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Wind tunnel test tail support interference correction method and application thereof

A wind tunnel test and interference correction technology, applied in the field of wind tunnel test, can solve the problems such as the inability to carry out the tail support interference correction test, the large size of the abdominal support system, and the jitter of the aircraft model, so as to achieve a stable blowing test process and a test angle of attack range. The effect of large and secondary interference is small

Active Publication Date: 2016-06-08
AERODYNAMICS NAT KEY LAB
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Problems solved by technology

[0005] The purpose of the present invention is to: In the high-speed wind tunnel aircraft model tail support interference correction test, the model belly support method is adopted. The size of the belly support system is large, which will cause secondary interference, and the test angle of attack is relatively small, which is easy to cause aircraft The model shakes, which leads to the problem that the tail support interference correction test cannot be carried out, and provides a tail support interference correction method for wind tunnel tests and its application

Method used

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  • Wind tunnel test tail support interference correction method and application thereof
  • Wind tunnel test tail support interference correction method and application thereof
  • Wind tunnel test tail support interference correction method and application thereof

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Embodiment 1

[0032] The test wind tunnel of this embodiment is a 2.4m×2.4m transonic wind tunnel, the test model is a large aircraft model with a scale ratio of 1:22, the test conditions are Mach number 0.4, 0.6, 0.8, and the test angle of attack is -4°~ 14°, it is required to obtain the aerodynamic data of the large aircraft model after correcting the support interference.

[0033] Under the condition of 2.4m×2.4m transonic wind tunnel and incoming flow Mach number 0.4, the corresponding measurement is carried out. The specific operation process is as follows.

[0034] Step 1. Design a set of test models. The test model includes a model fuselage, a real rear body of the model, and a damaged rear body of the tail support. The real rear body of the model is assembled on the tail of the model fuselage to form a real model, and the tail support damaged rear body is assembled on the tail of the model fuselage to form a rear body failure test model.

[0035] Step two, such as figure 1 As show...

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Abstract

The invention discloses a wind tunnel test tail support interference correction method and an application thereof. The wind tunnel test tail support interference correction method aims to settle a problem of incapability of performing tail support interference correction tests caused by factors secondary interference, relatively small test angle-of-attack and easy plane model vibration, wherein the factors occur because of a model belly supporting manner and relatively large dimension of a belly supporting system. According to the wind tunnel test tail support interference correction method, a stripe suspension supporting mechanism is used as an auxiliary support; and through simulating a testing state with a tail support system and a testing state without the tail support system, support interference correction amount of the tail support system to a tested sample is acquired, thereby acquiring a corrected testing result which comprises a model aerodynamic force, torque, etc. The wind tunnel test tail support interference correction method realizes the following advantages in correction: small secondary interference, large test angle-of-attack range, small tested model vibration amplitude, higher accuracy of obtained correction method, high use value and high economic benefit.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a wind tunnel test tail support interference correction method and its application. The invention can correct the interference of the tail support in the wind tunnel test, is especially suitable for the correction of the interference of the tail support of the high-speed wind tunnel, and has good application prospect. Background technique [0002] Wind tunnel test is the main method to study gas flow and its interaction with the model, and the aerodynamic characteristics of aircraft are mainly obtained through wind tunnel test. During the high-speed wind tunnel test, the aircraft model is fixed in the wind tunnel test section through the support device, the incoming wind from the wind tunnel acts on the aircraft model, and the aerodynamic characteristics of the aircraft model are obtained through a special balance placed inside the aircraft model. Most of the high-spee...

Claims

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Application Information

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IPC IPC(8): G01M9/00G01M9/06
CPCG01M9/00G01M9/06
Inventor 陈德华许新刘大伟尹陆平彭超师建元饶正周李强史晓军
Owner AERODYNAMICS NAT KEY LAB
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