A method for measuring the transition process characteristics of aircraft boundary layer in hypersonic flight test

Abstract

The invention provides a method for measuring the transition process characteristics of the aircraft boundary layer in a hypersonic flight test, the steps are as follows: 1) simulate and calculate the flow field around the aircraft to obtain the surface flow characteristics of the aircraft; 2) determine that the surface of the aircraft is suitable for boundary layer The area measured during the transition process; 3) Simulate and calculate the surface heat flow and structural thermal response of the aircraft, obtain the calculation results of the aircraft surface heat flow and structural temperature along the entire flight profile, and select the heat flow sensor and temperature sensor; 4) Evaluation Feasibility of sensor installation in the transition measurement area; 5) According to the analysis results of the surface flow and transition characteristics of the aircraft, determine the sensor position, the number of sensor measuring points and the distance between sensor measuring points; 6) Determine the Analyze the flight test data obtained by the transition process measurement plan, and draw the curve of surface heat flow or temperature change along the flow direction; 7) analyze the change law of the heat flow or temperature change curve along the flow direction, and determine the characteristics of the boundary layer transition process .

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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