Method for designing ultrasonic-speed turning flow channel

Abstract

The invention provides a method for designing an ultrasonic-speed turning flow channel. The method comprises the following steps of: determining the inlet boundary of the wall surface curve of the ultrasonic-speed flow channel according to the geometric constraint of the design structure of the ultrasonic-speed flow channel; determining the one-sided wall surface curve of the ultrasonic-speed flow channel according to the geometric constraint of the design structure of the ultrasonic-speed flow channel; determining the opposite-side wall surface curve which corresponds to the one-sided wall surface curve by adopting the method of characteristics; and determining the wall surface curve of the ultrasonic-speed flow channel according to the parameters of an outlet flow field. Due to the adoption of the method, the shock-free ultrasonic-speed flow channel of the whole flow field can be obtained, and a better flow field environment can be provided for the aerodynamic and structural design of an ultrasonic-speed wind tunnel, an ultrasonic-speed ejector and an ultrasonic-speed aircraft.

Description

technical field [0001] The invention relates to the field of aerodynamic design, in particular to a method for designing a supersonic turning channel. Background technique [0002] The change of supersonic flow direction is bound to be accompanied by Mach wave radiation. If the supersonic flow channel turns suddenly or the curvature of the turn is too large, there will be an obvious shock wave structure. The shock wave structure will not only bring the total pressure loss of the flow, but also interact with the wall boundary layer. The effect forms a complex separation zone structure, which greatly deteriorates the aerodynamic performance of the supersonic flow channel. [0003] The document "Gas Dynamics" (Tong Binggang, Higher Education Press, 1989) discloses a supersonic nozzle design method, the steps are as follows: [0004] 1. According to the requirements of shrinkage ratio and length-to-diameter ratio, design the subsonic section curve; [0005] 2. Determine the su...

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Problems solved by technology

[0008] In this method, the subsonic region must be designed, and it is generally a two-dimensional or axisymmetric structure. If the flow needs to turn, there will be concentrated expansion and compression waves. If the curvature is too large, shock waves will be generated, and the internal flow field parameters cannot be controlled. , which adversely affects the quality of the supersonic flow field. In addition, there is no design method for the supersonic shock-free turning channel in the prior art.

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