Mach number sensitivity analysis method for supersonic cavity flow

A technique of sensitivity analysis and Mach number, applied in the field of experimental fluid mechanics, which can solve problems such as inability to continuously change

Active Publication Date: 2017-05-10
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
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Problems solved by technology

However, in the supersonic wind tunnel test, parameters such as Reynolds number and model attitude can be continuously changed, but since the Mach number is determined by the nozzle profile, it cannot be continuously changed like subsonic speed

Method used

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  • Mach number sensitivity analysis method for supersonic cavity flow
  • Mach number sensitivity analysis method for supersonic cavity flow
  • Mach number sensitivity analysis method for supersonic cavity flow

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Embodiment Construction

[0029] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0030] Any feature disclosed in this specification (including any appended claims, abstract and drawings), unless expressly stated otherwise, may be replaced by alternative features which are equivalent or serve a similar purpose. That is, unless expressly stated otherwise, each feature is one example only of a series of equivalent or similar features.

[0031] This program includes the following steps:

[0032] a. Make the initial angle of attack of the plate be 0 degrees, set the angle of attack to increase by Δα for each step, and measure 3 steps in turn;

[0033] b. Install a total pressure measuring rake and a static pressure measuring hole at the front edge of the cavity to measure and obtain the Mach number at the cavity entrance at different angles of attack;

[0034] c. Control the ...

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Abstract

The invention provides a Mach number sensitivity analysis method for supersonic cavity flow, and the method comprises the steps: forming expansion waves at different angles at the front edge of a flat plate through adjusting the attack angle of a model, wherein the Mach number will rise after a gas flow passes through the expansion waves; and carrying out the sensitivity analysis of the Mach number through the comparison of the pulsating pressure data before and after the change of the attack angle. The method can achieve the Mach number sensitivity analysis under the supersonic conditions, and solves a key problem of a wind tunnel sensitivity analysis test.

Description

technical field [0001] The invention relates to the field of experimental fluid mechanics, in particular to a Mach number sensitivity analysis method suitable for supersonic cavity flow. Background technique [0002] With the independent innovation and development of my country's weapons and equipment, more and more unconventional aerodynamic layouts have been applied to advanced fighters. However, while the new aerodynamic layout scheme improves the agility and stealth effect of the aircraft, it also brings many new problems, such as vortex breakage during flight at high angles of attack, resulting in buffeting of the vertical tail, and the severe pressure generated when the internal weapon compartment is opened. pulsation etc. One of the consequences of these problems is that under the action of severe dynamic loads, cracks on the skin of the vertical tail and the thin-walled structure of the embedded weapon compartment accelerate to form and expand, which seriously threa...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 刘俊杨党国王显圣张征宇刘刚熊能刘昕郑向金何成军陈植
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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