CN112485013A - Single turbofan engine nacelle surface pressure measurement test device with turbine power simulation and pressure measurement test method - Google Patents
Single turbofan engine nacelle surface pressure measurement test device with turbine power simulation and pressure measurement test method Download PDFInfo
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- CN112485013A CN112485013A CN202011279452.XA CN202011279452A CN112485013A CN 112485013 A CN112485013 A CN 112485013A CN 202011279452 A CN202011279452 A CN 202011279452A CN 112485013 A CN112485013 A CN 112485013A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
Abstract
The invention discloses a single turbofan engine nacelle surface pressure measurement test device with turbine power simulation and a pressure measurement test method, wherein the pressure measurement test device comprises the following steps: the pressure measuring nacelle is provided with a plurality of pressure measuring holes along the radial direction of the pressure measuring nacelle at the air inlet and the outer surface, and a front end supporting mechanism is arranged below the pressure measuring nacelle; a hub is arranged in the pressure measuring short cabin, and a fan blade disc is arranged on the hub; the turbine is arranged in the turbine case; the turbine casing is arranged on the rear end supporting mechanism; the pressure measuring harrow and the culvert guide vane are fixedly arranged on the supporting rod. The method can accurately simulate the pneumatic design key parameters such as the contour dimension, the flight Mach number, the air intake flow coefficient and the like of the pressure measuring nacelle, realize the accurate measurement of the air inlet and the outer surface pressure of a single turbofan engine nacelle model, provide the original data of pneumatic load distribution for the calculation of the structural strength, and provide test basis for the research of the nacelle streaming characteristic and the overall performance of the airplane.
Description
Technical Field
The invention belongs to the technical field of measuring surface pressure of a turbofan engine nacelle model, and particularly relates to a single turbofan engine nacelle surface pressure measuring test device with turbine power simulation and a pressure measuring test method.
Background
The nacelle is a fairing of an outboard turbofan engine of an airplane, and the design and layout problems of the nacelle are always important problems in the overall design of the airplane. Nacelle contour design is an important aspect of nacelle design and layout, the primary objective being to provide a compact streamlined contour that encompasses the entire engine with minimal impact on engine and aircraft performance.
The surface pressure distribution test of the individual nacelle is an important means for researching the aerodynamic characteristics of the aircraft and verifying whether the numerical calculation method is correct. The purpose of the single nacelle pressure test is to measure the pressure distribution on the surface of the nacelle, provide the original data of the aerodynamic load distribution for the calculation of the structural strength, and provide the test basis for the research of the bypass flow characteristic of the nacelle and the overall performance of the airplane. The position of the minimum pressure point on the nacelle, the position of the shock wave, whether the air flow is separated or not, the positions of the lift force, the pressure difference resistance and the pressure center acting on the model and the like can be determined through the measurement of the distribution of the surface pressure of the nacelle.
A simulation method for air inlet and exhaust of a turbofan engine nacelle mainly comprises a blocking cone model, a ventilation model, a jet injection model, an air inlet injection model and a power simulator (TPS) model, and the simulation degrees of various simulation modes on the air inlet geometric shape, the exhaust geometric shape, the air inlet flow, the exhaust flow and the air inlet and exhaust interference of the nacelle are different. The influence of the air intake and exhaust of the nacelle on the aerodynamic performance of the nacelle is an important factor to be considered for carrying out the wind tunnel test of the individual nacelle. In comparison, the power simulation test with the turbine is the most advanced means for developing the aerodynamic characteristic test and verifying the numerical calculation method at the design stage of the turbofan engine nacelle at present.
Disclosure of Invention
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages described hereinafter.
To achieve these objects and other advantages in accordance with the purpose of the invention, there is provided a turbofan engine nacelle surface pressure measurement testing apparatus with a turbine power model, comprising:
the front end supporting mechanism is provided with a pressure measuring nacelle, and a plurality of pressure measuring holes are distributed on the air inlet and the outer surface of the pressure measuring nacelle along the radial direction of the pressure measuring nacelle; a pressure measuring pipeline is arranged in the front end supporting mechanism, one end of the pressure measuring pipeline is positioned at a pressure measuring hole and at the bottom of the pressure measuring nacelle, and the other end of the pressure measuring pipeline is connected with a pressure sensor;
a hub is installed in the pressure measuring short cabin, and a fan blade disc is installed on the hub; one end of the transmission shaft is fixedly connected with the propeller hub, the other end of the transmission shaft is provided with a turbine, a support rod and a turbine case are arranged outside the transmission shaft, the turbine is positioned in the turbine case, and the support rod is fixedly connected with the turbine case; the turbine casing is arranged on the rear end supporting mechanism;
the pressure measuring rake is positioned in the pressure measuring short cabin and close to the outlet, and a gap is formed between the pressure measuring rake and the pressure measuring short cabin; the culvert guide vane is arranged at the end part of the supporting rod and is positioned between the fan blade disc and the pressure measuring rake, and a gap is arranged between the culvert guide vane and the pressure measuring nacelle.
Preferably, the structure of the front end support mechanism includes:
the nacelle base is provided with a nacelle bracket above and is arranged on the wall surface of the wind tunnel through bolts, and the nacelle base is fixed on a wind tunnel wall plate through bolts; the pressure measuring nacelle is arranged on the nacelle bracket;
the structure of the rear end supporting mechanism comprises:
a support joint on which the turbine case is disposed;
and the wind tunnel attack angle mechanism is fixed below the supporting joint through a pin and a bolt.
Preferably, the supporting rod is provided with a culvert fairing through a screw, and the culvert fairing covers the connecting part of the pressure measuring rake and the supporting rod.
Preferably, a wedge-shaped angle changing sheet is arranged below the nacelle base.
Preferably, the pressure measuring nacelle is provided with 6-8 pressure measuring holes with cross sections in the radial direction.
Preferably, wherein the nacelle stand is streamlined in cross section.
Preferably, the pressure measuring lines are arranged in the nacelle stand and the nacelle base.
A single turbofan engine nacelle surface pressure measurement test device with turbine power simulation comprises the following pressure measurement test methods: the whole pressure measurement test device is placed in a wind tunnel, a turbine is driven to rotate through high-pressure gas in the wind tunnel, and then a transmission shaft and a fan blade disc are driven to rotate through the turbine so as to obtain pressure distribution characteristics of an air inlet and the outer surface of a pressure measurement nacelle under the influence of air inlet and exhaust in a simulated flight state; the total pressure of the incoming flow, the Mach number, the fan pressure ratio and the incidence angle conditions of the pressure measuring nacelle are changed, and the short collection time is obtainedThe signals of the pressure measuring hole and the pressure measuring rake of the cabin are processed by data to obtain a flow coefficient phi and a pressure coefficient C of the pressure measuring nacellepiAnd further acquiring the rule of influence of the air intake and exhaust on the pressure distribution of the pressure measuring nacelle, wherein the data processing step comprises the following steps of:
step one, measuring pressure coefficient C of air inlet and surface of nacellepiObtained by the following formula:
wherein, PiIs the static pressure value of the ith point on the surface of the pressure measuring nacelle, P∞For static pressure of incoming flow, q∞For the pressure of the incoming flow, q∞The calculation method comprises the following steps:
wherein M is∞For a given incoming flow Mach number, gamma is the specific heat ratio of the incoming flow medium, of the air medium
Step two, calculating the actual flow of the flow pipe where each pressure measuring point on the pressure measuring rake is located
The calculation method comprises the following steps:
wherein, P0eTotal pressure measured for the pressure measurement point of the pressure measurement rake, AeThe specific heat ratio is usually 1.4; is the flow area of the flow tube at which the pressure measurement point is located, T0eTotal temperature q measured for pressure-measuring rakeeIs the outlet velocity pressure, qeThe calculation method comprises the following steps:
wherein M iseTotal pressure P measured by pressure measuring rake0eAnd static pressure PeConversion is carried out to obtain:
step three, calculating the ideal flow of the flow pipe where each pressure measuring point on the pressure measuring rake is positioned
The calculation method comprises the following steps:
wherein A isinFor capture area of nacelle air intake, P0For total pressure of incoming flow of the test section, T0The total temperature of the incoming flow of the test section;
step four, calculating the air inflow coefficient phi of the pressure measuring nacelle, wherein the air inflow coefficient phi of the nacelle is the actual flow
And the ideal flow rate
The ratio of (A) to (B):
φ＝∑me/min
the flow coefficient phi obtained in the step one and the pressure coefficient C of the pressure measuring nacelle obtained in the step fourpAnd i, obtaining the influence rule of the air intake and exhaust on the pressure distribution of the pressure measuring nacelle.
The invention at least comprises the following beneficial effects: the single turbofan engine nacelle surface pressure measurement test device with the turbine power simulation and the pressure measurement test method provided by the invention are used for obtaining surface pressure distribution test data of a turbofan engine nacelle model affected by air intake and exhaust when the turbofan engine nacelle model simulates flight conditions, providing input conditions for optimization of the nacelle and calculation of structural strength, and providing test basis for researching nacelle flow characteristics and overall performance of an airplane. Meanwhile, the pressure measuring pipeline is arranged in the nacelle base and the nacelle bracket of the front end supporting mechanism, so that the wiring arrangement is more reasonable.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Description of the drawings:
FIG. 1 is a schematic structural view of a single turbofan engine nacelle surface pressure measurement test device with turbine power simulation provided by the present invention;
FIG. 2 is a schematic view of an installation structure of a single turbofan engine nacelle surface pressure measurement test device with turbine power simulation provided by the present invention;
FIG. 3 is a schematic sectional view of a pressure measuring nacelle measuring pressure along the airflow direction;
FIG. 4 is a schematic cross-sectional view of a nacelle stand.
The specific implementation mode is as follows:
the present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
It is to be understood that in the description of the present invention, the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are used only for convenience in describing the present invention and for simplification of the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, unless otherwise specifically stated or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are used broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection via an intermediate medium, or a communication between two elements, and those skilled in the art will understand the specific meaning of the terms in the present invention specifically.
Further, in the present invention, unless otherwise explicitly specified or limited, a first feature "on" or "under" a second feature may be directly contacted with the first and second features, or indirectly contacted with the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
As shown in fig. 1-4: the invention relates to a single turbofan engine nacelle surface pressure measuring test device with turbine power simulation, which comprises:
the front end supporting mechanism is provided with a pressure measuring nacelle 4, and a plurality of pressure measuring holes 41 are distributed on the air inlet and the outer surface of the pressure measuring nacelle 4 along the radial direction of the pressure measuring nacelle; pressure measuring pipelines are arranged in the front end supporting mechanism, one end of each pressure measuring pipeline 21 is located at a pressure measuring hole 41 and at the bottom of the pressure measuring nacelle 4, and the other end of each pressure measuring pipeline is connected with a pressure sensor;
a propeller hub 3 is arranged in the pressure measuring nacelle 4, and a fan blade disc 5 is arranged on the propeller hub 3; one end of the transmission shaft 10 is fixedly connected with the propeller hub 3, the other end of the transmission shaft is provided with a turbine 12, a support rod 9 and a turbine casing 11 are arranged outside the transmission shaft 10, the turbine 12 is positioned in the turbine casing 11, and the support rod 9 is fixedly connected with the turbine casing 11; the turbine casing 11 is arranged on the rear end supporting mechanism;
a pressure measuring rake 7 and an outer culvert guide vane 6 are fixedly arranged on the supporting rod 9, the pressure measuring rake 7 is positioned in the pressure measuring nacelle 4 close to the outlet, and a gap is arranged between the pressure measuring rake 7 and the pressure measuring nacelle 4; the culvert guide vane 6 is arranged at the end part of the supporting rod 9, the culvert guide vane 6 is positioned between the fan blade disc 5 and the pressure measuring rake 7, and a gap is arranged between the culvert guide vane 6 and the pressure measuring nacelle 4.
Pressure measurement principle: the whole pressure measurement test device is placed in a wind tunnel, a turbine 12 is driven to rotate through high-pressure gas in the wind tunnel, and then a transmission shaft 10 and a fan blade disc 5 are driven to rotate through the turbine 12, so that the pressure measurement test device is used for obtaining the pressure distribution characteristics of the air inlet and the outer surface of a pressure measurement nacelle 4 under the influence of air inlet and exhaust in a simulated flight state; changing the total pressure, Mach number, fan pressure ratio and 4-angle of attack conditions of the pressure measuring nacelle, collecting the signals of the pressure measuring hole and the pressure measuring rake of the nacelle, and obtaining the flow coefficient phi and the pressure coefficient C of the pressure measuring nacelle through data processingpiAnd further obtain the rule of influence of the air intake and exhaust on the pressure distribution of the pressure measuring nacelle 4. The front end supporting mechanism and the rear end supporting mechanism are used for providing support for the whole testing device; the pressure measuring rake 7 is used for measuring the total pressure, the total temperature and the static pressure of the pressure measuring nacelle 4; the bypass guide vanes 6 are used for guiding airflow and adjusting the flow velocity of the gas.
In the above technical solution, the structure of the front end supporting mechanism includes:
the nacelle base 1 is provided with a nacelle bracket 2 above, the nacelle bracket 2 is mounted on the wall surface of the wind tunnel through bolts, and the nacelle base 1 is fixed on a wind tunnel wall plate 15 through bolts; the pressure measuring nacelle 4 is arranged on the nacelle bracket 2;
the structure of the rear end supporting mechanism comprises:
a support joint 13, said turbine casing 11 being arranged on the support joint 13;
and the wind tunnel attack angle mechanism 14 is fixed below the support joint 13 through pins and bolts.
In the above technical scheme, the culvert fairing 8 is installed on the supporting rod 9 through a screw, the culvert fairing 8 covers the connection part of the pressure measuring rake 7 and the supporting rod 9, and the culvert fairing 8 with the smooth shape has the functions of exhausting and rectifying at the exhaust port of the pressure measuring nacelle 4.
In the above technical solution, a wedge-shaped angle transformer 16 is arranged below the nacelle base 1, and the test attack angle of the pressure measuring nacelle 4 can be changed by replacing different wedge-shaped angle transformers.
In the technical scheme, the pressure measuring nacelle 4 is radially provided with 6-8 pressure measuring holes 41 with cross sections.
In the above solution, the nacelle stand 2 is streamlined in cross section, and this arrangement is used to reduce aerodynamic interference with the nacelle 4.
In the technical scheme, the pressure measuring pipeline 21 is arranged in the nacelle bracket 2 and the nacelle base 1, the wiring arrangement of the pressure measuring pipeline 21 is more reasonable, and the interference on the test result can be effectively reduced.
The utility model provides a take turbine power simulation's individual turbofan engine nacelle surface pressure measurement test device, the pressure measurement test method is: the whole pressure measurement test device is placed in a wind tunnel, a turbine is driven to rotate through high-pressure gas in the wind tunnel, and then a transmission shaft and a fan blade disc are driven to rotate through the turbine so as to obtain pressure distribution characteristics of an air inlet and the outer surface of a pressure measurement nacelle under the influence of air inlet and exhaust in a simulated flight state; changing the total pressure, Mach number, fan pressure ratio and angle of attack of the pressure measuring nacelle, collecting the signals of the pressure measuring hole and pressure measuring rake of the nacelle, and obtaining the flow coefficient phi and the pressure coefficient C of the pressure measuring nacelle through data processingpiAnd further acquiring the rule of influence of the air intake and exhaust on the pressure distribution of the pressure measuring nacelle, wherein the data processing step comprises the following steps of:
step one, measuring pressure coefficient C of air inlet and surface of nacellepiObtained by the following formula:
wherein, PiIs the static pressure value of the ith point on the surface of the pressure measuring nacelle, P∞For static pressure of incoming flow, q∞For the pressure of the incoming flow, q∞The calculation method comprises the following steps:
wherein M is∞For a given incoming flow Mach number, gamma is the specific heat ratio of the incoming flow medium, air mediumIs/are as follows
Step two, calculating the actual flow of the flow pipe where each pressure measuring point on the pressure measuring rake is located
The calculation method comprises the following steps:
wherein, P0eTotal pressure measured for the pressure measurement point of the pressure measurement rake, AeThe specific heat ratio is usually 1.4; is the flow area of the flow tube at which the pressure measurement point is located, T0eTotal temperature q measured for pressure-measuring rakeeIs the outlet velocity pressure, qeThe calculation method comprises the following steps:
wherein M iseTotal pressure P measured by pressure measuring rake0eAnd static pressure PeConversion is carried out to obtain:
step three, calculating the ideal flow of the flow pipe where each pressure measuring point on the pressure measuring rake is positioned
The calculation method comprises the following steps:
wherein A isinFor capture area of nacelle air intake, P0For total pressure of incoming flow of the test section, T0The total temperature of the incoming flow of the test section;
step four, calculating the air inflow coefficient phi of the pressure measuring nacelle, wherein the air inflow coefficient phi of the nacelle is the actual flow
And the ideal flow rate
The ratio of (A) to (B):
φ＝∑me/min
the flow coefficient phi obtained in the step one and the pressure coefficient C of the pressure measuring nacelle obtained in the step fourpAnd i, obtaining the influence rule of the air intake and exhaust on the pressure distribution of the pressure measuring nacelle.
The number of apparatuses and the scale of the process described herein are intended to simplify the description of the present invention. Applications, modifications and variations of the present invention will be apparent to those skilled in the art.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (8)
1. The utility model provides a take individual turbofan engine nacelle surface pressure measurement test device of turbine power simulation which characterized in that includes:
the front end supporting mechanism is provided with a pressure measuring nacelle, and a plurality of pressure measuring holes are distributed on the air inlet and the outer surface of the pressure measuring nacelle along the radial direction of the pressure measuring nacelle; a pressure measuring pipeline is arranged in the front end supporting mechanism, one end of the pressure measuring pipeline is positioned at a pressure measuring hole and at the bottom of the pressure measuring nacelle, and the other end of the pressure measuring pipeline is connected with a pressure sensor;
a hub is installed in the pressure measuring short cabin, and a fan blade disc is installed on the hub; one end of the transmission shaft is fixedly connected with the propeller hub, the other end of the transmission shaft is provided with a turbine, a support rod and a turbine case are arranged outside the transmission shaft, the turbine is positioned in the turbine case, and the support rod is fixedly connected with the turbine case; the turbine casing is arranged on the rear end supporting mechanism;
the pressure measuring rake is positioned in the pressure measuring short cabin and close to the outlet, and a gap is formed between the pressure measuring rake and the pressure measuring short cabin; the culvert guide vane is arranged at the end part of the supporting rod and is positioned between the fan blade disc and the pressure measuring rake, and a gap is arranged between the culvert guide vane and the pressure measuring nacelle.
2. The apparatus for testing nacelle surface pressure of an individual turbofan engine with turbine dynamic simulation according to claim 1 wherein the structure of the front end support mechanism comprises:
the nacelle base is provided with a nacelle bracket above and is arranged on the wall surface of the wind tunnel through bolts, and the nacelle base is fixed on a wind tunnel wall plate through bolts; the pressure measuring nacelle is arranged on the nacelle bracket;
the structure of the rear end supporting mechanism comprises:
a support joint on which the turbine case is disposed;
and the wind tunnel attack angle mechanism is fixed below the supporting joint through a pin and a bolt.
3. The apparatus for testing the pressure of the nacelle surface of an individual turbofan engine with turbine dynamic simulation according to claim 1, wherein a bypass fairing is installed on the strut by a screw, and covers a connection portion of the pressure measuring rake and the strut.
4. The apparatus for testing the nacelle surface pressure of an individual turbofan engine with turbine dynamic simulation according to claim 2 wherein a wedge-shaped angle transformer is provided below the nacelle base.
5. The single turbofan engine nacelle surface pressure testing apparatus with turbine dynamic simulation according to claim 1, wherein the pressure measuring nacelle is provided with 6-8 pressure measuring holes with cross sections in a radial direction.
6. The apparatus for testing the nacelle surface pressure of an individual turbofan engine with turbine dynamic simulation according to claim 2 wherein the nacelle stand is streamlined in cross section.
7. The apparatus for testing the nacelle surface pressure of an individual turbofan engine with turbine dynamic simulation according to claim 2 wherein the pressure lines are provided in the nacelle bracket and the nacelle base.
8. The device for testing the pressure of the surface of the nacelle of the single turbofan engine with the turbine dynamic simulation according to any one of claims 1 to 7, wherein the pressure testing method comprises the following steps: the whole pressure measurement test device is placed in a wind tunnel, a turbine is driven to rotate through high-pressure gas in the wind tunnel, and then a transmission shaft and a fan blade disc are driven to rotate through the turbine so as to obtain pressure distribution characteristics of an air inlet and the outer surface of a pressure measurement nacelle under the influence of air inlet and exhaust in a simulated flight state; changing the total pressure, Mach number, fan pressure ratio and angle of attack of the pressure measuring nacelle, collecting the signals of the pressure measuring hole and pressure measuring rake of the nacelle, and obtaining the flow coefficient phi and the pressure coefficient C of the pressure measuring nacelle through data processingpiAnd further acquiring the rule of influence of the air intake and exhaust on the pressure distribution of the pressure measuring nacelle, wherein the data processing step comprises the following steps of:
step one, measuring pressure coefficient C of air inlet and surface of nacellepiObtained by the following formula:
wherein, PiIs the static pressure value of the ith point on the surface of the pressure measuring nacelle, P∞For static pressure of incoming flow, q∞For the pressure of the incoming flow, q∞The calculation method comprises the following steps:
wherein M is∞For a given incoming stream Mach number, gammaFor specific heat ratio of incoming flow medium, of air medium
Step two, calculating the actual flow of the flow pipe where each pressure measuring point on the pressure measuring rake is located
The calculation method comprises the following steps:
wherein, P0eTotal pressure measured for the pressure measurement point of the pressure measurement rake, AeThe specific heat ratio is usually 1.4; is the flow area of the flow tube at which the pressure measurement point is located, T0eTotal temperature q measured for pressure-measuring rakeeIs the outlet velocity pressure, qeThe calculation method comprises the following steps:
wherein M iseTotal pressure P measured by pressure measuring rake0eAnd static pressure PeConversion is carried out to obtain:
step three, calculating the ideal flow of the flow pipe where each pressure measuring point on the pressure measuring rake is positioned
The calculation method comprises the following steps:
wherein A isinFor capture area of nacelle air intake, P0For total pressure of incoming flow of the test section, T0The total temperature of the incoming flow of the test section;
step four, countingCalculating the air inflow coefficient phi of the pressure measuring nacelle, wherein the air inflow coefficient phi of the nacelle is the actual flow
And the ideal flow rate
The ratio of (A) to (B):
φ＝∑me/min
the flow coefficient phi obtained in the step one and the pressure coefficient C of the pressure measuring nacelle obtained in the step fourpAnd i, obtaining the influence rule of the air intake and exhaust on the pressure distribution of the pressure measuring nacelle.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112985822A (en) * | 2021-04-20 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN113252280A (en) * | 2021-04-20 | 2021-08-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
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