Design method for wide-speed-range waverider aircraft with equal shock wave flow field and variable mach number

Abstract

The invention discloses a design method for a wide-speed-range waverider aircraft with an equal shock wave flow field and a variable mach number and relates to the technical field of aerodynamic configuration design for hypersonic aircrafts. The design method aims at the hypersonic aircrafts and the speed range Ma is greater than or equal to 5. The design method is based on a specific shock wave flow field to obtain object face angles on conditions corresponding to different mach numbers, and a trailing edge line of the waverider aircraft with the variable mach number can be further obtained by adoption of a streamline tracing method. Based on a simplified cone-derived wave rider, a leading edge line of the waverider aircraft with the variable mach number can be determined based on the design criteria for a steady shock wave flow field after an ascender line of the wave rider is determined; and then by adoption of the streamline tracing method, trailing edge line of the waverider aircraft with the variable mach number can be obtained on the basis of a variable conical surface. The upper surface and the lower surface of the waverider aircraft can be obtained by connecting all flow lines into an integrated surface after the ascender line, the leading edge line and the trailing edge line are determined, and therefore, design for the waverider aircraft is completed.

Description

technical field [0001] The present invention relates to the technical field of aerodynamic shape design of hypersonic aircraft, in particular to a design method of constant shock wave flow field-variable Mach number wide speed range waveriding aircraft, and the target object is hypersonic aircraft, and the speed domain range is Ma≥ 5. Background technique [0002] With the rapid development of aerospace technology, the design of aircraft will develop in the direction of wider speed range and wider airspace, especially the aerodynamic shape design of hypersonic aircraft has become one of the research hotspots in this field. When a conventional shape aircraft flies under hypersonic conditions, it will encounter a "lift-to-drag ratio barrier" due to the limitation of its shape (see KuchemannD. The Aerodynamic Design of Aircraft[M].London: Pergamon Press, 1978). The design of wave aircraft can solve this problem well. Under hypersonic conditions, the waverider can well compres...

AI Technical Summary

Problems solved by technology

Using the "serial" method, the design of the connecting section is the focus of the design, which requires artificial splicing and combination, and the "repeatability" is poor

The "parallel connection" method is mainly for the design and modification of the leading edge line. In the design process, a large number of human intervention and operations are required to splice and combine the leading edge lines obtained under different design Mach number conditions. , and then get the leading edge of wide-speed aircraft suitable for wide-speed flight conditions, with higher human participation and poor "reproducibility"

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