Measuring point arrangement method suitable for hypersonic flight test transition research

Abstract

A measuring point arrangement method suitable for hypersonic flight test transition research is disclosed. The measuring point arrangement method is achieved through the following modes: S1, determining whether the natural transition or the forced transition is to be measured according to measurement requirements, and if the natural transition is to be measured, then going to S2; if the forced transition is to be measured, then going to S3; S2, measuring a main flow transition condition and / or a transition condition of a cross flow effect according to measurement requirements, wherein when themain flow transition condition is measured, a measuring point is arranged on a streamline of a hypersonic aircraft in the main flow direction; when the transition condition of the cross flow effect is measured, the measuring point is arranged at a position with a cross flow velocity in the lateral direction; the main flow direction is the central streamline direction of the aircraft and the streamline direction with an included angle of not more than 3 degrees with the central streamline direction; S3, arranging a rough element at a predetermined position on the aircraft, and arranging the measuring point at the downstream of the streamline where the rough element is located; and the measuring point positions realize the measurement of the physical quantity of the surface of the aircraftin the flight test process by installing sensors.

Description

technical field [0001] The invention belongs to the field of aerospace vehicle transition research. Background technique [0002] Transition refers to the process of changing the flow state from laminar flow to turbulent flow. The physical mechanism is that as the Reynolds number increases, the laminar flow becomes unstable, causing the disturbance in the flow to continue to grow, and then complex nonlinear disturbances appear, resulting in vortex flow. The fragmentation of structures and vortices eventually makes the flow evolve into a chaotic state (that is, a turbulent state). When the boundary layer transitions, the surface of the aircraft will transition from laminar heating to turbulent heating, and the surface heat flow will increase several times, resulting in a significant change in the surface thermal environment. figure 1 Given the change of the surface heat flow of the re-entry vehicle when the transition occurs, it can be seen that when the transition occurs, t...

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Problems solved by technology

[0007] The problem solved by the technology of the present invention is: in view of the lack of theoretical research on the transition of hypersonic vehicles and the fact that ground wind tunnel tests cannot meet the needs of transition research, it is necessary to measure transition data from flight tests to provide support for transition theory research and method improvement. The invention proposes a measuring point arrangement method suitable for hypersonic transition research, which can be effectively used for measuring point arrangement in transition research

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