CN115615655A - Continuous transonic wind tunnel test data interference correction method - Google Patents
Continuous transonic wind tunnel test data interference correction method Download PDFInfo
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Abstract
The application discloses a continuous transonic wind tunnel test data interference correction method, and belongs to the field of wind tunnel test data processing. The method solves the problems that the existing wind tunnel test data processing method is time-consuming and labor-consuming, and the result credibility is low. The technical points are as follows: simulating the flow interference of the wind tunnel wall to a flow field near the airplane model by using the wall pressure information; carrying out CFD simulation calculation on the test original model and the combined configuration of various supports to obtain the support interference amount of the model; modeling the actual measurement test model, and obtaining aerodynamic force with or without elastic deformation by CFD simulation calculation to obtain elastic deformation influence quantity; carrying out variable Reynolds number CFD simulation calculation on the test model to obtain a Reynolds number influence correction quantity; and superposing the correction quantities of the hole wall interference, the support interference, the elastic deformation influence and the Reynolds number influence to obtain the correction quantity from the scaled airplane model to the real flight model. The method and the device organically combine various interference quantities to form a complete correction system, and avoid repeated correction and insufficient correction.
Description
Technical Field
The application relates to a wind tunnel test data interference correction method, in particular to a continuous transonic wind tunnel test data interference correction method, and belongs to the field of wind tunnel test data processing.
Background
Aerodynamic force received by an aircraft during flying is an object of important research in aircraft design, and wind tunnel test is one of the most main means for researching the aerodynamic characteristics received by the aircraft. The aircraft is generally scaled to form a scaled model, the scaled model is supported in a wind tunnel, controllable artificial airflow flows on the surface of the scaled model in the wind tunnel, and aerodynamic force exerted on the model by air turbulence is measured through a balance.
In the wind tunnel test, because the size of the model is inconsistent with that of a real aircraft, airflow in the wind tunnel is inconsistent with turbulence of the real aircraft, the model is influenced by interference of a support, elastic deformation of the model is inconsistent with that of the real model or an ideal situation of airplane design, and the like, original data of wind tunnel test data can be provided for an airplane design data user through various corrections.
In the prior art, correction methods such as elastic angle correction of a balance and a support rod, model self-weight influence correction, two-center misalignment correction, bottom resistance correction, axial static pressure gradient correction, airflow deflection angle correction and the like are mature, and usually can be directly processed in a wind tunnel test data acquisition processing program, however, hole wall interference, support interference, elastic deformation influence, reynolds number influence and the like need to be processed through a special processing method, when a calculation technology is not developed, the processing method needs to be obtained through a test method, but the processing is time-consuming and labor-consuming, new interference factors are introduced while the interference influence quantity is corrected, and the result reliability is high.
Disclosure of Invention
In view of this, the application provides a continuous transonic wind tunnel test data interference correction method to solve the problems that the existing wind tunnel test data processing method is time-consuming and labor-consuming, and the result reliability is low.
The technical scheme of the application is realized as follows:
a continuous transonic wind tunnel test data interference correction method comprises the following steps:
s1: acquiring wall pressure information of a wind tunnel wall from a wind tunnel test, and simulating flow interference of the wind tunnel wall on a flow field near the airplane model by using the wall pressure information in numerical calculation;
s2: respectively carrying out CFD simulation calculation on the test original model and the combined configuration of various supports so as to obtain the support interference amount of the model;
s3: modeling the actual measurement test model, and obtaining aerodynamic force with or without elastic deformation by CFD simulation calculation so as to obtain elastic deformation influence quantity;
s4: carrying out variable Reynolds number CFD simulation calculation on the test model to obtain a Reynolds number influence correction quantity;
s5: and finally, according to the requirements, the correction quantities of the hole wall interference, the support interference, the elastic deformation influence and the Reynolds number influence are superposed to obtain the correction quantity from the scaled airplane model to the real flight model.
Preferably, the specific processing method of step S1 is as follows:
s11: under the test working condition given by the test outline, carrying out an air wind tunnel test, and measuring axial static pressure by using a shaft probe in the test process; respectively arranging 3-5 wall pressure pipes on an upper wall plate and a lower wall plate of the wind tunnel test section to measure the wall pressure of the air permeable wall under different working conditions; obtaining axial static pressure distribution and gradient, rotating center pressure of an attack angle mechanism and chamber standing pressure;
s12: calculating the Mach number at the rotating center according to the pressure of the rotating center of the shaft probe displacement attack angle mechanism and the total pressure of the incoming flowAnd obtainWith nominal mach number of residenceThe relationship betweenCalculating the floating resistance correction of the air wind tunnel by axial static pressure distribution and gradient of the shaft probe,is the difference between the Mach number at the center of rotation and the nominal Mach number of the parking cell;
s13: to be provided withCarrying out wind tunnel test of test model for Mach number of test section controlled by wind tunnel, and measuring by rod balanceThe lift coefficient CL (or normal force coefficient CN of the body axis system model), the drag coefficient CD (or axial force coefficient CA of the body axis system model) and the pitching moment coefficient CM of the model are measured, and the static pressures of the upper and lower breathable wall plates of the test section are measured at the same time;
s14: the static pressure of the air-permeable wall of the model test is differed from the static pressure of the air-permeable wall of the air tunnel to obtain wall pressure information of the air-permeable wall so as to eliminate the influence of irregular processing of a pressure measuring hole and the like, and the wall pressure is interpolated to the whole upper wall surface and the whole lower wall surface by a cubic spline fairing method;
s15: introducing wall pressure information of the air permeable wall into the air permeable wall by using a velocity potential function, and calculating the Mach number of the air permeable wall wind tunnel test section by using a double-parameter wall pressure information method integral methodAmount of influence of angle of attackAnd wind tunnel axis pressure distribution;
S16: according toCalculating the floating resistance generated under the constraint of the model and the support on the hole wall;
s17: influence quantity of CL and CD according to attack angleAnd (5) carrying out projection calculation again, and replacing the static pressure reference quantity and the quick pressure reference quantity to obtain the hole wall interference correction quantity.
In step S12, the floating resistance correction amount of the air tunnelThe calculation formula of (a) is as follows:
in the formula (1), V is the volume of the test model, S is the reference area of the test model, and L is the reference length of the test model.
in the formula (2), the first and second groups,as a function of the cross-sectional area distribution along the axial model,for the x-direction standing position of the tail support cavity,is the cross section area of the cavity,is the axial coordinate of the model machine head vertex,is the axial coordinate of the model machine tail end point,as a function of the wind tunnel axis pressure distribution.
In step S17, the calculation procedure of the hole wall disturbance correction amount is as follows:
in the formula (3), the first and second groups,is the ratio of the enthalpy of the incoming flow to the internal energy,1.4, p is the static pressure,for the reference amount of the pressure of the incoming flow rate,in order to correct the incidence angle,is the attack angle of the model after the air flow deflection angle correction,is an angle of attack;
in the formula (4), FA is the axial aerodynamic force of the measured model of the balance, and FN is the normal aerodynamic force of the model;the model resistance coefficient after the correction of the hole wall interference,the corrected model lift coefficient is obtained;
in the formula (5), the first and second groups of the chemical reaction materials are selected from the group consisting of,for the interference correction of the resistance coefficient of the hole wall interference model,And (4) correcting interference of the lift coefficient of the hole wall interference model.
Preferably, step S2 specifically comprises the following steps:
s21: the incoming flow conditions used for the support disturbance calculation are as follows:
in the formula (6), M is the Mach number of the corrected hole wall interference;
s22: respectively generating flow field calculation grids with and without straight tail supports, wherein except the flow field region space occupied by the supports, the flow field calculation grids with the support model and the flow field calculation grids without the supports are relatively consistent, so that calculation errors caused by grid differences are eliminated;
s23: respectively calculating flow fields with and without straight tail supports by using a CFD simulation calculation tool to obtain aerodynamic coefficients with the straight tail supportsAerodynamic coefficient without straight tail supportObtaining the disturbance correction quantity of the aerodynamic coefficient of the support disturbanceThe calculation formula is as follows:
preferably, step S3 specifically comprises the following steps:
s31: in the wind tunnel test process of the test model, a binocular vision system is used for photographing and recording mark points on the model wings, so that the displacement of the mark points after the model is deformed relative to the mark points before the model is deformed, namely the deformation generated by the test model wings under the test working condition is obtained;
s32: interpolating the deformation amount to a model surface grid of a calculation grid with a far-field unsupported model by using a RBF interpolation method according to the deformation amount of the mark point obtained in the step S31;
s33: according to the surface grid obtained after the model surface grid is deformed in the step S32, a motion grid method is used for transmitting the displacement disturbance of the surface grid to the whole computational domain grid, so that the flow field computational domain grid modeling with the elastic deformation model is realized, and the motion grid method is repeatedly used for performing computational domain grid modeling on the deformation of the test model under all working conditions;
s34: carrying out CFD flow field calculation on flow field calculation domain grids corresponding to the model deformed under different test working conditions to obtain aerodynamic coefficients of the real test model appearance under different working conditions;
S35: will be provided withAnd withThe correction quantity of the elastic deformation influence under the wind tunnel test working condition can be obtained by doing differenceThe calculation formula is as follows:
s36: changing the distribution of wing deformation torsion angles and the distribution of bending to form wings with different deformations, carrying out CFD pneumatic calculation on the wings with different deformations to obtain a sample set of aerodynamic force, deformation and working conditions, modeling by using a machine learning method according to the sample set, establishing a model between the deformation and flow working conditions of a wing structure and an aerodynamic force coefficient (or aerodynamic force coefficient correction), and giving a flight flow working condition and the aircraft deformation or structural attribute according to the real aircraft flight state to predict the aerodynamic force correction influenced by elastic deformation.
Preferably, the step S4 of correcting the influence of the reynolds number specifically includes the following steps:
s41: correcting the lift coefficient, the drag coefficient and the pitching moment coefficient, dividing the lift coefficient curve into three sections, and definingThe curve is a curve of aerodynamic coefficient variation with the angle of attack under the maximum Reynolds number data of a wind tunnel test, and ABC is defined as a curve of aerodynamic coefficient variation with the angle of attack under the condition of flight Reynolds number;
S42:of a curveThe critical Reynolds number at the point is equal to the maximum Reynolds number of the wind tunnel test, namelyThe critical Reynolds numbers Recrit of the curves at different attack angles are all smaller than the maximum Reynolds number of the wind tunnel test, and the aerodynamic force data of the AB section are obtained by correcting the wind tunnel test and CFD calculation data based on the variable Reynolds number;
s43: BC section aerodynamic data composed ofTo be provided withPoint-based point translation toIs obtained whereinPoint satisfiesThe slope of the tangent line corresponding to the lift line of the angle of attack is equal to the slope of the tangent line of the lift line at the AB section at the point B, and the slope is obtainedThe point corresponds to an attack angle;
s44: definition ofThe incidence angle corresponding to the point position is the critical incidence angleThe CFD aerodynamic coefficient is translated to wind tunnel test data along with the Reynolds number variation trend.
Preferably, the specific processing method of step S5 is as follows:
the wind tunnel test data is corrected to design data without a tunnel wall, support and deformation, and the design data is synthesized by using interference correction quantity, and the method specifically comprises the following steps:
nominal incoming flow conditions:、and the actual inflow working condition of the corrected data is as follows:、under the above working condition, the aerodynamic coefficient correction quantity is as follows:
in the formula (9), the first and second groups of the chemical reaction are shown in the specification,the disturbance correction amount of the resistance coefficient includes the sum of all disturbance amounts such as hole wall disturbance, support disturbance, elastic deformation influence, etc.,in order to support the disturbance correction amount,for the correction of the floating resistance of the empty wind tunnel,the model floating resistance correction quantity;
in the formula (10), the first and second groups,for the corresponding total lift coefficient correction amount,the disturbance correction is supported for the lift coefficient,the lift coefficient elastic deformation influence correction quantity;
when data needs to be corrected to a flight condition, the actual deformation and the actual Reynolds number of the airplane need to be introduced, and the specific formula is as follows:
in the formula (11, 12),、the Reynolds number obtained by calculating the variable Reynolds number influences the correction quantity of the drag coefficient and the lift coefficient, and is corrected from the test data to the data of the real flight Reynolds number condition.
And (3) superposing the correction quantities of the hole wall interference, the support interference, the elastic deformation influence and the Reynolds number influence according to requirements to obtain the correction quantity from the scaled airplane model to the real flight model, and superposing the wind tunnel test data to obtain the aerodynamic coefficient of the real flight model.
The application has beneficial effects that:
(1) The method comprises the steps of obtaining wall pressure information of a wind tunnel wall from a wind tunnel test, and simulating flow interference of the wind tunnel wall on a flow field near an airplane model by using the wall pressure information in numerical calculation; respectively carrying out CFD simulation calculation on the test original model and the combined configuration of various supports so as to obtain the support interference amount of the model; modeling the actual measurement test model, and obtaining aerodynamic force with or without elastic deformation by CFD simulation calculation so as to obtain elastic deformation influence quantity; carrying out variable Reynolds number CFD simulation calculation on the test model to obtain the Reynolds number influence correction quantity; and finally, according to the requirements, the correction quantities of the hole wall interference, the support interference, the elastic deformation influence and the Reynolds number influence are superposed to obtain the correction quantity from the scaled airplane model to the real flight model. The invention organically combines various interference quantities of the wind tunnel test model, forms a complete correction system and avoids repeated correction and insufficient correction. The method has the advantages that the actual measurement data of the wind tunnel test are utilized, the advantages of the CFD technology can be exerted, the matching degree of the correction result of the method and the correction method of the wind tunnel test is higher, and the correction of the wind tunnel test data can be carried out by replacing the test after full correction;
(2) The wind tunnel test data interference correction method combining the CFD technology and the test measurement data solves the problem of correlation between wind tunnel test data interference correction and flight data of an airplane scaling test model, can overcome the defect that a complicated test scheme needs to be additionally designed in the traditional independent test method, and even tests need to be developed in different wind tunnels, and is suitable for being applied to most of the wind tunnels.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
fig. 1 is a flowchart of a continuous transonic wind tunnel test data disturbance correction method according to an embodiment.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for the convenience of description, only the portions relevant to the application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Examples
The embodiment of the application provides a continuous transonic wind tunnel test data interference correction method (see fig. 1), which comprises the following steps:
fig. 1 shows in detail a flow of performing data correction such as tunnel wall interference, support interference, elastic deformation influence, reynolds number influence and the like on aircraft model wind tunnel test data, and includes the following steps:
s1: acquiring wall pressure information of a wind tunnel wall from a wind tunnel test, and simulating flow interference of the wind tunnel wall on a flow field near the airplane model by using the wall pressure information in numerical calculation;
the method comprises the following specific steps:
s11: carrying out an air wind tunnel test under the test working condition given by the test outline, and measuring axial static pressure by using a shaft probe in the test process; respectively arranging 3-5 wall pressure pipes on an upper wall plate and a lower wall plate of the wind tunnel test section to measure the wall pressure of the air permeable wall under different working conditions; obtaining axial static pressure distribution and gradient, rotating center pressure of an attack angle mechanism and chamber standing pressure;
s12: calculating the Mach number at the rotating center according to the pressure of the rotating center of the shaft probe displacement attack angle mechanism and the total pressure of the incoming flowAnd obtainWith nominal mach number of residenceThe relationship betweenCalculating the floating resistance correction of the air wind tunnel by axial static pressure distribution and gradient of the shaft probe; the calculation formula is as follows:
in the formula (1), V is the volume of the test model, S is the reference area of the test model, L is the reference length of the test model,is the difference between the Mach number at the center of rotation and the nominal Mach number of the parking cell;
s13: to be provided withCarrying out a wind tunnel test of a test model for a mach number of a test section controlled by a wind tunnel, measuring a lift coefficient CL (or a normal force coefficient CN of a body axis system model), a resistance coefficient CD (or an axial force coefficient CA of the body axis system model) and a pitching moment coefficient CM of the model through a rod balance, and simultaneously measuring static pressures of an upper ventilating wallboard and a lower ventilating wallboard of the test section;
s14: the static pressure of the air-permeable wall of the model test is differed from the static pressure of the air-permeable wall of the air tunnel to obtain wall pressure information of the air-permeable wall so as to eliminate the influence of irregular processing of a pressure measuring hole and the like, and the wall pressure is interpolated to the whole upper wall surface and the whole lower wall surface by a cubic spline fairing method;
s15: introducing wall pressure information of the air permeable wall into the air permeable wall by using a velocity potential function, and calculating the Mach number of the air permeable wall wind tunnel test section by using a double-parameter wall pressure information method integral methodAmount of influence of angle of attackAnd wind tunnel axis pressure distribution;
S16: according toCalculating the floating resistance generated under the constraint of the model and the support on the hole wall;
in the formula (2), the first and second groups of the compound,as a function of the cross-sectional area distribution along the axial model,for the x-direction standing position of the tail support cavity,is the cross section area of the cavity,is the axial coordinate of the model head vertex,is the axial coordinate of the model machine tail end point,is a wind tunnel axis pressure distribution function;
s17: influence quantity of CL and CD according to attack angleAnd (3) carrying out projection calculation again, and replacing the reference quantity of static pressure and quick pressure to obtain the correction quantity of the hole wall interference, wherein the calculation process is as follows:
in the formula (3), the first and second groups,is the ratio of the enthalpy of the incoming flow to the internal energy,=1.4, p is the static pressure,for the reference amount of the pressure of the incoming flow rate,in order to correct the incidence angle,is the attack angle of the model after the air flow deflection angle correction,is the angle of attack;
in the formula (4), FA is the axial aerodynamic force of the measured model of the balance, and FN is the normal aerodynamic force of the model;the model resistance coefficient after the correction of the hole wall interference,the corrected model lift coefficient is obtained;
in the formula (5), the first and second groups of the chemical reaction materials are selected from the group consisting of,the method is used for correcting the disturbance of the resistance coefficient of the disturbance model of the tunnel wall,And (4) correcting interference of the lift coefficient of the hole wall interference model.
S2: respectively carrying out CFD simulation calculation on the test original model and the combined configuration of various supports so as to obtain the support interference amount of the model;
the method comprises the following specific steps:
s21: obtaining the incoming flow working condition used for subsequently developing the support interference calculation according to the description result in the step S1:
s22: respectively generating flow field calculation grids with and without straight tail supports, wherein except for the flow field region space occupied by the supports, the flow field calculation grids with the support model and the flow field calculation grids without the supports are required to be as consistent as possible so as to eliminate calculation errors caused by grid differences;
s23: respectively calculating flow fields with and without straight tail supports by using a CFD simulation calculation tool to obtain respective aerodynamic coefficients C support 、C clean ;
S24: according to the above steps, the disturbance correction amount for supporting the disturbance aerodynamic coefficient is as follows.
S3: modeling the actually measured test model, and obtaining aerodynamic force with or without elastic deformation by CFD simulation calculation so as to obtain elastic deformation influence quantity;
the method comprises the following specific steps:
s31: in the wind tunnel test process of the test model, a binocular vision system is used for photographing and recording mark points on the model wings, so that the displacement of the mark points after the model is deformed relative to the mark points before the model is deformed, namely the deformation generated by the test model wings under the test working condition is obtained;
s32: according to the deformation of the mark points obtained in the S31, interpolating the deformation to a model surface grid of a calculation grid with a far-field unsupported model by using a RBF interpolation method;
s33: and (4) according to the surface mesh after the model surface mesh deformation obtained in the step (S32), transferring the surface mesh displacement disturbance to the whole computational domain mesh by using a motion mesh method, realizing the flow field computational domain mesh modeling with the elastic deformation model, and repeatedly using the motion mesh method to carry out the computational domain mesh modeling on the deformation of the test model under all working conditions. The motion grid method adopts a TFI/RBF method suitable for a structural grid;
s34: carrying out CFD flow field calculation on flow field calculation domain grids corresponding to the models deformed under different test working conditions to obtain aerodynamic coefficients of the shapes (with real deformation) of the real test models under different working conditions;
S35: and (4) subtracting the aerodynamic coefficient (with aeroelastic deformation and without support) calculated in the step (34) from the aerodynamic coefficient of the corresponding state (clean test model configuration and without support) in the step (23) to obtain the elastic deformation influence correction amount under the wind tunnel test working condition.
S36: the aerodynamic coefficient of the ideal rigid model without deformation is obtained through S35 correction. According to the aeroelastic deformation of the model wing measured in S31, on the basis of which the distribution of the torsion angle and the bending distribution of the wing deformation are changed to form a series of multiple deformations under various working conditions, CFD pneumatic calculation is carried out on the wings with different deformations to form a large number of samples of aerodynamic force, deformation and working conditions, a machine learning method is used for modeling on the samples to establish a model among the deformation quantity, the flow working condition and the aerodynamic force coefficient of the wing structure, or the model among the deformation quantity, the flow working condition and the aerodynamic force coefficient correction quantity of the wing structure, and the flight flow working condition and the aircraft deformation quantity or structural attributes are given according to the real aircraft flight state, so that the aerodynamic force correction quantity can be predicted.
S4: carrying out variable Reynolds number CFD simulation calculation on the test model to obtain the Reynolds number influence correction quantity;
the detailed steps are as follows:
s41: the lift coefficient curve obtained by correcting aerodynamic coefficients such as lift force, resistance force, pitching moment and the like is divided into three sections, whereinThe curve is a curve of aerodynamic coefficient variation with attack angle under the maximum Reynolds number data of a wind tunnel test, and ABC is a curve of aerodynamic coefficient variation with attack angle under the condition of flight Reynolds number;
S42:of curved linesThe critical Reynolds number at the point is equal to the maximum Reynolds number of the wind tunnel test, namelyThe critical Reynolds number Recrit under different attack angles of the curve is smaller than the maximum Reynolds number of the wind tunnel test, so that aerodynamic force data of a flight Reynolds number AB section can be obtained by correcting the wind tunnel test and CFD calculation data based on the variable Reynolds number;
s43: aerodynamic data of flight Reynolds number BC section is composed ofTo be provided withPoint-based point translation toIs obtained whereinPoint satisfiesThe slope of the tangent line corresponding to the lift line of the angle of attack is equal to the slope of the tangent line of the lift line at the AB section at the point B, so that the lift line of the angle of attack can be obtainedThe point corresponds to an attack angle;
s44: definition ofThe incidence angle corresponding to the point position is the critical incidence angleThe CFD aerodynamic coefficient is translated to wind tunnel test data along with the Reynolds number variation trend.
S5: and finally, according to the requirement, the correction quantities of the hole wall interference, the support interference, the elastic deformation influence and the Reynolds number influence are superposed to obtain the correction quantity from the scaled airplane model to the real flight model, wherein the specific method comprises the following steps:
the wind tunnel test data is corrected to design data without a tunnel wall, a support and an ideal deformation, and the following interference correction quantity synthesis method is used:
nominal working condition of incoming flow、(including the correction of the deflection angle of the airflow), and the actual inflow working conditions of the corrected data are as follows:、in this operating mode, the aerodynamic coefficient correction amount:
in the formula (9), the first and second groups of the chemical reaction are shown in the specification,the disturbance correction quantity of the resistance coefficient includes the sum of all disturbance quantities such as hole wall disturbance, support disturbance, elastic deformation influence and the like,in order to support the disturbance correction amount,for the correction of the floating resistance of the empty wind tunnel,is the model floating resistance correction;
in the formula (10), the first and second groups of the chemical reaction are shown in the formula,for a corresponding total lift coefficient correction,the disturbance correction is supported for the lift coefficient,the correction quantity is the elastic deformation influence correction quantity of the lift coefficient;
when data needs to be corrected to flight conditions, the actual deformation of the aircraft and the actual reynolds number also need to be considered.
In the formula (11, 12),、the Reynolds number obtained by calculating the variable Reynolds number influences the correction quantity of the drag coefficient and the lift coefficient, and is corrected from the test data to the data of the real flight Reynolds number condition.
And finally, according to the requirements, the correction quantities of the hole wall interference, the support interference, the elastic deformation influence and the Reynolds number influence are superposed to obtain the correction quantity from the scaled airplane model to the real flight model, and the wind tunnel test data are superposed to obtain the aerodynamic coefficient of the real flight model.
The above-mentioned embodiments are described in further detail for the purpose of illustrating the invention, and it should be understood that the above-mentioned embodiments are only examples of the present invention and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made on the basis of the technical solutions of the present invention should be included in the scope of the present invention.
Claims (10)
1. A continuous transonic wind tunnel test data interference correction method is characterized by comprising the following steps:
s1: acquiring wall pressure information of a wind tunnel wall from a wind tunnel test, and simulating flow interference of the wind tunnel wall on a flow field near the airplane model by using the wall pressure information in numerical calculation;
s2: respectively carrying out CFD simulation calculation on the original test model and the combined configuration of various supports so as to obtain the support interference of the model;
s3: modeling the actually measured test model, and obtaining aerodynamic force with or without elastic deformation by CFD simulation calculation so as to obtain elastic deformation influence quantity;
s4: carrying out variable Reynolds number CFD simulation calculation on the test model to obtain a Reynolds number influence correction quantity;
s5: and finally, according to the requirements, the corrections of the hole wall interference, the support interference, the elastic deformation influence and the Reynolds number influence are superposed to obtain the correction from the scaled airplane model to the real flight model.
2. The continuous transonic wind tunnel test data disturbance correction method according to claim 1, characterized in that the specific processing method of step S1 is as follows:
s11: carrying out an air wind tunnel test under the test working condition given by the test outline, and measuring axial static pressure by using a shaft probe in the test process; respectively arranging 3-5 wall pressure pipes on an upper wall plate and a lower wall plate of the wind tunnel test section to measure the wall pressure of the air permeable wall under different working conditions; obtaining axial static pressure distribution and gradient, rotation center pressure of an attack angle mechanism and chamber standing pressure;
s12: calculating the Mach number at the rotating center according to the pressure of the rotating center of the shaft probe displacement attack angle mechanism and the total pressure of the incoming flowAnd obtainMach number of nominal resident chamberThe relationship betweenCalculating the floating resistance correction of the air wind tunnel by axial static pressure distribution and gradient of the shaft probe,is the difference between the Mach number at the center of rotation and the nominal Mach number of the parking cell;
s13: to be provided withCarrying out a wind tunnel test of a test model for the Mach number of a test section controlled by a wind tunnel, measuring a lift coefficient CL, a resistance coefficient CD and a pitching moment coefficient CM of the model by a rod balance, and simultaneously measuring the static pressure of an upper ventilating wallboard and a lower ventilating wallboard of the test section;
s14: the static pressure of the air-permeable wall of the model test is differed from the static pressure of the air-permeable wall of the air tunnel to obtain wall pressure information of the air-permeable wall so as to eliminate the influence of irregular processing of a pressure measuring hole and the like, and the wall pressure is interpolated to the whole upper wall surface and the whole lower wall surface by a cubic spline fairing method;
s15: introducing wall pressure information of the air permeable wall into the air permeable wall by using a velocity potential function, and calculating the Mach number of the air permeable wall wind tunnel test section by using a double-parameter wall pressure information method integral methodAmount of influence of angle of attackAnd wind tunnel axis pressure distribution;
S16: according toCalculating the floating resistance generated under the constraint of the model and the support on the hole wall;
3. The continuous transonic wind tunnel test data disturbance correction method according to claim 2, wherein in step S12, the air wind tunnel floating resistance correction amountThe calculation formula of (a) is as follows:
in the formula (1), V is the volume of the test model, S is the reference area of the test model, and L is the reference length of the test model.
4. The continuous transonic wind tunnel test data interference correction method according to claim 3, characterized in that in step S16, the floating resistance isThe calculation formula of (a) is as follows:
in the formula (2), the first and second groups of the compound,as a function of the cross-sectional area distribution along the axial model,for the x-direction standing position of the tail support cavity,is the cross section area of the cavity,is the axial coordinate of the model head vertex,is the axial coordinate of the model machine tail end point,as a function of the wind tunnel axis pressure distribution.
5. The method for correcting the disturbance of the continuous transonic wind tunnel test data according to claim 4, wherein in step S17, the calculation process of the hole wall disturbance correction quantity is as follows:
in the formula (3), the first and second groups,is the ratio of the enthalpy of the incoming flow to the internal energy,1.4, p is the static pressure,for the reference amount of the pressure of the incoming flow rate,in order to correct the amount of the attack angle,is the attack angle of the model after the air flow deflection angle correction,is the angle of attack;
in the formula (4), FA is the axial aerodynamic force of the measured model of the balance, and FN is the normal aerodynamic force of the model;the model resistance coefficient after the correction of the hole wall interference,the corrected model lift coefficient;
in the formula (5), the first and second groups of the chemical reaction materials are selected from the group consisting of,the method is used for correcting the disturbance of the resistance coefficient of the disturbance model of the tunnel wall,And (4) correcting interference of the lift coefficient of the hole wall interference model.
6. The continuous transonic wind tunnel test data interference correction method according to claim 5, characterized in that the step S2 specifically comprises the following steps:
s21: the incoming flow conditions used for the support disturbance calculation are as follows:
in the formula (6), M is the Mach number after the hole wall interference is corrected;
s22: respectively generating flow field calculation grids with and without straight tail supports, wherein except the flow field region space occupied by the supports, the flow field calculation grids with the support model and the flow field calculation grids without the supports are relatively consistent, so that calculation errors caused by grid differences are eliminated;
s23: respectively calculating flow fields with and without straight tail supports by using a CFD simulation calculation tool to obtain aerodynamic coefficients with the straight tail supportsAerodynamic coefficient without straight tail supportObtaining the disturbance correction quantity of the aerodynamic coefficient of the support disturbanceThe calculation formula is as follows:
7. the continuous transonic wind tunnel test data disturbance correction method according to claim 6, wherein the step S3 specifically comprises the following steps:
s31: in the wind tunnel test process of the test model, a binocular vision system is used for photographing and recording the mark points on the model wings, so that the displacement of the mark points after the model is deformed relative to the mark points before the model is deformed, namely the deformation generated by the test model wings under the test working condition is obtained;
s32: interpolating the deformation amount to a model surface grid of a calculation grid with a far-field unsupported model by using a RBF interpolation method according to the deformation amount of the mark point obtained in the step S31;
s33: according to the surface grid obtained after the model surface grid is deformed in the step S32, a motion grid method is used for transmitting the displacement disturbance of the surface grid to the whole computational domain grid, so that the flow field computational domain grid modeling with the elastic deformation model is realized, and the motion grid method is repeatedly used for performing computational domain grid modeling on the deformation of the test model under all working conditions;
s34: carrying out CFD flow field calculation on flow field calculation domain grids corresponding to the model deformed under different test working conditions to obtain aerodynamic coefficients of the real test model appearance under different working conditions;
S35: will be provided withAndthe correction quantity of the elastic deformation influence under the wind tunnel test working condition can be obtained by doing differenceThe calculation formula is as follows:
s36: changing the distribution of wing deformation torsion angles and the distribution of bending to form wings with different deformations, carrying out CFD pneumatic calculation on the wings with different deformations to obtain a sample set of aerodynamic force, deformation and working conditions, and modeling by using a machine learning method according to the sample set;
establishing a model between the deformation and the flow condition of the wing structure and the aerodynamic coefficient, or establishing a model between the deformation and the flow condition of the wing structure and the correction of the aerodynamic coefficient;
and aiming at the flight state of the real airplane, the aerodynamic correction quantity influenced by the elastic deformation can be predicted by giving the flight flow working condition and the deformation quantity or the structural attribute of the airplane.
8. The continuous transonic wind tunnel test data disturbance correction method according to claim 7, characterized in that in step S33, the motion grid method adopts a TFI/RBF method suitable for a structural grid.
9. The continuous transonic wind tunnel test data interference correction method according to claim 8, characterized in that the step S4 of correcting the influence of Reynolds number specifically comprises the following steps:
s41: correcting the lift coefficient, the drag coefficient and the pitching moment coefficient, dividing the lift coefficient curve into three sections, and definingThe curve is a curve of aerodynamic coefficient variation with the angle of attack under the maximum Reynolds number data of a wind tunnel test, and ABC is defined as a curve of aerodynamic coefficient variation with the angle of attack under the condition of flight Reynolds number;
S42:of curved linesThe critical Reynolds number at the point is equal to the maximum Reynolds number of the wind tunnel test, namelyThe critical Reynolds numbers Recrit of the curves at different attack angles are all smaller than the maximum Reynolds number of the wind tunnel test, and the aerodynamic force data of the AB section are obtained by correcting the wind tunnel test and CFD calculation data based on the variable Reynolds number;
s43: BC section aerodynamic force data composed ofTo be provided withPoint-based point translation toIs obtained in whichPoint satisfiesThe slope of the tangent line corresponding to the lift line of the angle of attack is equal to the slope of the tangent line of the lift line at the AB section at the point B, and the slope is obtainedCorresponding to an attack angle;
10. The continuous transonic wind tunnel test data disturbance correction method according to claim 9, characterized in that the specific processing method of step S5 is as follows:
the wind tunnel test data is corrected to design data without a tunnel wall, support and deformation, and the design data is synthesized by using interference correction quantity, and the method specifically comprises the following steps:
nominal incoming flow conditions:、and the actual inflow working condition of the corrected data is as follows:、under the above working condition, the aerodynamic coefficient correction quantity is as follows:
in the formula (9), the first and second groups,the disturbance correction quantity is the disturbance correction quantity of the resistance coefficient, including the hole wall disturbance, the support disturbance, the elastic deformation influence and the likeThe sum of all the interference quantities is obtained,in order to support the disturbance correction amount,for the correction of the floating resistance of the empty wind tunnel,is the model floating resistance correction;
in the formula (10), the first and second groups of the chemical reaction are shown in the formula,for a corresponding total lift coefficient correction,the disturbance correction is supported for the lift coefficient,the correction quantity is the elastic deformation influence correction quantity of the lift coefficient;
when data needs to be corrected to a flight condition, the actual deformation and the actual Reynolds number of the airplane need to be introduced, and the specific formula is as follows:
in the formula (11, 12),、modifying the data of the real flying Reynolds number condition from the test data for the Reynolds number influence resistance coefficient and lift coefficient correction quantity obtained by calculating the variable Reynolds number;
and (3) according to the requirements, the corrections of the tunnel wall interference, the support interference, the elastic deformation influence and the Reynolds number influence are superposed to obtain the correction from the scaled aircraft model to the real flight model, and the wind tunnel test data are superposed to obtain the aerodynamic coefficient of the real flight model.
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