Aircraft wind tunnel test data consistency optimization method, system, device and medium
By constructing a dual correction factor model and automating the processing of wind tunnel force and pressure data, the problem of data inconsistency in aircraft wind tunnel tests was solved, improving correction efficiency and accuracy while reducing costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- 四川腾盾科技有限公司
- Filing Date
- 2026-04-13
- Publication Date
- 2026-07-03
AI Technical Summary
Existing technologies have systematic biases in wind tunnel testing of aircraft, leading to inconsistent test results. Correction methods are inefficient, experience-dependent, and costly.
By constructing a dual correction factor model, based on wind tunnel force and pressure measurement data, cubic spline interpolation and aerodynamic coefficient integration are used to automatically correct wind tunnel test data, reducing manual intervention.
It improved the accuracy and efficiency of data correction, reduced experimental costs, reduced human resource investment, and achieved data consistency optimization.
Smart Images
Figure CN122020861B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of wind tunnel testing technology for aircraft, and in particular to a method, system, equipment, and medium for optimizing the consistency of wind tunnel test data for aircraft. Background Technology
[0002] In the field of aerospace aerodynamics research, wind tunnel testing is a core means of obtaining the aerodynamic characteristics of aircraft. Among them, wind tunnel force measurement tests and wind tunnel pressure measurement tests are two fundamental and crucial test types. Wind tunnel force measurement tests directly acquire the aerodynamic and moment parameters (including lift, drag, side force, pitch moment, roll moment, and yaw moment) of the entire wind tunnel model and key components through high-precision mechanical measurement devices (typically multi-component strain gauge force balances). The measurement results directly reflect the overall mechanical response of the model under specific incoming flow conditions. Wind tunnel pressure measurement tests, on the other hand, collect surface pressure data at a limited number of discrete points on the model surface through a pressure sensor array (such as miniature piezoresistive sensors or piezoelectric sensors). Combined with the model surface topology, the aerodynamic characteristics of the entire aircraft or components are obtained through integral calculations. This test focuses more on revealing the interaction mechanism between the flow field and the model surface.
[0003] However, in practical engineering applications, there are often significant systematic deviations in the results of the two types of tests. The core causes include three aspects: First, model manufacturing errors. Force measurement models need to ensure stiffness to avoid interference from balance measurements, while pressure measurement models need to reserve sensor installation channels. The two have inherent differences in geometric shape (such as surface finish and the outline of key aerodynamic components) and structural stiffness, resulting in inconsistent flow field characteristics. Second, differences in measurement system accuracy. The measurement accuracy of force balances is affected by temperature drift and load coupling interference, while pressure sensors have problems such as zero-point drift and dynamic response hysteresis. The calibration standards and traceability systems of the two types of sensors are different, further aggravating data deviations. Third, disturbances in the test environment. There are subtle differences in the uniformity of incoming flow (such as turbulence intensity and Mach number stability), model installation attitude (such as the calibration accuracy of angle of attack and sideslip angle), and wind tunnel flow field boundary conditions (such as the tunnel wall interference correction coefficient) between the two tests, which makes it impossible to completely reproduce the test conditions.
[0004] Currently, the mainstream deviation correction method in engineering relies on manual comparison correction. This involves conducting individual component force measurement tests and comparing the component's force measurement data with the corresponding component's pressure measurement integral data point by point, establishing a correction factor matrix to iteratively correct the pressure measurement results. While this method can reduce deviations to some extent, it has significant technical drawbacks, specifically:
[0005] 1. Low testing efficiency: Individual force measurement test schemes and models need to be designed for each key component such as wings, fuselage, and tail. To complete the correction of the whole aircraft, multiple rounds of tests such as whole aircraft force measurement, whole aircraft pressure measurement, and multi-component force measurement need to be carried out in sequence. The entire correction cycle usually takes several weeks or even months, which is difficult to meet the high efficiency requirements of aircraft aerodynamic design iteration.
[0006] 2. High dependence on experience: The correction process relies on the engineer's understanding of aerodynamic flow mechanisms (such as shock wave location, boundary layer separation, and vortex interference), and the selection of correction factors and the direction of iteration are highly subjective. For complex flow fields (such as transonic flow and high angle-of-attack separated flow), empirical judgment is prone to deviation, resulting in insufficient reliability and robustness of the correction results.
[0007] 3. High overall costs: The design and fabrication of additional component force measurement models require significant materials and labor, and multiple rounds of testing consume wind tunnel testing resources, leading to a substantial increase in testing costs. Furthermore, the manual correction process requires a team of experienced engineers, further driving up labor costs. Summary of the Invention
[0008] To address the aforementioned issues, this invention proposes a method, system, equipment, and medium for optimizing the consistency of wind tunnel test data for aircraft. By integrating the geometric and aerodynamic features of the model, a dual correction factor model is constructed, eliminating manual intervention and improving correction efficiency and reliability. This solves the comprehensive problems of poor accuracy, low efficiency, reliance on experience, and high cost.
[0009] The technical solution adopted in this invention is as follows:
[0010] A method for optimizing the consistency of wind tunnel test data for aircraft includes:
[0011] Acquire wind tunnel force measurement data and wind tunnel pressure measurement data, perform cubic spline interpolation on the wind tunnel pressure measurement data, and calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle;
[0012] Based on the wind tunnel pressure measurement data and the geometric parameters of the pressure measurement model, the aerodynamic coefficients are integrated to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data;
[0013] The normal scaling factor is obtained by comparing the normal force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data, and the lateral scaling factor is obtained by comparing the lateral force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data.
[0014] Based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, a double correction factor model is constructed for each pressure measurement point, and the corrected pressure coefficient is solved.
[0015] Furthermore, the acquisition of wind tunnel force measurement data and wind tunnel pressure measurement data includes: obtaining the normal force coefficient through wind tunnel force measurement tests. and lateral force coefficient The pressure coefficients at all pressure measurement points of the entire machine were obtained through wind tunnel pressure testing. ;in, For the angle of attack, Sideslip angle, For aerodynamic control surface deflection, Number the pressure measurement point.
[0016] Furthermore, the step of performing cubic spline interpolation on the wind tunnel pressure measurement data to calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle includes:
[0017]
[0018]
[0019] in, The pressure coefficient, This is the partial derivative of the pressure coefficient with respect to the angle of attack. The partial derivative of the pressure coefficient with respect to the sideslip angle is given; the cubic spline interpolation process employs natural boundary conditions to make the interpolation curve second-order continuous and differentiable.
[0020] Furthermore, the aerodynamic coefficient integration based on wind tunnel pressure measurement data and the geometric parameters of the pressure measurement model to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data includes:
[0021]
[0022]
[0023] in, The normal force coefficient is from wind tunnel pressure measurement data. The lateral force coefficient is from wind tunnel pressure data. For the first The normal component of each pressure measurement point in the y-direction. For the first The normal component of each pressure measurement point in the z-direction. For the first The area corresponding to each pressure measurement point For reference area of the entire aircraft, Number the pressure measurement point.
[0024] Furthermore, the step of comparing the normal force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data to obtain the normal scaling factor, and comparing the lateral force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data to obtain the lateral scaling factor, includes:
[0025]
[0026]
[0027] in, Normal scaling factor This is the lateral scaling factor.
[0028] Furthermore, the construction of a dual-correction factor model for each pressure measurement point based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle includes:
[0029]
[0030] in, For the first The pressure coefficient after correction at each pressure measurement point and These are coefficients to be determined.
[0031] Furthermore, the solution for the corrected pressure coefficient includes:
[0032] Solving for undetermined coefficients using the method of undetermined coefficients and Solve the system of equations:
[0033]
[0034] Solving for the undetermined coefficients by solving a system of simultaneous equations and Then, substitute it into the double correction factor model to solve for the first... Pressure coefficient corrected for each pressure measurement point .
[0035] A system for optimizing the consistency of wind tunnel test data for aircraft includes:
[0036] The data acquisition and preprocessing module is configured to acquire wind tunnel force measurement data and wind tunnel pressure measurement data, perform cubic spline interpolation on the wind tunnel pressure measurement data, and calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle.
[0037] The aerodynamic coefficient integration module is configured to integrate aerodynamic coefficients based on wind tunnel pressure measurement data and pressure model geometric parameters to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data.
[0038] The scaling factor calculation module is configured to calculate the normal scaling factor by comparing the normal force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data, and to calculate the lateral scaling factor by comparing the lateral force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data.
[0039] The modified pressure coefficient solution module is configured to construct a dual-modification factor model for each pressure measurement point based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, and solve for the modified pressure coefficient.
[0040] A computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement the above-described method for optimizing the consistency of wind tunnel test data for aircraft.
[0041] A computer-readable storage medium storing a computer program that, when executed by a processor, implements the aforementioned method for optimizing the consistency of wind tunnel test data for aircraft.
[0042] The beneficial effects of this invention are as follows:
[0043] 1. Based on wind tunnel test data, this invention calculates the derivatives of the pressure coefficient at each pressure measurement point with respect to the angle of attack and sideslip angle using cubic spline interpolation. Compared with linear interpolation, this method has higher accuracy and smaller error.
[0044] 2. This invention incorporates both the geometric normal and the aerodynamic derivative of the model into the correction factor through a multi-feature fusion method, resulting in a clear physical meaning.
[0045] 3. This invention does not require additional component force measurement tests; corrections can be completed in a single wind tunnel pressure test, saving test time and effectively optimizing costs.
[0046] 4. The entire correction process of this invention can be implemented through a program, avoiding errors caused by insufficient experience of engineers and saving manpower and time costs. Attached Figure Description
[0047] Figure 1 This is a flowchart of a method for optimizing the consistency of wind tunnel test data for aircraft, according to Embodiment 1 of the present invention. Detailed Implementation
[0048] To provide a clearer understanding of the technical features, objectives, and effects of the present invention, specific embodiments are now described. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention; that is, the described embodiments are only a part of the embodiments of the invention, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.
[0049] Example 1
[0050] like Figure 1 As shown in the figure, this embodiment provides a method for optimizing the consistency of wind tunnel test data for aircraft, including:
[0051] Acquire wind tunnel force measurement data and wind tunnel pressure measurement data, perform cubic spline interpolation on the wind tunnel pressure measurement data, and calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle;
[0052] Based on the wind tunnel pressure measurement data and the geometric parameters of the pressure measurement model, the aerodynamic coefficients are integrated to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data;
[0053] The normal scaling factor is obtained by comparing the normal force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data, and the lateral scaling factor is obtained by comparing the lateral force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data.
[0054] Based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, a double correction factor model is constructed for each pressure measurement point, and the corrected pressure coefficient is solved.
[0055] Preferably, acquiring wind tunnel force measurement data and wind tunnel pressure measurement data includes: obtaining the normal force coefficient through wind tunnel force measurement tests. and lateral force coefficient The pressure coefficients at all pressure measurement points of the entire machine were obtained through wind tunnel pressure testing. ;in, For the angle of attack, Sideslip angle, For aerodynamic control surface deflection, Number the pressure measurement point.
[0056] Specifically, the wind tunnel force measurement data and wind tunnel pressure measurement data obtained are shown in Table 1 and Table 2.
[0057] Table 1 - Results of the Force Measurement Test
[0058]
[0059] Table 2 - Pressure Test Results
[0060]
[0061] Preferably, the wind tunnel pressure measurement data is subjected to cubic spline interpolation to calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, including:
[0062]
[0063]
[0064] in, The pressure coefficient, This is the partial derivative of the pressure coefficient with respect to the angle of attack. The partial derivative of the pressure coefficient with respect to the sideslip angle is given; the cubic spline interpolation process uses natural boundary conditions to make the interpolation curve second-order continuous and differentiable.
[0065] Specifically, taking data at a 4-degree angle of attack as an example, the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle... =[-0.0205,-0.0121,-0.0060,-0.0068……], Lateral heading .
[0066] Preferably, aerodynamic coefficients are integrated based on wind tunnel pressure measurement data and the geometric parameters of the pressure measurement model to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data, including:
[0067]
[0068]
[0069] in, The normal force coefficient is from wind tunnel pressure measurement data. The lateral force coefficient is from wind tunnel pressure data. For the first The normal component of each pressure measurement point in the y-direction. For the first The normal component of each pressure measurement point in the z-direction. For the first The area corresponding to each pressure measurement point For reference area of the entire aircraft, Number the pressure measurement point.
[0070] Specifically, the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data obtained by integration are shown in Table 3.
[0071] Table 3 - Integral Results of Pressure Distribution
[0072]
[0073] Preferably, the normal scaling factor is obtained by comparing the normal force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data, and the lateral scaling factor is obtained by comparing the lateral force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data, including:
[0074]
[0075]
[0076] in, Normal scaling factor This is the lateral scaling factor.
[0077] Specifically, taking data at an angle of attack of 4 degrees as an example, the normal force coefficient of wind tunnel force measurement data and wind tunnel pressure measurement data is compared to obtain the normal scaling factor. 1.164, the lateral scaling factor is obtained by comparing the lateral force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data. .
[0078] Preferably, a dual-correction factor model is constructed for each pressure measurement point based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, including:
[0079]
[0080] in, For the first The pressure coefficient after correction at each pressure measurement point and These are coefficients to be determined.
[0081] Specifically, this embodiment is based on the correction factor calculated using the aforementioned dual correction factor model. =[1.1094,1.0865,1.2338,1.2607……], and solve for the corrected pressure coefficient, as detailed in Table 4.
[0082] Table 4 - Corrected pressure coefficient distribution
[0083]
[0084] Preferably, solving for the corrected pressure coefficient includes solving for the undetermined coefficients using the method of undetermined coefficients. and Solve the system of equations:
[0085]
[0086] Solving for the undetermined coefficients by solving a system of simultaneous equations and Then, substitute it into the double correction factor model to solve for the first... Pressure coefficient corrected for each pressure measurement point .
[0087] Specifically, the corrected component integration results obtained in this embodiment are detailed in Table 5.
[0088] Table 5 - Corrected component integration results
[0089]
[0090] As shown in Table 5, the corrected result matches the force measurement result perfectly, demonstrating the effectiveness of this method.
[0091] Example 2
[0092] This embodiment provides a system for optimizing the consistency of wind tunnel test data for aircraft, including:
[0093] The data acquisition and preprocessing module is configured to acquire wind tunnel force measurement data and wind tunnel pressure measurement data, perform cubic spline interpolation on the wind tunnel pressure measurement data, and calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle.
[0094] The aerodynamic coefficient integration module is configured to integrate aerodynamic coefficients based on wind tunnel pressure measurement data and pressure model geometric parameters to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data.
[0095] The scaling factor calculation module is configured to calculate the normal scaling factor by comparing the normal force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data, and to calculate the lateral scaling factor by comparing the lateral force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data.
[0096] The modified pressure coefficient solution module is configured to construct a dual-modification factor model for each pressure measurement point based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, and solve for the modified pressure coefficient.
[0097] Example 3
[0098] This embodiment is based on embodiment 1:
[0099] This embodiment provides a computer device, including a memory and a processor. The memory stores a computer program, and the processor executes the computer program to implement the aircraft wind tunnel test data consistency optimization method of Embodiment 1. The computer program can be in the form of source code, object code, executable file, or some intermediate form.
[0100] Example 4
[0101] This embodiment is based on embodiment 1:
[0102] This embodiment provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the aircraft wind tunnel test data consistency optimization method of Embodiment 1. The computer program can be in the form of source code, object code, executable file, or some intermediate form. The storage medium includes any entity or device capable of carrying computer program code, a recording medium, a computer memory, a read-only memory (ROM), a random access memory (RAM), an electrical carrier signal, a telecommunication signal, and a software distribution medium, etc. It should be noted that the content contained in the storage medium can be appropriately added or removed according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the storage medium does not include electrical carrier signals and telecommunication signals.
[0103] The above description is merely a preferred embodiment of the present invention. It should be understood that the present invention is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the concept described herein through the above teachings or related technologies or knowledge. Modifications and variations made by those skilled in the art that do not depart from the spirit and scope of the present invention should be within the protection scope of the appended claims.
[0104] It should be noted that, for the sake of simplicity, the foregoing method embodiments are described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.
Claims
1. A method for optimizing data consistency for aircraft wind tunnel testing, comprising: include: Acquire wind tunnel force measurement data and wind tunnel pressure measurement data, perform cubic spline interpolation on the wind tunnel pressure measurement data, and calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle; Based on the wind tunnel pressure measurement data and the geometric parameters of the pressure measurement model, the aerodynamic coefficients are integrated to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data; The normal scaling factor is obtained by comparing the normal force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data, and the lateral scaling factor is obtained by comparing the lateral force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data. Based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, a double correction factor model is constructed for each pressure measurement point, and the corrected pressure coefficient is solved. The method constructs a dual-correction factor model for each pressure measurement point based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, including: in, For the first The pressure coefficient after correction at each pressure measurement point and These are coefficients to be determined; For the angle of attack, Sideslip angle, For aerodynamic control surface deflection, Number the pressure measurement points; This is the partial derivative of the pressure coefficient with respect to the angle of attack. This is the partial derivative of the pressure coefficient with respect to the sideslip angle; For the first The normal component of each pressure measurement point in the y-direction. For the first The normal component of each pressure measurement point in the z-direction; Normal scaling factor This is the lateral scaling factor; The solution for the corrected pressure coefficient includes: Solving for undetermined coefficients using the method of undetermined coefficients and Solve the system of equations: wherein, is the normal force coefficient, is the side force coefficient, is the pressure coefficient, is the area corresponding to the th pressure tap, is the total machine reference area; Solving the unknown coefficients by simultaneous equations and After that, the pressure coefficients of the first and the second pressure taps are solved by the double correction factor model .
2. The aircraft wind tunnel test data conformity optimization method of Claim 1, wherein, The acquisition of wind tunnel force measurement data and wind tunnel pressure measurement data includes: obtaining the normal force coefficient through wind tunnel force measurement tests. and lateral force coefficient The pressure coefficients at all pressure measurement points of the entire machine were obtained through wind tunnel pressure testing. ;in, For the angle of attack, Sideslip angle, For aerodynamic control surface deflection, Number the pressure measurement point.
3. The aircraft wind tunnel test data conformity optimization method of Claim 2, wherein, The process of performing cubic spline interpolation on the wind tunnel pressure measurement data and calculating the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle includes: wherein is the pressure coefficient, is the partial derivative of the pressure coefficient with respect to the angle of attack, is the partial derivative of the pressure coefficient with respect to the side slip angle; the cubic spline interpolation process employs natural boundary conditions, making the interpolated curve twice continuously differentiable.
4. The aircraft wind tunnel test data conformity optimization method of Claim 3, wherein, The aerodynamic coefficients are integrated based on wind tunnel pressure measurement data and the geometric parameters of the pressure measurement model to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data, including: in, The normal force coefficient is from wind tunnel pressure measurement data. The lateral force coefficient is from wind tunnel pressure data. For the first The normal component of each pressure measurement point in the y-direction. For the first The normal component of each pressure measurement point in the z-direction. For the first The area corresponding to each pressure measurement point For reference area of the entire aircraft, Number the pressure measurement point.
5. The aircraft wind tunnel test data conformity optimization method of Claim 4, wherein, The process of comparing the normal force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data to obtain the normal scaling factor, and comparing the lateral force coefficients of wind tunnel force measurement data and wind tunnel pressure measurement data to obtain the lateral scaling factor, includes: wherein is a normal proportionality factor, is a lateral proportionality factor.
6. An aircraft wind tunnel test data consistency optimization system applying the aircraft wind tunnel test data consistency optimization method as recited in claim 1, characterized by, include: The data acquisition and preprocessing module is configured to acquire wind tunnel force measurement data and wind tunnel pressure measurement data, perform cubic spline interpolation on the wind tunnel pressure measurement data, and calculate the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle. The aerodynamic coefficient integration module is configured to integrate aerodynamic coefficients based on wind tunnel pressure measurement data and pressure model geometric parameters to obtain the normal force coefficient and lateral force coefficient of the wind tunnel pressure measurement data. The scaling factor calculation module is configured to calculate the normal scaling factor by comparing the normal force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data, and to calculate the lateral scaling factor by comparing the lateral force coefficients of the wind tunnel force measurement data and the wind tunnel pressure measurement data. The modified pressure coefficient solution module is configured to construct a dual-modification factor model for each pressure measurement point based on the normal scaling factor, the lateral scaling factor, and the partial derivatives of the pressure coefficient with respect to the angle of attack and sideslip angle, and solve for the modified pressure coefficient.
7. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the aircraft wind tunnel test data consistency optimization method according to any one of claims 1-5.
8. A computer readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the aircraft wind tunnel test data consistency optimization method according to any one of claims 1-5.