CN110207946A - Flow integrated model in wind tunnel scale reduction method inside and outside a kind of high speed - Google Patents
Flow integrated model in wind tunnel scale reduction method inside and outside a kind of high speed Download PDFInfo
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- CN110207946A CN110207946A CN201910557923.XA CN201910557923A CN110207946A CN 110207946 A CN110207946 A CN 110207946A CN 201910557923 A CN201910557923 A CN 201910557923A CN 110207946 A CN110207946 A CN 110207946A
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a kind of scale reduction methods of flow integrated model in wind tunnel inside and outside high speed, contracting ratio forms scale model to model in wind tunnel in proportion on the basis of full scale model, and the discharge coefficient φ of the scale model is not more than 5% with respect to the variable quantity of full scale model.Present invention ensure that the interior stream flowing of scale model simulation is consistent with flying condition, the precision of ground prediction aeroperformance is improved.
Description
Technical field
The invention belongs to high-speed aircraft technical fields, and in particular to a kind of interior outflow one suitable under high-speed condition
Change the scale reduction method of model in wind tunnel.
Background technique
High-speed flight technology is one of the research hotspot of 21 century aerospace field, but high-speed aircraft pushes away resistance surplus
It is small, inside and outside it is flow integrated cause performance prediction difficult, therefore flow integrated flight inside and outside Developing High-speed wind-tunnel technique, raising
The precision of prediction of device aeroperformance will be the critical issue that must be solved in high-speed aircraft development.
It is limited by domestic existing wind tunnel test facility size, is difficult that full-scale vehicle model is directly put into wind-tunnel
It is tested, test model will generally carry out a degree of ratio contracting ratio on the basis of full-scale vehicle.In wind-tunnel
In test, the test model after contracting ratio is generally possible to the outflow flowing of relatively accurately simulated flight device, but interior outflow coupling flies
Inner flow passage size of the row device contracting than after is generally all smaller, and the reasons such as wind tunnel noise lead to the attached face of inner flow passage under wind-tunnel state in addition
Thickness degree is partially thick (being equivalent to the true breathing area for reducing inner flow passage), causes above-mentioned equal proportion contracting than this geometric similarity standard
Then not fully it is applicable in.It is exactly that interior outflow is highly coupled using punching engine as the high-speed aircraft most typically feature of power, it is right
In this kind of aircraft, if also designing scale model with the outflow scale reduction method of existing maturation in wind tunnel test, may lead
Causing the interior stream of wind tunnel simulation to flow between the flowing of the interior stream of live flying state, there are bigger differences.Currently, studies in China list
Also internally the scale reduction method of stream flowing did not carried out further investigation for position, did not form practical interior stream flowing scale reduction method yet, this
The wind-tunnel technique of aspect needs to break through.
Summary of the invention
The present invention need to solve technical problem be to provide it is a kind of suitable for flow integrated wind tunnel test inside and outside under high-speed condition
The scale reduction method of model, it is ensured that the interior stream flowing of model in wind tunnel simulation is consistent as far as possible with flying condition, improves ground prediction
The precision of aeroperformance.
In order to solve the above technical problems, the invention proposes a kind of contracting ratios of flow integrated model in wind tunnel inside and outside high speed
Method, specific as follows:
Contracting ratio forms scale model to model in wind tunnel in proportion on the basis of full scale model, the scale model
Discharge coefficient φ is not more than 5% with respect to the variable quantity of full scale model, it may be assumed that
|φScale model-φFull scale model|≤5%.
Further, contracting ratio forms scale model to the model in wind tunnel in proportion on the basis of full scale model,
Include the following steps:
Step 1) calculates the discharge coefficient of full scale model and different contractings than scale model；
Step 2) calculates separately discharge coefficient of the different contractings than scale model on the basis of the discharge coefficient of full scale model
Variable quantity；
Step 3) is according to criterion: | φScale model-φFull scale model|≤5%, and current wind tunnel test equipment size, really
It is reduced than ratio, form the scale model of wind tunnel test.
Compared with prior art, the beneficial effects of the present invention are:
The scale reduction method of flow integrated model in wind tunnel inside and outside high-speed aircraft proposed by the present invention, it can be ensured that contracting ratio
The interior stream flowing of modeling is consistent with flying condition, and have passed through effective inspection of wind tunnel test, improves ground prediction gas
The precision of dynamic performance.
Detailed description of the invention
The present invention shares 3 width attached drawings.
Fig. 1 is each schematic cross-section of punching engine；
The discharge coefficient of Fig. 2 difference scale model and the relative variation curve of full scale model discharge coefficient；
Fig. 3 be in wind tunnel test stream flowing can the corresponding model engine inner flow passage of simulated flight condition along stroke pressure pair
Compare curve.
Wherein: 1 is free flow section, 2 be Fighter Inlet, 3 is venturi.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
Punching engine inner flow passage is the important component of interior outflow coupling aircraft, is directly related to engine inlets energy
No normal starting, combustion chamber can efficient operation, engine performance can meet design requirement.By wind tunnel test facility size
Limitation, be difficult that full-scale vehicle model is directly put into wind-tunnel and test, test model will generally fly full-scale
A degree of ratio contracting ratio is carried out on the basis of row device.In wind tunnel test, the test model after contracting ratio can be relatively more accurate
The outflow of simulation aircraft is flowed, but inner flow passage size of the interior outflow coupling aircraft contracting than after is generally all smaller, in addition
The reasons such as wind tunnel noise cause inner flow passage boundary layer thickness thickness partially under wind-tunnel state (to be equivalent to the true ventilation for reducing inner flow passage
Area), it can be seen that the equal proportion scale reduction method suitable for outer flow field simulation can not be completely suitable for interior outflow coupling aircraft,
It needs to propose model scale reduction method for inside and outside flow integrated aircraft, it is ensured that the interior stream of model in wind tunnel simulation flows and flies
Row condition is consistent as far as possible, improves the precision of ground prediction aeroperformance.[remarks: wind tunnel test methods are aerodynamic scopes
Common analysis method, for details, reference can be made to " wind tunnel test handbook " (the main work in the clean river of model, aircraft industry publishing house, in December, 2002
It publishes, ISBN 7-80134-985-7]
The affecting laws of aeroperformance are compared based on model contracting in body/propelling integrated aircraft ventilation dynamometer check,
Then scale reduction method of the scale model in wind tunnel test:
Contracting ratio forms scale model to model in wind tunnel in proportion on the basis of full scale model, the scale model
Discharge coefficient φ is not more than 5% with respect to the variable quantity of full scale model, it may be assumed that
|φScale model-φFull scale model|≤5%.
Each schematic cross-section of punching engine is as shown in Figure 1, include free flow section 1, Fighter Inlet 2, venturi 3, stream
Coefficient of discharge refers to that the mass flow for actually entering punching engine venturi 3 is caught with the theory being calculated by free flow section 1
The ratio of flow is obtained, is generally indicated with symbol φ, wherein the mass flow for actually entering punching engine venturi 3 can be by high-precision
Degree value calculating method is calculated that [remarks: numerical computation method is the common analysis method of aerodynamic scope, specifically may be used
Referring to " Fluid Mechanics Computation study course (first edition) ", (Zhang Deliang is write, Higher Education Publishing House, and in November, 2010 publishes, ISBN
978-704-029741-6)], theoretical capture flow is by remote front incoming flow density p0, speed of incoming flow v0It is captured with Fighter Inlet 2
Area three's product obtains.
In scale model wind tunnel test, the condition of following formula expression need to be met, just can ensure that scale model simulation
Interior stream flowing is consistent with flying condition.
|φScale model-φFull scale model|≤5%.
For aircraft flow integrated inside and outside certain, specific embodiments of the present invention are provided.First by high-precision
Degree value calculating method calculates separately to obtain the discharge coefficient of full scale model and different contractings than scale model；Secondly with full ruler
On the basis of the discharge coefficient of very little model, discharge coefficient variable quantity (as shown in Figure 2) of the different contractings than scale model is calculated separately；Most
Afterwards with criterion proposed by the present invention: | φScale model-φFull scale model|≤5%, it is seen that it is directed to the inside and outside flow integrated aircraft,
It can ensure that the interior stream flowing of scale model simulation is consistent with flying condition than 1:2,1:4 and 1:7 model using contracting, and use contracting
Than 1:15 model cannot be guaranteed scale model simulation interior stream flowing it is consistent with flying condition, for it is available contract than ratio 1:2,
1:4 and 1:7, it is contemplated that the limitation of current wind tunnel test equipment size, it is proposed that wind tunnel test is carried out than 1:7 model using contracting.
It is verified by wind tunnel test, the contracting ratio of flow integrated model in wind tunnel inside and outside high-speed aircraft proposed by the present invention
Method, it can be ensured that stream flowing is consistent with flying condition in scale model, has reached desired effect.The energy of flow is flowed in wind tunnel test
The corresponding model engine inner flow passage of no simulated flight condition is as shown in Figure 3 along stroke pressure correlation curve.
Unspecified part of the present invention is known to the skilled person technology.
Claims (2)
1. the scale reduction method of flow integrated model in wind tunnel inside and outside a kind of high speed, it is characterised in that:
Contracting ratio forms scale model to model in wind tunnel in proportion on the basis of full scale model,
The discharge coefficient φ of the scale model is not more than 5% with respect to the variable quantity of full scale model, it may be assumed that
|φScale model-φFull scale model|≤5%.
2. the scale reduction method of flow integrated model in wind tunnel, feature exist inside and outside a kind of high speed according to claim 1
In: contracting ratio forms scale model to the model in wind tunnel in proportion on the basis of full scale model, includes the following steps:
Step 1) calculates the discharge coefficient of full scale model and different contractings than scale model；
On the basis of the discharge coefficient φ of full scale model, the discharge coefficient for calculating separately different contractings than scale model becomes step 2)
Change amount；
Step 3) is according to criterion: | φScale model-φFull scale model|≤5%, and current wind tunnel test equipment size, determine contracting
Than ratio, the scale model of wind tunnel test is formed.
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| CN117740307A (en) * | 2024-02-18 | 2024-03-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for predicting performance of full-size rotor wing |
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Application publication date: 20190906 |