Design method of supersonic flow field based on characteristic line tracing

Abstract

The invention discloses a supersonic flow field design method based on characteristic line tracing. The supersonic flow field design method includes the steps that mach number distribution on a certain flow line in a supersonic flow field is set, initial flow channel configuration is given, and the flow field in the initial flow channel configuration is calculated; one point on the wall face is selected as a starting point, a characteristic line is traced from the starting point in the flow field obtained through calculation and intersects with the preset flow line, the actual mach number of the intersecting point is obtained through interpolation and compared with the ideal mach number, and according to the residual error correction concept, the wall face configuration is adjusted continuously to reduce the difference value between the actual mach number of the intersecting point and the ideal mach number; when the difference value reaches a preset threshold value, the upstream flow channel configuration of the starting point on the wall face is fixed, and stepping to the next wall face point is executed according to the preset step length; the steps are repeated until the preset supersonic flow field is obtained. The method can be universally used for designing two-dimensional and three-dimensional supersonic flow channels, under the viscose flow design conditions, a traditional boundary layer correction technology is not needed, internal flow of the designed flow channels is even, and the flow field is high in quality.

Description

technical field [0001] The invention relates to the field of aerodynamic design, in particular to a method for designing a supersonic flow field based on characteristic line tracing. Background technique [0002] The flow field design of hypersonic vehicle intake and exhaust systems and corresponding experimental equipment is a hot and difficult issue in current research. The quality of the designed flow field directly affects the combustion efficiency of the engine and thus the overall performance of the aircraft. [0003] There are many existing supersonic flow field design methods, the most typical of which are the method of characteristic lines (MOC, Method of Characteristics) and the streamline tracing method. [0004] The steps of the characteristic line method are as follows: [0005] 1), given the Mach number distribution or velocity distribution on the centerline of the flow channel and the corresponding boundary conditions; [0006] 2), assuming that the flow is ...

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Problems solved by technology

[0013] The invention provides a supersonic flow field design method based on characteristic line tracing, starting from the basic characteristics of the flow, to solve the problem that the existing supersonic flow field design requires boundary layer correction to introduce errors or the shape of the transition interface is complex and difficult to process, or the method is limited to a certain Technical problems of a class of working conditions

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