed range corresponding to the speeds of the aircraft the earth.

The technical result of solving the problem of fixing the ingress of reversible jets of an aircraft power plant into the inlet nozzle of an air-jet engine in accordance with the claimed aerodynamic test methods is achieved as follows.

In accordance with the first and second variants of the proposed method of aerodynamic tests during aerodynamic tests using a model of the aircraft, composed of a model of a glider and models of nacelles with through channels for air flow and reversing cameras with simulators of reversing devices. During aerodynamic tests in accordance with the claimed methods, the model of the aircraft is placed in the working part of the wind tunnel, mounting it on the screen simulator of the runway. Then the screen simulator of the runway is deployed together with the model of the aircraft at a given angle of slip relative to the direction of air flow of the wind tunnel.

After that, in accordance with the first and second claimed variants of the aerodynamic test method, blowing the model of the aircraft with the air flow of the wind tunnel is carried out. The air flow velocity of the wind tunnel is monotonically reduced from a speed close to the landing speed of the aircraft under natural conditions.

In accordance with the first and second claimed variants of the test method when blowing an aircraft model, the air flow through the engines is simulated, in which the air flow of the wind tunnel is passed through the channels of the models of the nacelles, it is sucked from the channels with a given flow rate and it is taken outside the working part of the wind tunnel .

In accordance with both the first and second claimed test methods when blowing a model of an aircraft with an air stream, the reverse jets of a power plant are simulated.

In accordance with the first claimed variant of the aerodynamic test method, when simulating the reversing jets of the power plant, hot gas with a predetermined flow rate is supplied to the reversing chambers of the engine nacelle models, it is allowed to pass outside the model of the engine nacelle, and then it is directed by the above mentioned simulators of reversing devices towards the incoming air flow. In addition, in accordance with the first variant of the proposed test method, blowing the model is accompanied by measuring the temperature of the stream near the inlet of the through channel of at least one of the models of nacelles.

In accordance with the first variant of the proposed test method for increasing the temperature of the air flow at the inlet of the through channel with a decrease in the blowing speed of the model, the reversible jets of the power plant enter the channel of the model of the nacelle. An increase in temperature by more than 2 degrees, with a decrease in the air flow velocity by 5 m / s, indicates that reversible jets enter the inlet nozzle of the nacelle model.

In accordance with the second claimed variant of the aerodynamic test method, when simulating the reversible jets of the power plant, gas with a predetermined flow rate is supplied to the reversing chambers of the models of the nacelle, they are passed outside the model of the nacelle, and they are directed by simulators of the reversing devices towards the incoming air flow. In addition, in accordance with the second variant of the proposed test method, blowing the model is accompanied by measuring the total flow pressure near the inlet of the through channel of at least one of the models of nacelles. The measurements calculate the relative amplitude of the pulsations of the total pressure (ε) of the input stream. During testing, it is most preferable to measure the total pressure at several points located practically in the same plane near the inlet nozzle of the nacelle model and calculate the amplitude of the total pressure pulsations as the average of n measurement results

where ε _i is the relative rms amplitude of the pulsations of the total pressure at one of the measurement points near the inlet of the nacelle channel

in which T is the registration period, δP ₀ is the deviation of the total pressure from the average value of P ₀ .

In accordance with the second claimed variant of the test method, increasing the relative amplitude of the pulsations of the total pressure (ε) under conditions of a decrease in the air flow rate while blowing the model judges the reversal jets entering the through channel of the model of the nacelle. An increase in the relative amplitude of the pulsations of the total pressure by 0.2% with a decrease in the air flow velocity by 5 m / s indicates that reverse jets enter the inlet nozzle of the nacelle model.

The proposed operations of the aerodynamic test methods make it possible to achieve the indicated technical result - to fix the hit of the reverse jets of a power plant operating in thrust reverse mode when simulating the movement of the aircraft along the runway under conditions close to the full-scale conditions of movement of the aircraft over the earth's surface during power operation installation in thrust reverse mode.

The first version of the proposed method of aerodynamic tests gives more reliable results, since an increase in the temperature of the air flow at the inlet to the air intake gives good reason for concluding that reversible jets enter the inlet nozzle of the jet engine. However, the use of hot gas tests in this method complicates and complicates the experiment.

The second variant of the proposed method of aerodynamic testing is simpler compared to the first method, since there is no need to use hot gas during testing. This method can be recommended for rapid testing of aircraft models when operating their power plant in thrust reversal mode.

The experimental work of the authors showed that the rate of reinjection — the beginning of the reversal jets entering the inlet nozzle of the engine nacelle model, determined in accordance with the first variant of the proposed method (by “casting” the temperature), practically coincides with the results of determining the speed of reinjection in accordance with the second variant of the proposed test method (by "casting" the amplitude of the pulsations of the total pressure).

During aerodynamic tests of a passenger aircraft model, carried out in accordance with the first claimed variant, the re-injection speed was determined - the speed of the aircraft along the runway, at which the reversing jets of the power plant begin to fall into the inlet nozzle of the jet engine, for various operating modes power plant in reverse thrust mode and various slip angles relative to the air flow. In this case, the rate of reinjection was determined as the beginning of the temperature increase in the air intake with a change in the speed of the air flow created by the wind tunnel. Depending on the operating mode of the reversing device (the set value of the gas flow supplied to the reversing chambers) and the sliding angles with respect to the air flow, the re-injection speed can vary from 25 m / s to 55 m / s. The inventive test method, in addition, allows you to evaluate the effect of the temperature of the reverse jet on the speed of reinjection.

During aerodynamic tests in accordance with the second claimed test method, the experiments performed showed that in the absence of re-injection of reverse jets there are practically no pressure disturbances at the engine inlet of the aircraft model under study. Reversing jets entering the air intake are accompanied by a sharp increase in the amplitude of the pulsations of the total pressure at the engine inlet.

In accordance with the first embodiment of the proposed test method, it is most expedient to use a mixture of liquid fuel combustion products, for example kerosene, and air as the gas.

Moreover, in accordance with the first embodiment of the proposed method of aerodynamic tests, before supplying hot gas to the reversing chambers of the models of nacelles, the products of the combustion of liquid fuel can be mixed with air. While changing the air flow, the gas temperature can be brought to the set. When bringing the temperature of the mixture of products of combustion of liquid fuel and air to a predetermined temperature, it can be bypassed into the diffuser of the wind tunnel. After the mixture of the products of combustion of liquid fuel and air reaches the resulting gas, it can be sent to the reversing chambers of the models of nacelles. This increases the safety of testing.

According to a second embodiment of the inventive test method, it is most preferable to use air as a gas.

In addition, when conducting aerodynamic tests in accordance with the first and second claimed test methods when blowing a model of an aircraft with air flow, it is advisable to suck the boundary layer from the surface of the screen of the simulator of the runway in front of the model of the aircraft. The appropriateness of the additional introduction of this operation is explained by the following circumstance. Under natural conditions, the aircraft moves in a stationary air environment. Under the experimental conditions, the air moves, and the model of the aircraft is stationary. In this case, a boundary layer is formed on the surface of the screen, which can distort the results of studies, in order to avoid this, it is advisable to carry out the suction of the boundary layer from the surface of the runway simulator screen, which substantially brings the simulation conditions for the movement of the aircraft closer to full-scale ones.

The technical result is achieved by the inventive installation for aerodynamic testing as follows.

Installation for aerodynamic testing contains a screen simulator of the runway, an aircraft model, a vacuum system and a gas source.

The front end of the runway screen simulator is oval in plan. In addition, the screen simulator of the runway is made with the possibility of a turn around the vertical axis.

The model of the aircraft is installed on the screen simulator of the runway and is composed of a model of a glider and models of nacelles. Each of the nacelle models is mounted on the screen-simulator of the runway at the base and is equipped with a through channel for air flow. In the claimed solution, in the inlet nozzle of the through channel of each of the nacelles placed sensors receivers for measuring the parameters of the input stream. In addition, nacelles are equipped with reversing cameras with simulators of reversing devices. Simulators of reversing devices are configured to ensure the outflow of gas from the reversing chambers towards the incoming air flow.

The rarefaction system is connected by air ducts to the exits of the through channels of each of the nacelle models and is equipped with air suction means and a means of providing a predetermined level of air flow from the through channels of the nacelles.

The gas source is configured to generate gas with a predetermined temperature from a temperature range from ambient temperature to a temperature of 400 ° C. In addition, the gas source is configured to generate gas with a given flow rate. The gas source is connected by gas supply lines to the reversing cameras of nacelle models. At the same time, gas supply lines are passed through the bases of the models of nacelles.

The presence in the installation of a screen simulator of a runway with a complete model of an aircraft placed on it, made up of a model of a glider and models of nacelles, the possibility of a turn of a screen simulator of a runway and the execution of its front end with an oval shape in plan allows approximation of tests using installation in a wind tunnel to the full-scale conditions of the movement of the aircraft on the surface of the earth.

The implementation of nacelles with channels for the air flow, the outlets of which are connected by air ducts to a rarefaction system that allows air to be sucked out from the through channels with a predetermined flow rate, allows you to simulate the operation of the power plant while driving along the runway.

The presence in the models of nacelles of reversing chambers with simulators of reversing devices made with the possibility of gas flowing out of the reversing chambers towards the incoming air flow, and connected to a gas source that allows generating gas in a wide temperature range, starting from the ambient temperature, and a given flow rate allows simulate the operation of the power plant of the aircraft in thrust reversal mode. The ability to generate hot gas makes it possible to use the installation in accordance with the first embodiment of the proposed method. The ability to generate gas with an ambient temperature makes it possible to use the test apparatus in accordance with the second embodiment of the proposed method in the most economical and safe conditions.

The installation of sensor receivers for measuring the parameters of the input stream near the inlet nozzle of the nacelle models allows for fixing changes in the parameters of the input stream, which, in combination with the above, ultimately allows fixing the occurrence of reverse jets in the model of the nacelles under conditions close to the natural conditions of the aircraft’s movement ground at various modes of operation of the power plant in the mode of reverse traction.

In the inventive installation, the gas source may include a liquid fuel source, a gas heater and a mixing chamber. The output of the source of liquid fuel through the fuel line, equipped with a shut-off valve, can be connected to the first input of the heater. The second input of the heater in the claimed solution is connected through the first outlet of the tee to the compressed air supply line. It is advisable to equip the compressed air supply line with a valve, which makes it possible to control the flow of compressed gas. The output of the gas heater through the first controlled throttle in the claimed solution is connected to the diffuser of the wind tunnel, and through the second controlled throttle with the first input of the mixing chamber. The second input of the mixing chamber is connected to the second output of said tee. The output of the mixing chamber is connected to gas pipelines for supplying gas to the reversing chambers of the models of nacelles.

Such a schematic design solution of the gas source allows the generation of gas in a wide temperature range from ambient temperature to 400 ° C. By supplying liquid fuel to the gas heater, mixing the products of fuel combustion with compressed air in the mixing chamber and setting the flow rate of the products of combustion by the second controlled choke, the gas source can generate gas in a wide temperature range, which allows the first version of the proposed aerodynamic test method to be implemented.

The presence of a valve in the compressed gas supply line, the first and second controlled chokes allows you to generate gas with a given flow rate.

By shutting off the shut-off valve of the fuel line and thereby eliminating the burning of fuel in the gas heater, the gas source allows the generation of gas at ambient temperature, which is most appropriate to use when conducting tests in accordance with the second claimed embodiment of the test method.

The gas heater in the claimed solution may contain a cylinder-shaped housing with a combustion chamber and a nozzle placed inside it. The first inlet of the gas heater can be placed on the side wall of the housing and connected to the nozzle. At one end of the gas heater case, a second gas heater input may be placed, and at the other end, a gas heater output. The combustion chamber can be made in the form of a slotted thin-walled axisymmetric casing with an open end facing the outlet of the gas heater. It is advisable to place the combustion chamber inside the housing with a gap relative to it.

The proposed device gas heater allows you to efficiently and economically produce the burning of liquid fuel.

The front end of the runway simulator screen can be made with a rounded leading edge, which allows for an uninterrupted and slightly perturbed air flow over the runway simulator screen.

The screen simulator of the runway can be equipped with a transverse slit located in front of it and configured to ensure the overflow of the boundary layer from the upper surface of the screen simulator of the runway to its lower surface. This further brings the test conditions closer to field conditions.

In addition, on the lower surface of the runway simulator screen, visors can be placed in front of each of the slots, making it possible to change their tilt angles to the lower surface of the simulator screen, which allows controlling the flow of air flowing from the boundary layer on the upper surface a screen simulator of the runway to its lower surface, which further expands the possibilities of modeling field conditions.

In the inventive installation, the screen simulator of the runway can be made in the form of a flat panel, including the upper and lower casing and transverse partitions located between them, while the slit of the screen simulator can be made in the form of slots on the lower and upper casing of the screen- simulators that are shifted relative to each other in the direction of air flow, and the said transverse partitions can be placed near the slots.

The claimed solutions to the methods of aerodynamic testing and installation for their implementation are illustrated by the following materials:

figure 1 - General view of the installation in the working part of the wind tunnel,

figure 2 - General view of the installation in the working part of the wind tunnel in a plan view,

figure 3 is an enlarged side view of the installation with a model of a nacelle (in section) and with a model of a glider,

figure 4 - model of a nacelle (side view),

figure 5 - model of a nacelle ((view A from figure 4), the sensors of the parameters of the input stream and their installation conditionally not shown),

6 is a model of a nacelle (section BB of figure 4),

Fig.7 is a longitudinal section of a model of a nacelle with receivers of temperature measurement sensors (section BB of Fig.5),

Fig.8 is a typical view of the dependence of the temperature of the air flow near the inlet of the channel of the model of the nacelle from the speed of blowing,

Fig.9-11 - experimental dependence of the temperature of the air flow near the inlet of the model nacelle’s channel on the blowing speed at various levels of flow of hot gas supplied to the reversing chambers, and sliding angles relative to the direction of air flow of the wind tunnel,

12 is a characteristic view of the pulsations of the amplitude of the total pressure of the relative average value,

13-15 are graphs of the dependence of the change in the relative amplitude of the pulsations of the total pressure 8 at the inlet of the nacelle model when the blowing speed changes at different levels of gas flow and at different slip angles,

Fig is a diagram of a vacuum system,

Fig is a diagram of a gas source,

Fig is a diagram of a gas heater,

Fig is a diagram of the device screen simulator runway with a drain drain boundary layer,

Fig. 20 is a front view of a runway simulator screen (side view),

Fig.21 is a graph of the dependence of the rate of reinjection on the change in gas flow supplied to the reversing chambers obtained using the first and second variants of the aerodynamic test method.

The inventive methods of aerodynamic testing are performed as follows.

When conducting tests in accordance with the first and second claimed variants use the model of the aircraft 1, composed of a model of a glider 2 and models of engine nacelles 3 (see figures 1, 2, 3). A model of the aircraft 1 is placed in the working part of the wind tunnel (see figure 1). Each of the models of the engine nacelles 3 is equipped with a through channel 4 for the air flow, a reversing chamber 5 and simulators of the reversing devices 6 (see Figs. 3-5).

In accordance with the first and second claimed variants of the aerodynamic test method when placing the model of the aircraft in the working part of the wind tunnel, the model of the airframe and model of the nacelle are mounted on the screen simulator 7 of the runway. Then the screen simulator 7 of the runway is deployed together with the model of the aircraft 1 relative to the vertical axis 8 at a predetermined angle of slip relative to the direction of air flow of the wind tunnel. The turn of the runway screen simulator to angles of 15-20 degrees from the axis of the wind tunnel makes it possible to simulate the movement of the aircraft along the runway with a cross wind, which is especially important when conducting tests with simulated reverse thrust. The combination of the task of the speed of the air flow of the wind tunnel in the range of 10-80 m / s with the rotation of the screen-simulator of the runway within 15 ... 20 degrees from the axis of the wind tunnel allows you to simulate the movement of the aircraft along the runway with a side wind of 0 ... 15 m / s.

In accordance with the first and second variants of the proposed test method, blowing the model of the aircraft air flow of the wind tunnel. Blowing the model is accompanied by a monotonous decrease in the air flow velocity from a speed value close to the landing speed of the aircraft under natural conditions. Due to this, a change in the speed of the oncoming flow is simulated when the aircraft moves along the runway. Thus, a change in the speed of blowing of an aircraft model in the range of 10 ... 80 m / s allows us to simulate the movement of a passenger aircraft along the runway.

In accordance with the first and second variants of the proposed method of aerodynamic tests when blowing aircraft models simulate air flow through the engines, while the air flow of the wind tunnel is passed through the channels 4 of the models of the nacelles 3, it is sucked from the through channels 4 with a given flow rate and output it for limits of the working part of the wind tunnel. To simulate the operation of the air-jet engines of modern passenger aircraft, it is sufficient to provide the possibility of suction from the output nozzles of the channels of the models of the air nacelle with a flow rate of up to 5 kg / s.

In accordance with the first and second variants of the proposed method when conducting aerodynamic tests simulate reversible jets 12 of jet engines (see Fig.6).

In accordance with the first embodiment of the proposed aerodynamic test method, hot gas with a given flow rate is supplied to the reversing chambers of 5 models of engine nacelles 3 (see Fig. 7). When conducting tests in accordance with this variant of the method, it is advisable to supply gas to the reversing chambers with a temperature not exceeding 300 ° C. The flow rate of hot gas supplied to the reversing chambers is selected from the simulation conditions, as a rule, it should correspond to the fraction of the engine air flow taken to reverse the thrust. To simulate the operation of air-jet engines of modern passenger aircraft, it does not exceed 3-5 kg / s.

In accordance with the first embodiment of the proposed test method, hot gas is passed outside the model of the nacelle (see Fig.6) and is directed under the influence of simulators of reversing devices 6 towards the incoming air flow.

In accordance with the first variant of the proposed method of aerodynamic tests when blowing the model and modeling the reversible jets 12 measure the temperature of the stream near the inlet of the through channel of the model of the air intake (see Fig.7). It is sufficient to measure the temperature of the input stream in one of the models of nacelles. When measuring the temperature of the flow near the inlet of the through channel of the air intake model, it is practically enough to measure with a step changing the air flow velocity from 0.5 to 20 m / s. To increase the accuracy of temperature fixation in the through channel of the nacelle model, it is advisable to measure the temperature at several points located practically in the same plane, as shown in Fig. 7, and determine the temperature of the air flow as the average value of temperature measurements at these points.

On Fig shows a characteristic view of the dependence, which can be obtained during aerodynamic tests in accordance with the first claimed variant of the method. With a decrease in the speed of blowing from the landing speed of the aircraft (approximately 80 m / s), the temperature of the inlet flow gradually decreases from 14 ° C ... 16 ° C to 10 ° C ... 12 °, then a sharp increase in the temperature of the air flow begins, which indicates the fixation of hit into the inlet nozzle of the reversible jet engine model. The corresponding air flow rate is the rate of reinjection - V _p . So, the engine operation parameters and design features of the nacelle model that were used during the experiment, the results of which are shown in Fig. 8, led to a re-injection speed of approximately 45 m / s.

With a decrease in the blowing speed of the model (see Fig. 8), the flow temperature at the inlet of the model first gradually decreases: with a decrease in the air flow velocity by 5 m / s, the temperature decreases by no more than 1-2 degrees. Then the temperature rises. An increase in temperature by more than 2 degrees with a decrease in the air flow rate by 5 m / s indicates that reverse jets enter the inlet nozzle of the nacelle model.

When implementing the first proposed variant of the test method, it is most expedient to use a mixture of products of combustion of liquid fuel and air as the gas. When using, for example, kerosene with a combustion temperature of 1000 ... 1100 ° C as a liquid fuel, it is advisable to mix its combustion products with high pressure air and lower the temperature of the mixture to 300 ... 400 ° C and send this mixture of kerosene and air combustion products to reversing chambers models of nacelles. Before supplying hot gas to the reversing chambers, it is advisable to mix the liquid fuel combustion products with air and, changing the air flow rate, bring the gas temperature to a predetermined (300 ... 400 ° C), bypassing the gas obtained in the diffuser of the wind tunnel. After the gas reaches a predetermined temperature, for example, to a temperature of 300 ... 400 ° C, it is advisable to redirect the gas through the gas supply pipelines 33 (see FIGS. 1, 16, 17) to the reversing chambers of the nacelle models.

Use in aerodynamic tests of the first variant of the proposed method allows to obtain a wide range of results. Figure 9-11 shows the test results of the model of the aircraft when simulating its movement along the runway at different slip angles relative to the direction of the air flow of the wind tunnel (β = 0 °, β = 5 °, β = 10 °, respectively). Each of FIGS. 11–13 shows the test results related to fixing the reversal jets entering the channel of the nacelle model at various levels of flow of hot gas supplied to the reversing chambers. With a decrease in the speed of blowing, the temperature at the inlet to the through channel of the nacelle decreases. The ingress of reverse engine jets into the inlet nozzle is accompanied by a sharp increase in temperature: when the blowing speed decreases by 5 m / s, the temperature may increase by 10 ... 12 ° C. An increase in temperature in the inlet nozzle of the nacelle by 2 degrees with a decrease in the blowing speed by 5 m / s is the basis for fixing the reversal jets entering the through channel of the nacelle model. Experimental data show that the speed of the aircraft, at which the reversible jet of the engine begins to fall into the inlet nozzle — the rate of re-injection, can vary with the sliding angle from β = 0 ° to β = 5 ° and then to β = 10 ° from 30 ... 35 m / s up to 20 ... 25 m / s and up to 15 ... 20 m / s.

In accordance with the second variant of the proposed method of aerodynamic tests in the reversing chamber 5 of the model of the nacelle 3 (see Fig.7) serves gas with a given flow rate. The flow rate of hot gas supplied to the reversing chambers is selected from the simulation conditions, as a rule, it should correspond to the fraction of the engine air flow taken to reverse the thrust. To simulate the operation of air-jet engines of modern passenger aircraft, it does not exceed 3-5 kg / s.

When using the second embodiment of the aerodynamic test method, it is most preferable to use air as the gas. When conducting tests in accordance with the second test method, it is most expedient to supply gas with an ambient temperature to the reversing chambers.

In accordance with the second variant of the proposed test method, the gas is passed outside the model of the engine nacelle (see Fig.6) and then directed under the influence of simulators of reversing devices 6 towards the incoming air flow.

In accordance with the second variant of the proposed method of aerodynamic testing when blowing the model measure the total pressure P (τ) (τ - current time) flow near the entrance of the through channel. Measurement of the total pressure in the air flow at the inlet to the through channel of the nacelle model is sufficient to carry out in one of the nacelle models. When measuring the total pressure in the flow near the inlet of the through channel of the air intake model, it is practically enough to measure with a step changing the air flow velocity from 0.5 to 20 m / s.

To increase the accuracy of fixing the total pressure in the channel of the model of the nacelle, it is advisable to measure at several points, as shown in Fig.7. It is advisable to place the points for measuring the total pressure practically in the same plane and take the average value as the total pressure P _o .

Full pressure P (τ) in accordance with the second variant of the test method, it is advisable to carry out with a frequency of about 10 ... 20 kHz. This makes it possible to track fluctuations in total pressure from the average value of P _o (see Fig. 12). In accordance with the second embodiment of the test method for measuring the total pressure at each measurement point, calculate the parameter of the relative rms amplitude of the pulsations of the total pressure ε _i (see Fig. 12)

where δPo (τ) is the deviation of the total pressure from its average value of P _o at the time τ, T is the averaging period, which is advisable to choose not exceeding about 20 seconds. By averaging the calculated values of ε _i over all (n) points, the parameter of the relative rms amplitude of the pulsations of the total pressure ε can be calculated

Figures 13-15 show the dependences of the relative root-mean-square amplitude of the pulsations of the total pressure at the inlet of the nacelle model versus the model airflow rate at various gas flow rates through the reversing chambers of the nacelle models and at different slip angles with respect to the air flow direction of the wind tunnel: β = 0 ° ( Fig. 13), β = 5 ° (14) and β = 10 ° (Fig. 15). Experimental studies have shown that when the blowing speed decreases from the value corresponding to the aircraft landing speed, in the absence of reverse jet re-injection, there are practically no dynamic pulsation perturbations at the entrance to the nacelle model: ε is less than 0.1%. The beginning of the reversal jets entering the through channel of the nacelle model (see zone 11 in Figs. 13-15) is accompanied by a sharp increase in the amplitude of fluctuations of the total pressure pulsations at the entrance to the nacelle model, the average value of the rms amplitude of the total pressure pulsations at the entrance to the nacelle model can reach 2 ... 3% or more.

Thus, by increasing the relative amplitude of the pulsations of the total pressure while decreasing the air flow rate, one can judge whether the reverse jets hit the inlet nozzle of the aircraft’s nacelle. Experiments show that an increase in the relative amplitude of the pulsations of the total pressure by 0.2% with a decrease in the air flow velocity by 5 m / s indicates that reversible jets enter the inlet nozzle of the nacelle model.

When blowing the model of the aircraft with air flow in accordance with the first and second claimed variants of the test method, it is advisable to suck the boundary layer from the surface of the screen of the simulator of the runway in front of the model of the aircraft, for example, as shown in Fig. 19. The expediency of this operation is due to the fact that the boundary layer under the models of nacelles can significantly distort the test results compared to the full-scale conditions. Using the drain of the boundary layer from the upper surface of the screen-emitter of the runway to its lower surface in front of the aircraft model leads to the fact that the boundary layer behind the drain gap is practically absent.

To implement the claimed methods of aerodynamic testing, it is most advisable to use the inventive installation for aerodynamic testing, although for the implementation of the considered test method can be used with another device.

The inventive aerodynamic installation is arranged as follows.

The installation comprises a screen simulator 7 of the runway, a model of the aircraft 1, a vacuum system and a gas source. The installation is located in the working part of the wind tunnel, for example, a wind tunnel with an open working part of T-104 (see, for example, A.N. Radzig. Experimental hydroaeromechanics. M., published by MAI, 2004, pp. 273-274) between its nozzle and diffuser.

The screen simulator 7 of the runway is rotatable relative to the vertical axis 8. At the same time, as shown in figure 1, the screen simulator of the runway can be placed in the working part of the wind tunnel on the racks 13 located on the control cabin 14, and the control cabin 14 and the screen simulator 7 of the runway can be made with the possibility of joint rotation around the vertical axis 8. When designing an installation for conducting aerodynamic tests of a model of an aircraft In conditions of its movement along the runway, it is advisable to provide for the possibility of opening the runway simulator screen with the model of the aircraft up to an angle of 15-20 degrees from the axis of the wind tunnel.

The front end 15 of the screen-simulator 7 of the runway (see figure 2), it is advisable to perform an oval shape in plan. The front edge of the runway simulator screen is expediently rounded, as shown in FIG.

In the front of the screen simulator of the runway in front of the model of the aircraft, it is advisable to place a transverse slit 16 (see figure 2, 19). The gap should be made with the possibility of ensuring the overflow of the boundary layer from the upper surface of the screen-simulator of the runway to its lower surface. As shown in FIG. 2, a slot in the runway screen simulator can be made of four separate sections.

The screen simulator of the runway can be made in the form of a flat panel (see Fig. 19) containing the upper and lower sheaths 17, between which the transverse partitions are located 18. In this case, the slit of the screen simulator is made in the form of slots on the lower and upper skins of the screen simulator, which are shifted relative to each other in the direction of air flow. Mentioned transverse partitions are placed near the slots.

A visor 19 can be placed on the lower surface of the runway screen simulator in front of each of the slots. When the visor flows around it, a tear-off zone with a reduced pressure is formed behind it, which ensures overflow of the boundary layer from the upper surface of the runway simulator screen to the lower surface. It is most preferable to make a visor with the possibility of changing its angle of inclination α to the lower surface of the screen simulator, which allows you to adjust the air flow from the boundary layer flowing from the upper surface of the screen simulator runway to the lower surface.

To measure the thickness of the boundary layer on the upper surface of the screen-simulator can be used combs 20, which can be installed on the upper surface of the screen-simulator of the runway in front of the drain hole of the boundary layer and behind it.

The model of the aircraft 1 in the claimed solution of the installation for aerodynamic testing is composed of a model of a glider 2 and models of a nacelle 3. A model of a glider and a model of a nacelle can be installed relative to each other with a gap of 23 δ (see Figs. 3, 16). At the same time, the model of the glider 2 can be fixed on the tail holder 21. The tail holder 21 can be installed on the screen-simulator 7 of the runway. The model of the aircraft on the tail holder must be installed relative to the screen simulator of the runway in a position corresponding to the position of the aircraft when it moves along the runway.

Models of nacelles 3 are installed on the bases 22 (see figure 3) on the screen-simulator 7 of the runway.

Each of the models of nacelles 3 (see Figs. 3-6) is equipped with a through channel 4 for air flow, a reversing chamber 5 and simulators of reversing devices 6. Simulators of reversing devices 6 are configured to allow gas to flow out of the reversing chambers towards the incoming air flow. To expand the range of studies in the design of the model of a nacelle, it may be possible to use reversible devices with different geometry of simulators, which gives an additional opportunity to search for optimal design solutions for reversing devices in an experiment.

Reversible cameras 5 can be made in the form of an annular cavity, covering the through channel of the model of the nacelle.

Near the entrance of the channel models of nacelles placed sensors receivers for measuring the parameters of the input stream 24 (see Fig.7). As sensors of the parameters of the input stream, temperature sensors, full pressure sensors can be used. It is most preferable to place the sensors of the input flow parameters in the through channel of the nacelle model in practically the same plane, which ensures the measurement of the input flow parameters over the entire channel section. When testing an aircraft equipped with several engine nacelles, for example, a passenger aircraft with underwing engines with two engine nacelles, one of the models of the engine nacelles can be equipped with sensors for the input flow parameters to measure its temperature, while other models of the engine nacelles can have sensors for the input parameters flow for measuring the total pressure, as shown in Fig.7.

Thermocouples can be used as sensors for input flow parameters for temperature measurement.

Stationary pressure sensors can be used as sensors of the input flow parameters for measuring the total pressure, providing the possibility of recording the total pressure and averaging its value over a significant interval, for example, sensors of the MSP-32 type. In addition, low-inertia pressure sensors can be used as full pressure sensors, providing the possibility of recording the total pressure with a frequency of the order of 10 ... 20 kHz, from the measurements of which the deviation δРо (τ) of the total pressure from its average value of P _o and averaging of this can be calculated deviation δРо (τ) on the period (T) up to 20 s.

The rarefaction system (see Fig. 16) includes air ducts 25 connected to the outputs 26 of the channels 4 of each of the nacelle models, air suction means 27 and means for providing a predetermined level of air flow 28 from the channels of each of the nacelles. The inlet of the duct 25 is connected to the output 26 of the channel of each of the nacelles. To exhaust air from the channels of the nacelle models, the outlet of the air duct 25 is connected to the air suction means 27 from the channels of the models of the nacelles, which can be used, as shown in Fig. 16, an ejector connected to a high pressure air source, such as a gas tank. Means for ensuring a given level of air flow 28, sucked from the channels of the models of nacelles, can be performed in this case, for example, in the form of a multi-position damper installed in the path for supplying high pressure air to the ejector. Other constructive options for the implementation of the rarefaction system are also possible to ensure air suction from the channels of the models of nacelles with a given flow rate.

The gas source (see Fig. 17) is configured to generate gas. In this case, the gas source is configured to control the temperature of the gas from the ambient temperature to a temperature of 400 ° C. In addition, the gas source of the inventive installation is made with the provision of regulation of its flow. The gas source is connected through the gas supply lines 33 (see Fig. 16, 17) to the reversing cameras of the nacelle models 5. The gas supply lines are passed through the bases of the models of the nacelles 22.

The gas source (Fig. 17) may include a liquid fuel source 30, a gas heater 31, a mixing chamber 32, and gas supply pipelines 33 to the reversing chambers 5 of the nacelle models 3.

The fuel source 30 is expediently performed with the possibility of supplying liquid fuel to the gas heater under pressure, for example, 5 ... 15 MPa, with a flow rate of 0.1 ... 0.5 kg / s, and the possibility of controlling the flow rate of liquid fuel supplied to the heater from nominal to zero and discharge liquid fuel. In addition, the fuel source should, for safety reasons, be able to limit the maximum pressure of the supplied liquid fuel. The output of the fuel source 30 is connected to the fuel line 34.

The fuel line 34 may be equipped with a shut-off valve 35, configured to bypass liquid fuel through the fuel line to the gas heater 31 or shut off the supply of liquid fuel to the gas heater. The shut-off valve 35 can be made in the form of a three-position distributor with servo action, valves and a spool valve having three positions: neutral, fuel supply to the heater, fuel discharge to the drain. In this neutral position, the fuel supply line 34 to the gas heater 31 is closed.

The gas heater 31 (see Fig. 18) should provide for the burning of liquid fuel. The first inlet 36 of the gas heater is connected to the fuel line 34. The second inlet 37 of the gas heater is connected through the first outlet of the tee 40 to the compressed air supply 38. It is most expedient to use kerosene as liquid fuel in the installation, while burning it in the heater can be obtained gas with a temperature of 1000 ... 1100 ° C.

The line 38 of the compressed air supply is equipped with an adjustable valve 39, made with the possibility of regulating the flow of compressed air.

The output of the gas heater 41 through the first controlled throttle 42 is connected to the diffuser of the wind tunnel and through the second controlled throttle 43 is connected to the first input 44 of the mixing chamber 32. The second input 45 of the mixing chamber 32 is connected to the second output of the tee 40. The output of the mixing chamber 32 is connected to the supply gas pipelines 33 gas in reversing chambers of 5 models of engine nacelles 3.

The gas heater 31 (see Fig. 18) may comprise a cylinder-shaped housing 46, inside which a combustion chamber 47 with a nozzle 48 is placed. The first inlet 36 of the gas heater mentioned above is placed on the side wall of the housing, made in the form of a fitting and connected by a nozzle 48. On the first the end of the gas heater body, made in the form of a flange, the second inlet 37 of the gas heater is placed, and at the second end, also made in the form of a flange, the output of the gas heater 41. The combustion chamber 47 is made in the form of a thin-walled axisymmetric casing in which slots 50 are made. One end of the casing of the combustion chamber is closed, a nozzle 48 is placed on it, the other end of the casing is open and faces the outlet 41 of the gas heater. The combustion chamber is placed with a gap relative to the walls of the housing.

During aerodynamic tests, an aircraft model made up of a model of a glider and models of nacelles is placed in the working part of the wind tunnel on a screen simulating a runway. A screen simulator of the runway is deployed together with the model of the aircraft at a predetermined sliding angle relative to the direction of the air flow of the wind tunnel and blowing the model of the aircraft with air flow of the wind tunnel. Blowing the aircraft model begins at a speed close to the landing speed of the aircraft. When blowing using means of a wind tunnel, the air velocity is monotonously reduced.

When blowing the model, the air flow is passed through the through channels of the models of the nacelles and it is sucked out from the through channels using the air suction means 22. The suction is carried out with a predetermined flow rate, setting it using the flow control means 28. If necessary, the suction flow rate is changed during the blowing process air.

When simulating the reversing jets of the power plant with gas at a temperature close to the ambient temperature in accordance with the second variant of the test method, the shut-off valve 35 is closed, and using valve 39, the first 42 and second 43 controlled throttles, gas is supplied to the reversing chambers of the nacelles with a given level expense.

When simulating reversible jets of a power plant with a temperature exceeding the ambient temperature in accordance with the first claimed variant of the test method, the shut-off valve 35 is opened and liquid fuel is supplied to the heater. Compressed air is supplied through a valve 39 and a tee 40 to a heater, where liquid fuel is burned. At the beginning of operation, the controlled throttle 43 is closed, and through the throttle 42, gas from the heater is directed to the diffuser of the wind tunnel 47. After the set temperature has been set, hot gas is sent to the reversing chambers of the nacelle models.

When blowing an aircraft model, input flow parameter sensors measure the necessary parameters.

The inventive installation for aerodynamic testing provides testing in accordance with the first and second claimed test methods. On Fig shows the results of experiments to determine the rate of reinjection - the beginning of the reversal jets entering the inlet nozzle of the air intake model depending on the gas flow through the reversing device, obtained in accordance with the first inventive test method (curve 51) and in accordance with the second variant of the inventive method tests (curve 52). A comparison of the results shows that the results are practically the same.

In addition to conducting experiments in accordance with the claimed methods of aerodynamic tests, the inventive installation can be used for other tests to study the effect of reverse jets on the characteristics of the aircraft and its movement along the runway.

Claims (14)

1. The method of aerodynamic testing of an aircraft model made up of a model of a glider and models of nacelles with through channels for air flow and reversing chambers with simulators of reversing devices, in which the model of the aircraft is placed in the working part of the wind tunnel on the screen simulator of the runway, deploy it together with the model of the aircraft at a given angle of slip relative to the direction of air flow of the wind tunnel, blow the model flying of an airborne apparatus with an air flow of a wind tunnel, accompanied by a monotonous decrease in air velocity from a value close to the landing speed of the aircraft, while blowing the models simulate air flow through the engines, passing the air flow of the wind tunnel through the channels of the nacelle models, sucking it from the channels with a given level flow and taking it outside the working part of the wind tunnel, simulate the reversing jets of the power plant, feeding mode into the reversing chambers to her engine nacelles hot gas with a given flow rate and directing it with the action of the mentioned simulators of reversing devices towards the incoming air flow, measure the temperature of the flow near the inlet of the through channel of at least one of the models of the nacelles, and the reversal jets of the power plant in the channel model of the nacelle. 2. The method of aerodynamic testing according to claim 1, characterized in that the gas used is a mixture of products of combustion of liquid fuel and air. 3. The aerodynamic test method according to claim 2, characterized in that when blowing the model of the aircraft before supplying hot gas to the reversing chambers, the products of combustion of liquid fuel are mixed with air and, changing the air flow rate, bring the gas temperature to a predetermined one, bypassing the gas obtained into the diffuser of the wind tunnel, and after the gas reaches the set temperature, they direct it into the reversing chambers of the models of nacelles. 4. The aerodynamic test method according to claim 1, characterized in that when blowing the model of the aircraft with air flow, the boundary layer is sucked off the surface of the screen of the simulator of the runway in front of the model of the aircraft. 5. The method of aerodynamic testing of a model of an aircraft composed of a model of a glider and models of engine nacelles with through channels for air flow and reversing chambers with simulators of reversing devices, in which the model of the aircraft is placed in the working part of the wind tunnel on the screen simulator of the runway, unfold it together with the model of the aircraft at a given angle of slip relative to the direction of the air flow of the wind tunnel, blow the model flying of an airborne apparatus with an air flow of a wind tunnel, accompanied by a monotonous decrease in air velocity from a value close to the landing speed of the aircraft, while blowing the models simulate air flow through the engines, passing the air flow of the wind tunnel through the channels of the nacelle models, sucking it from the channels with a given level flow and taking it outside the working part of the wind tunnel, simulate the reversing jets of the power plant, feeding mode into the reversing chambers to it the nacelle gas with a given flow rate and directing it with the influence of the mentioned simulators of reversing devices towards the incoming air flow, measure the total flow pressure near the channel inlet of at least one of the nacelle models, calculate the relative amplitude of the pulsations of the total pressure of the inlet flow, increasing which is judged on the entry of reversible jets into the through channel of the nacelle model. 6. The aerodynamic test method according to claim 5, characterized in that air is used as gas. 7. The aerodynamic test method according to claim 5, characterized in that when blowing the model of the aircraft with air flow, the boundary layer is sucked off the surface of the screen of the simulator of the runway in front of the model of the aircraft. 8. Installation for aerodynamic testing, containing a screen simulator of the runway, made with the front end of the oval in plan and with the possibility of rotation relative to the vertical axis, a model of the aircraft installed on the screen simulator of the runway and made up of the model of the glider and models of nacelles, each of which is mounted on the screen-simulator of the runway at the base and is equipped with a through channel for air flow, near the entrance of which sensors are placed for measuring the parameters of the input flow, a reversing chamber with simulators of reversing devices, made with the possibility of gas flowing out of the reversing chambers towards the incoming air flow, a rarefaction system connected by air ducts with the outlets of the through channels of each of the nacelle models and equipped with air suction means and means for providing a predetermined the level of air flow from the channels of the nacelles, a gas source that provides the ability to generate gas with a given flow rate and a given pace Aturi the range from ambient temperature to a temperature of 400 ° C and a predetermined flow rate and connected Gassing highways through said missing base with reversing chambers nacelles models. 9. Installation for aerodynamic tests of claim 8, characterized in that the gas source includes a liquid fuel source, a gas heater and a mixing chamber, while the output of the liquid fuel source is connected through a fuel line equipped with a shut-off valve, with the first input of the heater, the second input which is connected through the first outlet of the tee to the compressed air supply line, equipped with an adjustable valve made with the possibility of regulating the flow of compressed gas, the gas heater output through the first controlled throttle is connected to the wind tunnel diffuser, and through the second controlled throttle to the first input of the mixing chamber, the second input of the mixing chamber is connected to the second output of the said tee, and the output of the mixing chamber is connected to gas pipelines for supplying gas to the reversing chambers of the nacelle models. 10. Installation for aerodynamic tests according to claim 9, characterized in that the gas heater comprises a cylinder-shaped housing with a combustion chamber and an injector placed inside it, while the first inlet of the gas heater is placed on the side wall of the housing and connected by an injector at one end of the gas heater housing the second input of the gas heater is placed, and the gas heater output is at the other end, the combustion chamber is made in the form of a thin-walled axisymmetric casing provided with slots with an open end facing the outlet revatelya gas, and placed with a gap relative to the housing. 11. Installation for aerodynamic testing of claim 8, characterized in that the front end of the screen simulator of the runway is made with a rounded front edge. 12. Installation for aerodynamic testing of claim 8, characterized in that the screen simulator of the runway is provided with a transverse slit configured to allow overflow of the boundary layer from the upper surface of the screen simulator of the runway to its lower surface. 13. Installation for aerodynamic testing according to item 12, characterized in that on the lower surface of the screen simulator of the runway in front of each of the slots are visors made with the possibility of changing their angles to the bottom surface of the screen simulator. 14. Installation for aerodynamic tests according to item 12, characterized in that the screen simulator of the runway is made in the form of a flat panel including upper and lower casing and transverse partitions located between them, while the slit of the screen simulator is made in the form the slots on the lower and upper casing of the screen simulator, which are shifted relative to each other in the direction of air flow, and the said transverse partitions are located near the slots.

Images