Hypersonic Shock Interactions About a 25°/65° Sharp Double Cone | Zendy

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Hypersonic Shock Interactions About a 25°/65° Sharp Double Cone

Author(s) -

James N. Moss

Publication year - 2003

Publication title -

aip conference proceedings

Language(s) - English

Resource type - Conference proceedings

SCImago Journal Rank - 0.177

H-Index - 75

eISSN - 1551-7616

pISSN - 0094-243X

DOI - 10.1063/1.1581578

Subject(s) - hypersonic speed , mach number , wind tunnel , shock (circulatory) , sensitivity (control systems) , flow (mathematics) , expansion tunnel , mechanics , computation , focus (optics) , direct simulation monte carlo , code (set theory) , monte carlo method , computer science , aerospace engineering , physics , algorithm , optics , medicine , statistics , mathematics , set (abstract data type) , dynamic monte carlo method , electronic engineering , engineering , programming language

This paper presents the results of a numerical study of shock interactions resulting from Mach 10 air flow about a sharp double cone. Computations are made with the direct simulation Monte Carlo (DSMC) method by using two different codes: the G2 code of Bird and the DAC (DSMC Analysis Code) code of LeBeau. The flow conditions are the pretest nominal free‐stream conditions specified for the ONERA R5Ch low‐density wind tunnel. The focus is on the sensitivity of the interactions to grid resolution while providing information concerning the flow structure and surface results for the extent of separation, heating, pressure, and skin friction.

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