Method for measuring transition process characteristics of aircraft boundary layer in hypersonic flight test

Abstract

The invention provides a method for measuring the transition process characteristics of an aircraft boundary layer in a hypersonic flight test. The method comprises the following steps of 1), carryingout the simulation calculation of a flow field around an aircraft, and obtaining the surface flow characteristics of the aircraft, 2) determining an area suitable for boundary layer transition process measurement on the surface of the aircraft,3) carrying out simulation calculation on the surface heat flow and the structural thermal response of the aircraft, obtaining the calculation results of the surface heat flow and the structural temperature of the aircraft along the whole flight profile, and carrying out model selection on a heat flow sensor and a temperature sensor,4) evaluating feasibility of sensor installation in the transition measurement area, 5) determining the positions of sensors, the number of sensor measuring points and the distance between the sensor measuring points according to the analysis result of the surface flow and transition characteristics of the aircraft,6) analyzing flight test data obtained by the transition process measurement schemes determined in thesteps 1)-5), and drawing a curve of surface heat flow or temperature changing along the flow direction, and 7) analyzing the change rule of the curve of heat flow or temperature changing along the flow direction, and determining the transition process characteristics of the boundary layer.

Description

technical field [0001] The invention relates to a method for measuring transition process characteristics of an aircraft boundary layer in a hypersonic flight test, and belongs to the field of aerodynamic / thermal research of a hypersonic aircraft. Background technique [0002] A hypersonic vehicle spans a wide flight airspace and speed domain. As the Reynolds number of the incoming flow increases, the flow on the surface of the vehicle will undergo a boundary layer transition. Since the wall friction coefficient / heat transfer coefficient of the laminar boundary layer and the turbulent boundary layer are significantly different, the boundary layer transition will have a significant impact on the aerodynamic force on the aircraft surface, especially the aerodynamic heat distribution. During the propulsion process of the transition, there are obvious changes in the aerodynamic and control characteristics of the aircraft. After the transition occurs, the surface heat flow increa...

AI Technical Summary

Problems solved by technology

[0004] The technical solution problem of the present invention is: to overcome the deficiencies of the prior art, aiming at the problem that it is difficult to obtain information on the transition process of the boundary layer in the current hypersonic flight test, it provides a method that can measure the transition process of the boundary layer in the hypersonic flight test. The information method overcomes the problem that the current technical means can only obtain a small amount of single boundary layer transition information, and can obtain information including the boundary layer transition start point, transition transition zone and transition end point in hypersonic flight tests. The complete transition process information provides more abundant experimental data for the study of boundary layer transition theory and prediction methods

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