CN112857736A - Test method for obtaining influence of flow field nonuniformity on model aerodynamic characteristics - Google Patents
Test method for obtaining influence of flow field nonuniformity on model aerodynamic characteristics Download PDFInfo
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Abstract
The invention discloses a test method for obtaining the influence of flow field nonuniformity on model aerodynamic characteristics. The method comprises the steps of placing a model at a plurality of positions such as the upstream, the center and the downstream of a uniform area of a wind tunnel test section, and carrying out force measurement tests at different positions along the airflow direction; placing the model on a plurality of positions such as an axis, an upper part of the axis, a lower part of the axis and the like of a uniform area of a wind tunnel test section, and performing force measurement tests at different positions in the vertical direction; by changing the length of the balance supporting rod, the rotation center of the mechanism is positioned at the front section, the middle section and the tail end of the model, and force measurement tests of the rotation center at different positions of the model are carried out; under the same attack angle, a downwind direction continuous force measurement test and a vertical airflow direction continuous force measurement test are carried out. And the influence of the flow field nonuniformity of each factor on the pneumatic characteristic of the model can be examined in a mode of combining one or more modes. The method is simple and convenient, obtains comprehensive data, and can accurately analyze the influence of the flow field nonuniformity on the model aerodynamic characteristics.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a test method for obtaining influence of flow field nonuniformity on model aerodynamic characteristics.
Background
In the aircraft development process, the performance of the aircraft needs to be verified through a wind tunnel test, and the quality of wind tunnel test data directly influences the design and the development period of the aircraft. Therefore, there is a need for evaluation of wind tunnel test data quality, which has shifted from the early evaluation of data repeatability accuracy alone to evaluation of data uncertainty.
From published literature, NASA, aecc, boeing, etc. have performed uncertainty analysis on typical tests performed in multiple wind tunnels. The main influence factors of the wind tunnel data uncertainty are found from the calibration of a wind tunnel flow field and a balance, in a supersonic flow field, the non-uniformity of airflow is the main influence factor of the uncertainty, and the influence of the flow field quality on the error depends on the layout form of the model. The existing method for evaluating test data cannot accurately evaluate the influence of flow field nonuniformity on aerodynamic characteristics.
At present, a test method for acquiring the influence of flow field nonuniformity on the model aerodynamic characteristics needs to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a test method for obtaining the influence of flow field nonuniformity on model aerodynamic characteristics.
The test method for acquiring the influence of the flow field nonuniformity on the model aerodynamic characteristics comprises the following steps:
a. the model is arranged between a wind tunnel spray pipe and a diffuser of a test section and is fixed on an attack angle mechanism of the wind tunnel test section, the center of the model is positioned at the rotation center of the attack angle mechanism, the length of the model is L, and the height of the model projected on the section of the spray pipe when the model is positioned at the maximum attack angle is H;
b. defining the horizontal position of the model in the step a as a streamwise middle position S2, the forward position along the X-axis direction of the wind tunnel as a streamwise upstream position S1, the backward position along the X-axis direction of the wind tunnel as a streamwise downstream position S3, wherein the distances among S1, S2 and S3 are equal, the distance between S1 and S3 is a streamwise continuous change position range SL, and SL is more than L; respectively moving the model to S1, S2 and S3 positions, adjusting the attack angle of the model to zero, and performing a wind tunnel variable attack angle force measurement test;
c. defining the vertical position of the model in the step a as a central axis position V2 in the vertical airflow direction, the upward position in the Y-axis direction of the wind tunnel as a position V1 above the central axis in the vertical airflow direction, the downward position in the Y-axis direction of the wind tunnel as a position V3 below the central axis in the vertical airflow direction, wherein the distances among V1, V2 and V3 are equal, the distance between V1 and V3 is a position range VL of continuous change in the vertical airflow direction, and VL is greater than H; respectively moving the model to V1, V2 and V3 positions, adjusting the attack angle of the model to zero, and performing a wind tunnel variable attack angle force measurement test;
d. defining the position of the model in the step a as a rotation center, wherein the position of the rotation center in the model is R2, and the length of a corresponding model support rod II is LL; processing a model supporting rod I, wherein the length of the model supporting rod I is LL + delta L, replacing a model supporting rod II with the model supporting rod I, and enabling the rotation center of the model to be at the tail position R1 of the model; processing a model supporting rod III, wherein the length of the model supporting rod III is LL-delta L, replacing the model supporting rod I with the model supporting rod III, and the rotating center of the model is at the head position R3 of the model; adjusting the model attack angle to zero at the positions of R1, R2 and R3, and carrying out a wind tunnel variable attack angle force measurement test;
e. the positions S2, V2 and R2 in the steps b-d are the same, 3 times of six-component force measurement test results f1(A, N, Z, Mx, My and Mz) of the same position are obtained, and 3 times of f1 are simply called multiple times of measurement; the positions of S1, S3, V1, V3, R1 and R3 are different, and the dynamometry test results f2(A, N, Z, Mx, My and Mz), f3(A, N, Z, Mx, My and Mz), f4(A, N, Z, Mx, My and Mz), f5(A, N, Z, Mx, My and Mz), f6(A, N, Z, Mx, My and Mz) and f7(A, N, Z, Mx, My and Mz) of the other six positions are respectively obtained, and f 1-f 7 are simply called multi-position measurement; a, N, Z, Mx, My and Mz are respectively axial force, normal force, lateral force, rolling moment, yawing moment and pitching moment of the model;
respectively calculating the root mean square error sigma of each aerodynamic coefficient measured for multiple times under each attack angleA、σN、σZ、σMx、σMy、σMzAnd uncertainty UA、UN、UZ、UMx、UMy、UMz；
Respectively calculating the maximum deviation delta of each aerodynamic coefficient measured at multiple positions under each attack angleA、δN、δZ、δMx、δMy、δMz；
f. Examining the maximum deviation δ of the aerodynamic coefficients of the multi-position measurement of step eA、δN、δZ、δMx、δMy、δMzSearching an attack angle corresponding to the maximum deviation, adjusting the attack angle of the model to be under the attack angle, and continuously moving the SL to measure the force along the airflow direction through the wind tunnel test section attack angle mechanism along the S1, S2 and S3 to obtain a continuous force measurement test result along the airflow direction; continuously moving the VL to measure the force along the vertical airflow directions V1, V2 and V3 by the wind tunnel test section attack angle mechanism along the airflow direction to obtain a test result of continuously measuring the force along the vertical airflow direction;
g. and e, combining the test results of the step e and the step f, respectively calculating error bands of A, N, Z, Mx, My and Mz of the model, and evaluating the influence of the flow field nonuniformity on the A, N, Z, Mx, My and Mz of the model.
Further, the wind tunnel variable attack angle force measurement test adopts a step variable attack angle mode or a continuous variable attack angle mode.
Further, the downwind direction middle position is unchanged, and S1, S2 and S3 are expanded to S1 and S2 … … Sm according to the calculation requirement, wherein m is larger than 3.
Further, the positions of the central axes in the vertical airflow direction are unchanged, V1, V2 and V3 are expanded to V1 and V2 … … Vn according to the calculation requirement, and n is larger than 3.
Further, the rotation center is unchanged at the middle position of the model, R1, R2 and R3 are expanded to R1 and R2 … … Rk according to the calculation requirement, and k is larger than 3.
Further, the test method selects one of the steps b, c and d, and correspondingly completes research on influence of the non-uniformity of the flow field in the forward direction on the aerodynamic characteristics of the model, research on influence of the non-uniformity of the flow field in the vertical direction on the aerodynamic characteristics of the model and research on influence of the non-uniformity of the flow field at different rotation center positions on the aerodynamic characteristics of the model.
Further, the test method selects any two of the steps b, c and d, and correspondingly completes the research on the influence of the flow field nonuniformity of any two factors in the downstream direction, the vertical direction flow field and the rotation center position on the model aerodynamic characteristics.
According to the test method for acquiring the influence of the flow field nonuniformity on the aerodynamic characteristics of the model, the model is placed at multiple positions such as the upstream, the center and the downstream of a uniform area of a wind tunnel test section, and force measurement tests are performed at different positions along the airflow direction; placing the model on a plurality of positions such as an axis, an upper part of the axis, a lower part of the axis and the like of a uniform area of a wind tunnel test section, and performing force measurement tests at different positions in the vertical direction; by changing the length of the balance supporting rod, the rotation center of the mechanism is positioned at the front section, the middle section and the tail end of the model, and force measurement tests of the rotation center at different positions of the model are carried out; under the same attack angle, a downwind direction continuous force measurement test and a vertical airflow direction continuous force measurement test are carried out. And the influence of the flow field nonuniformity of each factor on the pneumatic characteristic of the model can be examined in a mode of combining one or more modes.
In order to fully and completely examine the range, the test method for obtaining the influence of the flow field nonuniformity on the model aerodynamic characteristics requires that the downstream position transformation range is larger than the model length, the vertical airflow position transformation range is larger than the model projection height, namely the downstream position SL is larger than the model length L, and the vertical airflow position VL is larger than the model projection height H.
The test method for acquiring the influence of the flow field nonuniformity on the model aerodynamic characteristics can accurately acquire the wind tunnel test data error band; particularly, the continuous force measurement test in the air flow direction and the continuous force measurement test in the vertical air flow direction enrich data information, and are beneficial to analyzing the influence rule of the flow field uniformity on the model aerodynamic characteristics.
By adopting the test method for acquiring the influence of the flow field nonuniformity on the model aerodynamic characteristics, a sufficient number of multi-position tests can be selected to be developed in a large-scale wind tunnel to estimate the test data error band, and the test data error band is estimated without performing a plurality of wind tunnel comparison tests.
The test method for acquiring the influence of the flow field nonuniformity on the model aerodynamic characteristics is simple and convenient, acquires comprehensive data, and can accurately analyze the influence of the flow field nonuniformity on the model aerodynamic characteristics.
Drawings
FIG. 1 is a schematic diagram of a model in a wind tunnel in a variable angle of attack force measurement test;
FIG. 2 is a schematic view of a force measurement test at different positions along the air flow direction in a wind tunnel variable attack angle force measurement test;
FIG. 3 is a schematic view of a force measurement test at different positions in the vertical direction in a wind tunnel variable attack angle force measurement test;
FIG. 4 is a schematic view of a force measurement test of a rotation center at different positions of a model in a wind tunnel variable attack angle force measurement test;
FIG. 5 is a schematic view of a downwind direction continuous force measurement test in a wind tunnel variable angle of attack force measurement test;
FIG. 6 is a schematic diagram of a vertical airflow direction continuous force measurement test in a wind tunnel variable angle of attack force measurement test;
FIG. 7 is a comparison of different statistical results of the error Δ CA of the axial force coefficient CA;
FIG. 8 is a comparison of different statistical results of the error Δ CN of the normal force coefficient CN;
FIG. 9 is a comparison of the different statistics of the error Δ CMz for the pitch moment coefficient CMz;
FIG. 10 is a curve of the axial force coefficient CA obtained from a continuous force measurement test in the down-stream direction;
FIG. 11 is a normal force coefficient CN curve obtained by a continuous force measurement test in the down-stream direction;
FIG. 12 is a plot of the pitching moment coefficient CMz obtained from a downwind continuous force test.
In the figure, 1, a wind tunnel spray pipe 2, a model 3, a diffuser 4, an angle of attack mechanism rotation center 5 and a test section are arranged;
s1, an upstream position S2 along the airflow direction, a middle position S3 along the airflow direction and a downstream position along the airflow direction;
v1. vertical airflow direction deviates from the upper position of the central axis V2. vertical airflow direction central axis position V3. deviates from the lower position of the central axis vertical airflow direction;
r1, the rotation center is at the tail position of the model R2, the rotation center is at the middle position of the model R3, and the rotation center is at the head position of the model;
l, model length H, length delta L of model strut II, length difference of model strut L, length delta L of model strut II, and length delta L of model strut L, wherein the height SL. of the cross section projection of the spray pipe when the model is located at the maximum attack angle is in the continuous change position range VL. along the airflow direction and in the continuous change position range LL. perpendicular to the airflow direction.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
The test method for acquiring the influence of the flow field nonuniformity on the model aerodynamic characteristics comprises the following steps:
a. as shown in fig. 1, a model 2 is installed between a wind tunnel nozzle 1 and a diffuser 3 of a test section 5 and fixed on an attack angle mechanism of the wind tunnel test section, the center of the model 2 is located at a rotation center 4 of the attack angle mechanism, the length of the model 2 is L, and the height of the projection on the nozzle section when the model 2 is located at the maximum attack angle is H;
b. defining the horizontal position of the model 2 in the step a as a downwind direction middle position S2, the forward position along the X-axis direction of the wind tunnel as a downwind direction upstream position S1, the backward position along the X-axis direction of the wind tunnel as a downwind direction downstream position S3, wherein the distances among S1, S2 and S3 are equal, the distance between S1 and S3 is a downwind direction continuous change position range SL, and SL is more than L; as shown in fig. 2, the model 2 is moved to positions S1, S2 and S3 respectively, the attack angle of the model 2 is adjusted to zero, and a wind tunnel variable attack angle force measurement test is performed;
c. defining the vertical position of the model 2 in the step a as a central axis position V2 in the vertical airflow direction, the upward position in the Y-axis direction of the wind tunnel as a position V1 above the central axis in the vertical airflow direction, the downward position in the Y-axis direction of the wind tunnel as a position V3 below the central axis in the vertical airflow direction, wherein the distances among V1, V2 and V3 are equal, the distance between V1 and V3 is a position range VL continuously changing in the vertical airflow direction, and VL is greater than H; as shown in fig. 3, the model 2 is moved to the positions of V1, V2 and V3 respectively, the attack angle of the model 2 is adjusted to zero, and the wind tunnel variable attack angle force measurement test is carried out;
d. defining the position of the model 2 in the step a as a rotation center, wherein the position in the model is R2, and the length of a corresponding model support rod II is LL; processing a model supporting rod I, wherein the length of the model supporting rod I is LL + delta L, replacing a model supporting rod II with the model supporting rod I, and enabling the rotation center of the model 2 to be at the tail position R1 of the model; processing a model supporting rod III, wherein the length of the model supporting rod III is LL-delta L, replacing the model supporting rod I with the model supporting rod III, and the rotating center of the model 2 is at the head position R3 of the model; as shown in fig. 4, at the positions of R1, R2, and R3, the angle of attack of model 2 is zeroed, and a wind tunnel variable angle of attack force measurement test is performed;
e. the positions S2, V2 and R2 in the steps b-d are the same, 3 times of six-component force measurement test results f1A, N, Z, Mx, My and Mz at the same position are obtained, and 3 times of f1 are simply called multiple times of measurement; the positions of S1, S3, V1, V3, R1 and R3 are different, the dynamometry test results of the other six positions f2A, N, Z, Mx, My, Mz, f3A, N, Z, Mx, My, Mz, f4A, N, Z, Mx, My, Mz, f5A, N, Z, Mx, My, Mz, f6A, N, Z, Mx, My, Mz, f7A, N, Z, Mx, My and Mz are respectively obtained, and f 1-f 7 are simply called multi-position measurement; wherein, A, N, Z, Mx, My and Mz are respectively the axial force, normal force, lateral force, rolling moment, yawing moment and pitching moment of the model 2;
respectively calculating the root mean square error sigma of each aerodynamic coefficient measured for multiple times under each attack angleA、σN、σZ、σMx、σMy、σMzAnd uncertainty UA、UN、UZ、UMx、UMy、UMz；
Respectively calculating the maximum deviation delta of each aerodynamic coefficient measured at multiple positions under each attack angleA、δN、δZ、δMx、δMy、δMz；
f. Examining the maximum deviation δ of the aerodynamic coefficients of the multi-position measurement of step eA、δN、δZ、δMx、δMy、δMzSearching for an attack angle corresponding to the maximum deviation, adjusting the attack angle of the model 2 to be under the attack angle as shown in fig. 5, and continuously moving the SL to measure the force along the airflow direction through the wind tunnel test section attack angle mechanism along S1, S2 and S3 to obtain a test result of continuous force measurement along the airflow direction; as shown in fig. 6, continuously moving VL along the vertical airflow direction in V1, V2 and V3 for VL force measurement by the wind tunnel test section attack angle mechanism, to obtain a vertical airflow direction continuous force measurement test result;
g. and (e) respectively calculating error bands of A, N, Z, Mx, My and Mz of the model 2 by combining the test results of the step (e) and the step (f) so as to evaluate the influence of the flow field nonuniformity on the A, N, Z, Mx, My and Mz of the model 2.
Further, the wind tunnel variable attack angle force measurement test adopts a step variable attack angle mode or a continuous variable attack angle mode.
Further, the downwind direction middle position is unchanged, and S1, S2 and S3 are expanded to S1 and S2 … … Sm according to the calculation requirement, wherein m is larger than 3.
Further, the positions of the central axes in the vertical airflow direction are unchanged, V1, V2 and V3 are expanded to V1 and V2 … … Vn according to the calculation requirement, and n is larger than 3.
Further, the rotation center is unchanged at the middle position of the model, R1, R2 and R3 are expanded to R1 and R2 … … Rk according to the calculation requirement, and k is larger than 3.
Further, the test method selects one of the steps b, c and d, and correspondingly completes research on influence of the non-uniformity of the flow field in the forward direction on the aerodynamic characteristics of the model, research on influence of the non-uniformity of the flow field in the vertical direction on the aerodynamic characteristics of the model and research on influence of the non-uniformity of the flow field at different rotation center positions on the aerodynamic characteristics of the model.
Further, the test method selects any two of the steps b, c and d, and correspondingly completes the research on the influence of the flow field nonuniformity of any two factors in the downstream direction, the vertical direction flow field and the rotation center position on the model aerodynamic characteristics.
Example 1
The mold 2 of this embodiment is a vent moldModel, the total length of the model 2 after the reduction is 0.932m, the test Mach number is 4, and the total pressure P00.5MPa total temperature T0＝280K。
As can be seen from fig. 7 to 12, the absolute magnitude of the mean square deviation δ of the aerodynamic force/moment coefficient 2 times obtained by the test is small and is much smaller than the initial uncertainty U and the maximum deviation δ of the multi-position test. For the aerodynamic coefficient CA, the maximum deviation delta of the multi-position test is slightly smaller than the initial uncertainty U; for the aerodynamic coefficient CN, the maximum deviation of the multi-position test is equivalent to the initial uncertainty; whereas for the aerodynamic moment coefficient CMz, the multi-position trial maximum deviation δ is significantly greater than the initial uncertainty U. The flow field of the hypersonic wind tunnel is non-uniform, sensed flow field conditions are different when the model 2 is located at different positions, the difference of the flow field can cause small difference of pressure distribution when the model is located at different positions of the wind tunnel, namely, the pressure center position is changed, the pressure center of the model is close to the mass center, and when the pressure distribution of the model is slightly different, the pressure center of the model can have small movement amount, so that relatively large deviation is formed on the pitching moment CMz. The results of two multi-position tests (repeated tests are carried out for a plurality of times when the model is positioned at different positions of the test section in a step change model attack angle mode, and continuous scanning force measurement tests are carried out on the model at different positions of the test section in a fixed model attack angle mode) are well matched.
In short, 2 times the root mean square error σ is much smaller than the uncertainty U obtained by the evaluation; the uncertainty U of the aerodynamic force X, Y, Z coefficient is basically consistent with the maximum deviation delta of the multi-position test; the uncertainty U of the coefficients of the aerodynamic moments Mx, My and Mz is smaller than the maximum deviation delta of the multi-position test. Therefore, the influence of the flow field nonuniformity on the model moment characteristic is obvious, and the difference of test results of different positions in part states is far greater than the uncertainty of data obtained by a repeatability test.
Claims (7)
1. A test method for acquiring the influence of flow field nonuniformity on model aerodynamic characteristics is characterized by comprising the following steps:
a. the method comprises the following steps that a model (2) is installed between a wind tunnel spray pipe (1) and a diffuser (3) of a test section (5) and fixed on an attack angle mechanism of the wind tunnel test section, the center of the model (2) is located at a rotation center (4) of the attack angle mechanism, the length of the model (2) is L, and the height of the model (2) projected on the section of the spray pipe when located at the maximum attack angle is H;
b. defining the horizontal position of the model (2) in the step a as a downwind direction middle position S2, a forward position along the X-axis direction of the wind tunnel as a downwind direction upstream position S1, a backward position along the X-axis direction of the wind tunnel as a downwind direction downstream position S3, wherein the distances among S1, S2 and S3 are equal, the distance between S1 and S3 is a downwind direction continuous change position range SL, and SL is larger than L; respectively moving the model (2) to S1, S2 and S3 positions, adjusting the attack angle of the model (2) to zero, and performing a wind tunnel variable attack angle force measurement test;
c. defining the vertical direction position of the model (2) in the step a as a central axis position V2 in the vertical airflow direction, the upward position in the Y-axis direction of the wind tunnel as a position V1 above the central axis in the vertical airflow direction, the downward position in the Y-axis direction of the wind tunnel as a position V3 below the central axis in the vertical airflow direction, wherein the distances among V1, V2 and V3 are equal, the distance between V1 and V3 is a position range VL continuously changing in the vertical airflow direction, and VL is greater than H; respectively moving the model (2) to the positions of V1, V2 and V3, adjusting the attack angle of the model (2) to zero, and performing a wind tunnel variable attack angle force measurement test;
d. defining the position of the model (2) in the step a as a rotation center, wherein the position in the model is R2, and the length of a corresponding model support rod II is LL; processing a model supporting rod I, wherein the length of the model supporting rod I is LL + delta L, replacing a model supporting rod II with the model supporting rod I, and enabling the rotation center of the model (2) to be at the tail position R1 of the model; processing a model supporting rod III, wherein the length of the model supporting rod III is LL-delta L, the model supporting rod I is replaced by the model supporting rod III, and the rotating center of the model (2) is at the head position R3 of the model; adjusting the attack angle of the model (2) to zero at the positions of R1, R2 and R3, and carrying out a wind tunnel variable attack angle force measurement test;
e. the positions S2, V2 and R2 in the steps b-d are the same, 3 times of six-component force measurement test results f1(A, N, Z, Mx, My and Mz) of the same position are obtained, and 3 times of f1 are simply called multiple times of measurement; the positions of S1, S3, V1, V3, R1 and R3 are different, and the dynamometry test results f2(A, N, Z, Mx, My and Mz), f3(A, N, Z, Mx, My and Mz), f4(A, N, Z, Mx, My and Mz), f5(A, N, Z, Mx, My and Mz), f6(A, N, Z, Mx, My and Mz) and f7(A, N, Z, Mx, My and Mz) of the other six positions are respectively obtained, and f 1-f 7 are simply called multi-position measurement; wherein A, N, Z, Mx, My and Mz are respectively the axial force, normal force, lateral force, rolling moment, yawing moment and pitching moment of the model (2);
respectively calculating the root mean square error sigma of each aerodynamic coefficient measured for multiple times under each attack angleA、σN、σZ、σMx、σMy、σMzAnd uncertainty UA、UN、UZ、UMx、UMy、UMz；
Respectively calculating the maximum deviation delta of each aerodynamic coefficient measured at multiple positions under each attack angleA、δN、δZ、δMx、δMy、δMz；
f. Examining the maximum deviation δ of the aerodynamic coefficients of the multi-position measurement of step eA、δN、δZ、δMx、δMy、δMzSearching an attack angle corresponding to the maximum deviation, adjusting the attack angle of the model (2) to be under the attack angle, and continuously moving the SL to measure the force along the airflow direction through the wind tunnel test section attack angle mechanism along S1, S2 and S3 to obtain a continuous force measurement test result along the airflow direction; continuously moving the VL to measure the force along the vertical airflow directions V1, V2 and V3 by the wind tunnel test section attack angle mechanism along the airflow direction to obtain a test result of continuously measuring the force along the vertical airflow direction;
g. and (e) respectively calculating error bands of A, N, Z, Mx, My and Mz of the model (2) by combining the test results of the step (e) and the step (f) so as to evaluate the influence of the flow field nonuniformity on the A, N, Z, Mx, My and Mz of the model (2).
2. The test method for obtaining the influence of the flow field nonuniformity on the aerodynamic characteristics of the model according to claim 1, wherein a step attack angle changing mode or a continuous attack angle changing mode is adopted in the wind tunnel attack angle changing force measurement test.
3. The experimental method for obtaining the influence of the flow field nonuniformity on the model aerodynamic characteristics as claimed in claim 1, wherein the streamwise middle position is unchanged, and S1, S2 and S3 are expanded to S1 and S2 … … Sm, and m is greater than 3 according to the calculation requirements.
4. The experimental method for obtaining the influence of the flow field nonuniformity on the model aerodynamic characteristics as claimed in claim 1, wherein the positions of the central axes in the vertical airflow direction are unchanged, and V1, V2 and V3 are expanded to V1 and V2 … … Vn according to the calculation requirements, wherein n is greater than 3.
5. The experimental method for obtaining the influence of the flow field nonuniformity on the model aerodynamic characteristics as claimed in claim 1, wherein the rotation center is unchanged at the middle position of the model, and R1, R2 and R3 are expanded to R1 and R2 … … Rk according to the calculation requirements, wherein k is greater than 3.
6. The test method for obtaining the influence of the flow field nonuniformity on the model aerodynamic characteristics according to claim 1, wherein one of the steps b, c and d is selected to correspondingly complete the study on the influence of the flow field nonuniformity in the forward direction on the model aerodynamic characteristics, the study on the influence of the flow field nonuniformity in the vertical direction on the model aerodynamic characteristics and the study on the influence of the flow field nonuniformity in different rotation center positions on the model aerodynamic characteristics.
7. The test method for acquiring the influence of the flow field nonuniformity on the model aerodynamic characteristics according to claim 1, wherein any two of the steps b, c and d are selected to correspondingly complete the research on the influence of the flow field nonuniformity on the model aerodynamic characteristics of any two factors of the flow field in the downstream direction, the vertical direction and the rotation center position.
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