CN112393873A - Attack angle matching method - Google Patents
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- CN112393873A CN112393873A CN202110029454.1A CN202110029454A CN112393873A CN 112393873 A CN112393873 A CN 112393873A CN 202110029454 A CN202110029454 A CN 202110029454A CN 112393873 A CN112393873 A CN 112393873A
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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
- G01M9/02—Wind tunnels
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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
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention is suitable for the technical field of wind tunnel tests, and provides an attack angle matching method, which comprises the following steps: will be provided withS=S ri Substituting into the change curve of the location of the stagnation point along with the angle of attackS=Aα+BIn the middle, the nominal angle of attack is obtainedα ri Corresponding calculated angle of attackα ci (ii) a Rotating the wind tunnel rotor to place the test model at the calculated angle of attackα ci And measuring and calculating the angle of attackα ci Lower test stagnation positionS ci (ii) a Judgment-S ci ‑S ri I andΔSand determining a true trial angle of attack of the trial model, wherein,ΔSis the minimum allowable error. Compared with the prior art, the method can improve the accuracy and efficiency of the matching of the attack angle.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to an attack angle matching method.
Background
When the aircraft flies in a high-altitude cloud layer, the wind-facing component impacts supercooled water drops in the cloud layer to cause the problem of icing, so that the flight performance of the aircraft is obviously reduced, the components are damaged, and even the flight accidents of machine damage and people death are caused. The icing wind tunnel is used as an important ground simulation facility and widely applied to airplane icing research.
The icing degree of an airplane is not only related to meteorological environment, but also related to the attack angle during flight. Therefore, the research on the icing condition of the airplane under different attack angles is also significant.
However, due to the limitation of the size of the icing wind tunnel, generally only icing test research on an aircraft component (such as a wing) model can be performed, so that during icing test, only nominal attack angle conditions of the whole aircraft can be given, and the actual flight attack angle of the aircraft component (such as the wing) model cannot be directly determined; on the other hand, when an icing test is performed, the model of the aircraft component (such as a wing) is usually installed on the turntable, and due to the influence of wind tunnel wall interference and airflow deviation, a certain deviation also exists between the actual test attack angle of the model of the aircraft component (such as the wing) and the actual flight attack angle of the model of the aircraft component during the test.
Therefore, before the icing test is performed, the attack angle needs to be matched in advance, and the test attack angle of the aircraft component model is adjusted to the real test attack angle, so that the real test attack angle of the aircraft component model is as close as possible to the actual flight attack angle of the aircraft component model.
In the prior art, in the process of adjusting the test attack angle of the aircraft component model to the real test attack angle, the adjustment is completely carried out in a manual mode, and the specific adjustment method does not have related prior art, and particularly, the method usually needs to match a plurality of nominal attack angles of the whole aircraft, so that the aircraft component model needs to be repeatedly rotated for many times, and therefore, the attack angle matching method in the prior art has the defects of low efficiency and low precision.
Disclosure of Invention
The invention aims to provide an attack angle matching method, and aims to solve the technical problems of low efficiency and low precision of the attack angle matching method in the prior art.
The invention provides an attack angle matching method, which comprises the following steps:
step S10: will be provided withS=S ri Substituting into the change curve of the location of the stagnation point along with the angle of attackS=Aα+BIn the middle, the nominal angle of attack is obtainedα ri Corresponding calculated angle of attackα ci Wherein, in the step (A),iis a serial number of a nominal angle of attack,S ri is nominal angle of attackα ri The position of the lower reference stagnation point is determined,Ais a slope of the light beam in the direction of the light beam,Bis the intercept of the position of the stagnation point,Sis a dependent variable of the location of the stagnation point,αangle of attack independent variable;
step S20: rotating the wind tunnel rotor to place the test model at the calculated angle of attackα ci And measuring and calculating the angle of attackα ci Lower test stagnation positionS ci ；
Step S30: judgment-S ci -S ri I andΔSand determining a true trial angle of attack of the trial model, wherein,ΔSis the minimum allowable error.
Optionally, the step S30 includes the following steps:
step S31: if notS ci -S ri |<ΔSThen the angle of attack will be calculatedα ci As nominal angle of attackα ri True test angle of attack for the test model below.
Optionally, the step S30 includes the following steps:
step S32: if notS ci -S ri |>ΔSRotational windHole turnplate to make test model at adjusting attack angleα ci -sign(S ci - S ri )fτAnd measuring the angle of attackα ci -sign(S ci -S ri )fτLower test stagnation positionS cif Wherein, in the step (A),τin order to achieve the resolution of the wind tunnel rotor,fis the fine tuning times of the wind tunnel rotary table,ftraverse from 1 until &S cif -S ri |<ΔS，signAs a function of the sign, willα ci -sign(S ci -S ri )fτAsα ri True test angle of attack for the test model below.
Optionally, the curve of the change of the stagnation point position with the attack angle is obtained by the following steps:
step S11: rotating the wind tunnel turntable to place the test model at the test angle of attackα k And measuring the angle of attackα k Surface pressure distribution coefficient ofc kj Wherein, in the step (A),ka serial number representing the angle of attack of the test,jrepresenting the serial number of a pressure measuring hole on the test model;
step S12: maximum surface pressure distribution coefficientc kj-max The position of the corresponding pressure measuring hole is used as a test attack angleα k Lower test stagnation positionS kj Wherein, in the step (A),c kj-max =max(c kj )；
step S13: will test the angle of attackα k As abscissa, test angle of attackα k Corresponding test stationing positionS kj And fitting a change curve of the position of the stationary point along with the attack angle as a vertical coordinate.
Optionally, in step S11, the attack angle is testedα k Is defined asα rmin -∆α t <α k <α rmax +∆α t Wherein, in the step (A),α rmin =min(α ri )，α rmax =max(α ri )，∆α t the range of values of the left and right angles of attack.
Compared with the prior art, the invention has the technical effects that:
1. according to the method, the calculated attack angle can be calculated through the change curve of the stagnation point position along with the attack angle, and the calculated attack angle is positioned near the real test attack angle (namely the expected attack angle which is finally expected to be reached), so that a test model can be quickly positioned near the real test attack angle by rotating the wind tunnel turntable;
2. in the invention, after the wind tunnel turntable is finely adjusted each time, the calculation can be carried out by judging the calculation ofS cif -S ri I andΔSto determine whether to continue fine tuning the wind tunnel rotor until calculatingS cif -S ri |<ΔSTherefore, high-precision matching of the attack angle can be achieved, and the test model is already in the state of calculating the attack angle before the wind tunnel turnplate is finely adjusted, so that the times of finely adjusting the wind tunnel turnplate are not large usually, and the efficiency of matching the attack angle is high.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic flow chart of an attack angle matching method according to the present invention.
Detailed Description
Aspects of the present invention will be described more fully hereinafter with reference to the accompanying drawings. This invention may, however, be embodied in many different forms and should not be construed as limited to any specific structure or function presented throughout this disclosure. Rather, these aspects are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Based on the teachings herein one skilled in the art should appreciate that the scope of the present invention is intended to encompass any aspect disclosed herein, whether alone or in combination with any other aspect of the invention to accomplish any aspect disclosed herein. For example, it may be implemented using any number of the apparatus or performing methods set forth herein. In addition, the scope of the present invention is intended to cover apparatuses or methods implemented with other structure, functionality, or structure and functionality in addition to the various aspects of the invention set forth herein. It is to be understood that any aspect disclosed herein may be embodied by one or more elements of a claim.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.
As shown in fig. 1, an embodiment of the present invention provides an attack angle matching method, which includes the following steps:
step S10: will be provided withS=S ri Substituting into the change curve of the location of the stagnation point along with the angle of attackS=Aα+BIn the middle, the nominal angle of attack is obtainedα ri Corresponding calculated angle of attackα ci Wherein, in the step (A),iis a serial number of a nominal angle of attack,S ri is nominal angle of attackα ri The position of the lower reference stagnation point is determined,Ais a slope of the light beam in the direction of the light beam,Bis the intercept of the position of the stagnation point,Sis a dependent variable of the location of the stagnation point,αangle of attack independent variable;
nominal angle of attackα ri Given as one of the test conditions, and given the nominal angle of attackα ri While at the same time, the nominal attack angle is also givenα ri Corresponding surface pressure distribution coefficient according to nominal angle of attackα ri The surface pressure distribution coefficient under the condition can obtain the nominal attack angleα ri Lower reference stagnation positionS ri ；
In particular, the nominal angle of attackα ri The position of the pressure measuring hole corresponding to the maximum surface pressure distribution coefficient under the condition is used as the reference stagnation point positionS ri ；
In addition, a plurality of pressure measuring holes are distributed on the surface of the test model, each pressure measuring hole corresponds to a surface pressure distribution coefficient under a certain test condition, and the position of each pressure measuring hole can be expressed by adoptingC/LIt is shown that, among others,Cthe length between the pressure cell and the front edge point position profile curve,Lthe length between the pressure measuring hole and the chord length of the wing section is taken as the leading edge point, the coordinate of the pressure measuring hole positioned on the lower wing surface is positive, and the coordinate of the pressure measuring hole positioned on the upper wing surface is negative;
step S20: rotating the wind tunnel rotor to place the test model at the calculated angle of attackα ci And measuring and calculating the angle of attackα ci Lower test stagnation positionS ci ；
In the icing wind tunnel test, the test model is arranged on a wind tunnel turntable, and the test model can be positioned at different attack angles by rotating the wind tunnel turntable;
step S30: judgment-S ci -S ri I andΔSand determining a true trial angle of attack of the trial model, wherein,ΔSis the minimum allowable error.
In the embodiment of the invention, the attack angle can be calculated and calculated through the change curve of the stagnation point position along with the attack angleα ci And calculating the angle of attackα ci The wind tunnel rotary table is positioned near a real test attack angle (namely, an expected attack angle which is finally desired to be reached), so that a test model can be quickly positioned near the real test attack angle by rotating the wind tunnel rotary table, and in a processing mode in the prior art, no corresponding data reference exists when the wind tunnel rotary table is rotated, and the adjustment is completely carried out step by experience, so that the efficiency is greatly improved in the embodiment of the invention compared with the prior art;
on the other hand, in the embodiment of the invention, the determination of the amount of Y is performedS ci -S ri I andΔSthe relationship (c) is used for determining the true test attack angle of the test model, so that compared with the prior art, the accuracy is greatly improved by the embodiment of the invention.
Further, the step S30 includes the following steps:
step S31: if notS ci -S ri |<ΔSThen the angle of attack will be calculatedα ci As nominal angle of attackα ri True test angle of attack for the test model below.
Therefore, the matching precision of the embodiment of the invention can be ensured;
further, the step S30 includes the following steps:
step S32: if notS ci -S ri |>ΔSRotating the wind tunnel turntable to make the test model at the adjusted attack angleα ci -sign(S ci - S ri )fτAnd measuring the angle of attackα ci -sign(S ci -S ri )fτLower test stagnation positionS cif Wherein, in the step (A),τin order to achieve the resolution of the wind tunnel rotor,fis the fine tuning times of the wind tunnel rotary table,ftraverse from 1 until &S cif -S ri |<ΔS，signAs a function of the sign, willα ci -sign(S ci -S ri )fτAsα ri True test angle of attack for the test model below.
In particular, when(S ci -S ri )<0When the temperature of the water is higher than the set temperature,sign(S ci -S ri )=-1; when in use(S ci -S ri )>0When the temperature of the water is higher than the set temperature,sign(S ci -S ri )=1；
will adjust the angle of attackα ci -sign(S ci -S ri )fτThe position of the pressure measuring hole corresponding to the maximum surface pressure distribution coefficient under the condition is used as the position of the test stagnation pointS cif ；
fTraversing from 1 means that first one willfSubstitution of =1α ci -sign(S ci -S ri )fτIn other words, the angle of attack is adjusted toα ci -sign(S ci -S ri )τIf it is already satisfiedS cif -S ri |<ΔSThen, there is no need to continue to rotate the wind tunnel rotor, i.e. there is no need to continue to rotate the wind tunnel rotorfReplacement of =2α ci -sign(S ci -S ri )fτIn (1).
In the embodiment of the invention, the high-precision attack angle can be efficiently realized by finely adjusting the wind tunnel turntableDegree matching, specifically, after the wind tunnel turnplate is finely adjusted each time, the calculation can be carried out by judging the luminanceS cif -S ri I andΔSto determine whether to continue fine tuning the wind tunnel rotor until calculatingS cif -S ri |<ΔSHigh-precision matching of the angle of attack can be achieved, and the test model is already in the state of calculating the angle of attack before the wind tunnel turnplate is finely adjustedα ci Therefore, the number of times of fine tuning the wind tunnel rotary table is not large, and therefore, the efficiency of matching the attack angle is high.
Further, the change curve of the stagnation point position along with the attack angle is obtained by the following steps:
step S11: rotating the wind tunnel turntable to place the test model at the test angle of attackα k And measuring the angle of attackα k Surface pressure distribution coefficient ofc kj Wherein, in the step (A),ka serial number representing the angle of attack of the test,jrepresenting the serial number of a pressure measuring hole on the test model;
step S12: maximum surface pressure distribution coefficientc kj-max The position of the corresponding pressure measuring hole is used as a test attack angleα k Lower test stagnation positionS kj Wherein, in the step (A),c kj-max =max(c kj )；
step S13: will test the angle of attackα k As abscissa, test angle of attackα k Corresponding test stationing positionS kj And fitting a change curve of the position of the stationary point along with the attack angle as a vertical coordinate.
The calculated attack angle can be calculated through the change curve of the stagnation point position along with the attack angleα ci And accordingly, the wind tunnel rotary table can be quickly rotated to enable the test model to be positioned near the real test attack angle, and the prior art does not have related technology and is completely adjusted step by experience.
Further, in order to further improve the matching efficiency and the matching accuracy, the step SIn 11, the angle of attack will be testedα k Is defined asα rmin -∆α t <α k <α rmax +∆α t Wherein, in the step (A),α rmin =min(α ri )，α rmax =max(α ri )，∆α t the range of values of the left and right angles of attack.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (5)
1. An attack angle matching method is characterized by comprising the following steps:
step S10: will be provided withS=S ri Substituting into the change curve of the location of the stagnation point along with the angle of attackS=Aα+BIn the middle, the nominal angle of attack is obtainedα ri Corresponding calculated angle of attackα ci Wherein, in the step (A),iis a serial number of a nominal angle of attack,S ri is nominal angle of attackα ri The position of the lower reference stagnation point is determined,Ais a slope of the light beam in the direction of the light beam,Bis the intercept of the position of the stagnation point,Sis a dependent variable of the location of the stagnation point,αangle of attack independent variable;
step S20: rotating the wind tunnel rotor to place the test model at the calculated angle of attackα ci And measuring and calculating the angle of attackα ci Lower test stagnation positionS ci ；
Step S30: judgment-S ci -S ri I andΔSand determining a true trial angle of attack of the trial model, wherein,ΔSis the minimum allowable error.
2. The angle of attack matching method of claim 1, wherein the step S30 includes the steps of:
step S31: if notS ci -S ri |<ΔSThen the angle of attack will be calculatedα ci As nominal angle of attackα ri True test angle of attack for the test model below.
3. The angle of attack matching method according to claim 1 or 2, wherein the step S30 includes the steps of:
step S32: if notS ci -S ri |>ΔSRotating the wind tunnel turntable to make the test model at the adjusted attack angleα ci -sign(S ci - S ri )fτAnd measuring the angle of attackα ci -sign(S ci -S ri )fτLower test stagnation positionS cif Wherein, in the step (A),τin order to achieve the resolution of the wind tunnel rotor,fis the fine tuning times of the wind tunnel rotary table,ftraverse from 1 until &S cif -S ri |<ΔS，signAs a function of the sign, willα ci -sign(S ci -S ri )fτAsα ri True test angle of attack for the test model below.
4. A method of angle of attack matching as claimed in claim 3, wherein the curve of the dwell position versus angle of attack is obtained by:
step S11: rotating the wind tunnel turntable to place the test model at the test angle of attackα k And measuring the angle of attackα k Surface pressure distribution coefficient ofc kj Wherein, in the step (A),ka serial number representing the angle of attack of the test,jrepresenting the serial number of a pressure measuring hole on the test model;
step S12: maximum surface pressure distribution coefficientc kj-max The position of the corresponding pressure measuring hole is used as a test attack angleα k Lower test stagnation positionS kj Wherein, in the step (A),c kj-max =max(c kj )；
step S13: will test the angle of attackα k As abscissa, test angle of attackα k Corresponding test stationing positionS kj And fitting a change curve of the position of the stationary point along with the attack angle as a vertical coordinate.
5. The method of claim 4, wherein in step S11, the angle of attack is testedα k Is defined asα rmin -∆α t <α k <α rmax +∆α t Wherein, in the step (A),α rmin =min(α ri )，α rmax =max(α ri )，∆α t the range of values of the left and right angles of attack.
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