Wind tunnel test method for researching influence of transition on aerodynamic characteristics of hypersonic aircraft

Abstract

The invention discloses a wind tunnel test method for researching influence of transition on aerodynamic characteristics of a hypersonic aircraft. The test model used in the method is a non-metallic polytetrafluoroethylene test model, the transition state of the hypersonic aircraft is simulated in a natural transition mode or a forced transition mode, the aerodynamic force of the test model is measured by adopting a conventional strain balance, the surface thermogram of the test model is obtained by adopting a thermal infrared imager, and the transition position of the test model is identified. And the aerodynamic force of the test model and the surface heat map of the test model are combined to research the influence of transition on the aerodynamic characteristics of the hypersonic aircraft. According to the wind tunnel test method, aerodynamic force data and the transition position of the test model can be measured at the same time, and a reference basis is provided for accurately analyzing the influence of transition on the aerodynamic characteristics of the test model.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a wind tunnel test method for studying the influence of transition on the aerodynamic characteristics of hypersonic aircraft. Background technique [0002] At present, hypersonic technology is regarded as a disruptive technology, and the development of hypersonic vehicles is a research hotspot. A large number of engineering practices have proved that the boundary layer transition problem has become an important problem restricting the further development of hypersonic vehicles. This is because the boundary layer transition will lead to a substantial increase in the resistance and wall heat flow of hypersonic vehicles, serious wall ablation, and difficulty in flight attitude control. The increase will not only affect the aerodynamic force and aerodynamic heat of the aircraft, but also have a significant impact on flight stability and thermal protec...

AI Technical Summary

Problems solved by technology

Since the surface flow state determination test of the test model and the aerodynamic influence test need to be carried out separately in two blowing tests, the above-mentioned transition research test method is an indirect method, which has the following disadvantages: First, it will introduce additional errors, and the transition is very sensitive to external environmental factors. Sensitive, when the aerodynamic test is carried out, the transition position of the test model may have changed. At this time, the transition state and transition position of the test model cannot completely correspond to the surface flow state determination test; the second is that the test preparation time is long and the test steps Complicated and expensive

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