A correction method for the effect of rear body distortion on lateral heading aerodynamic characteristics of high-speed wind tunnel model

A kind of aerodynamic characteristics, high-speed wind tunnel technology, applied in the field of wind tunnel test, can solve the problems of misleading flight control system design, influence correction, lack of horizontal and vertical aerodynamic characteristics, etc.

Active Publication Date: 2017-09-01
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If the test data before the correction of the distortion effect is directly used in the design of the aircraft, it will mislead the design of the flight control system, which may cause very serious consequences and even crash the aircraft.
At present, in high-speed wind tunnel tests at home and abroad, wingtip double supports, strip suspension supports and traditional blade supports are generally used to correct the longitudinal aerodynamic characteristics of the rear body distortion of the test model. Ability to correct

Method used

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  • A correction method for the effect of rear body distortion on lateral heading aerodynamic characteristics of high-speed wind tunnel model
  • A correction method for the effect of rear body distortion on lateral heading aerodynamic characteristics of high-speed wind tunnel model
  • A correction method for the effect of rear body distortion on lateral heading aerodynamic characteristics of high-speed wind tunnel model

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0073] The state of body effect correction after distortion is: pre-bias sideslip angle βM=4°, test Mach number M=0.65, attack angle sequence α=-2°, 0°, 2°, 4°, 6°, 8°.

[0074] The specific implementation steps are as follows:

[0075] a. Design and process a set of high-speed wind tunnel test models, including real and distorted rear bodies, which can be freely replaced during the test. Among them, the real rear body is to simulate the complete shape of the tail without destruction or enlargement. Distorted rear body simulating the enlargement and hollowing out of the rear body of the test model during the tail support test.

[0076] b. The abdominal support rod is installed on the scimitar interface of the wind tunnel, the base blade is installed on the abdominal support rod, and the angle blade with the pre-biased sideslip angle βM=4° is installed on the base blade.

[0077] c. Through the balance connecting cone of the angle blade, the balance is installed on the belly ...

Embodiment 2

[0088] The state of body effect correction after distortion is: pre-bias sideslip angle βM=8°, test Mach number M=0.65, attack angle sequence α=-2°, 0°, 2°, 4°, 6°, 8°.

[0089] The implementation process is similar to that of Embodiment 1, but in step b, blades with an angle of βM=8° are installed. Table 2 presents the rear body effect correction amount of the lateral heading aerodynamic characteristics of test model 6 when βM=8°.

[0090] Table 2

[0091]

Embodiment 3

[0093] The status of body effect correction after distortion is: pre-bias sideslip angle βM=12°, test Mach number M=0.65, attack angle sequence α=-2°, 0°, 2°, 4°, 6°, 8°.

[0094]The implementation process is similar to Embodiment 1 and Embodiment 2, but in step b, blades with an angle of βM=12° are installed. Table 3 presents the rear body effect correction amount of the lateral heading aerodynamic characteristics of test model 6 when βM=12°.

[0095] table 3

[0096]

[0097] It can be seen that the rear body effect correction obtained by this method can correct the rear body distortion effect on the lateral heading aerodynamic data of the tail brace test at a given sideslip angle, and obtain real and reliable model aerodynamic force and moment data , which is of great significance to aircraft design. As shown in Table 4, the comparison of lateral derivatives of different rear body configurations of the test model is given, and the effect of rear body distortion on the ...

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Abstract

The invention provides a method for correcting the influence of the rear body distortion of a high-speed wind tunnel model on the aerodynamic characteristics in the transverse direction. The test model includes the real rear body and the distorted rear body model which can be replaced freely, and the test model is pre-deflected to a given sideslip angle through the blade belly support device with variable sideslip angle. The wind tunnel test is carried out on the real rear body model and the distorted rear body model under the same test conditions, and the transverse heading aerodynamic coefficient is interpolated according to the same sequence of attack angles. The lateral directional aerodynamic coefficients after interpolation of the two rear bodies are subtracted, and the difference obtained is considered to be the influence of rear body distortion on the aerodynamic characteristics of the test model, which can be used to test the effect of rear body distortion on the lateral directional aerodynamic characteristics of the test model at a given sideslip angle. Affected corrections.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a method for correcting the influence of the rear body distortion of a high-speed wind tunnel model on the aerodynamic characteristics in the transverse direction. Background technique [0002] Wind tunnel test is the main means to evaluate the aerodynamic performance of aircraft. In the high-speed wind tunnel test, the aircraft model is generally fixed in the test section with the tail support for wind tunnel tests. The shape of the connection between the tail of the test model and the support device will be damaged to a certain extent, which is harmful to the test model, especially for large aircraft and large aircraft. The aspect ratio of the UAV has a more obvious influence on the aerodynamic force and moment. [0003] Especially for large aircraft, the rear body of the fuselage shrinks at the stern, and the cavity formed by the tail support in the rear...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/06
Inventor 刘大伟陈德华李强李巍许新李永红姜明杰李聪健彭鑫何彬华
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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