高超声速内收缩进气道分步优化设计方法

doi:10.7527/S1000-6893.2015.0095

Abstract

Abstract:

Hypersonic inward turning inlet is optimized by a multistage method of separating the base flow and lip shape. Multi-objective optimization is imposed on the base flow with the target of minimizing the flow non-uniformity after the reflected shock and maximizing the total pressure recovery. The flow field has been solved by the method of characteristic (MOC) integrated with the Tayler-Maccoll equations. Base flow optimization obtains a dual-infection point internal cone's element. Inlet lip shape is optimized by the target of minimizing the inviscid drag obtained by streamline integral method (SIM) and a semi-oval two-dimensional lip shape is obtained. Compared with the traditional straight element base flow, dual-infection point internal cone flow's non-uniformity is decreased by about 40% and the total pressure loss is decreased by 35%, and thus the overall performance is enhanced significantly. Semi-oval inlet's inviscid drag per unit mass flow is decreased by 6% compared with the circle lip shape inlet at the design point, and its good compress characteristics and aerodynamic efficiency can partially get over the inlet system's adverse influence on the aerodynamic performance of vehicle. Research proves the design method of hypersonic inward turning inlet proposed in this paper is efficient and functional.

Key words: hypersonic, inward turning inlet, optimization design, streamlines tracing, Navier-Stokes equation, numerical simulation

CLC Number:

V211.48

WANG Jifei, CAI Jinsheng, DUAN Yanhui. Multistage optimization design method of hypersonic inward turning inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(12): 3759-3773.

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Multistage optimization design method of hypersonic inward turning inlet

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