Aerothermodynamics of Hypersonic Small Nose Cone with Local Rarefied Gas Effects

CHINESE JOURNAL OF COMPUTATIONAL PHYSICS ›› 2010, Vol. 27 ›› Issue (1): 59-64.

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Aerothermodynamics of Hypersonic Small Nose Cone with Local Rarefied Gas Effects

WANG Zhihui, BAO Lin

Graduate University of Chinese Academy of Sciences, Beijing 100049, China

Received:2008-08-18 Revised:2008-12-16 Online:2010-01-25 Published:2010-01-25

Abstract

Abstract: A small nose sphere-cone is taken as vehicles leading-edge,and kinetic-theory based DSMC method is used to simulate aerothermal environment of hypersonic sphere-cone with different nose radii.Stagnation point heat fluxes calculated by DSMC are compared with that by Fay-Riddell formulae and other theories.Aerothermodynamic characteristics of hypersonic small nose cone with local rarefied gas effect are studied.It is found that the modified Cheng's parameter is a credible criterion in predicting rarefied gas effects at stagnation point of sharp leading-edges.

Key words: rarefied gas effect, DSMC, sharp leading-edge, hypersonic

CLC Number:

O356
O354.4

WANG Zhihui, BAO Lin. Aerothermodynamics of Hypersonic Small Nose Cone with Local Rarefied Gas Effects[J]. CHINESE JOURNAL OF COMPUTATIONAL PHYSICS, 2010, 27(1): 59-64.

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Aerothermodynamics of Hypersonic Small Nose Cone with Local Rarefied Gas Effects

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