Comparison of Hypersonic Experiments and PNS Predictions Part I: Aerothermodynamics

Autor:	Clark H. Lewis, Bilal A. Bhutta
Rok vydání:	1991
Předmět:	Physics Hypersonic speed Turbulence Angle of attack Turbulence modeling Aerospace Engineering Laminar flow Mechanics Physics::Fluid Dynamics symbols.namesake Mach number Space and Planetary Science symbols Cebeci–Smith model Choked flow
Zdroj:	Journal of Spacecraft and Rockets. 28:376-386
ISSN:	1533-6794 0022-4650
DOI:	10.2514/3.55626
Popis:	A parabolized Navier-Stokes (PNS) scheme has been developed to study perfect-gas and equilibrium-air hypersonic flows around three-dimensional configurations. This numerical scheme is unconditionally time-like in the subsonic as well as the supersonic flow regions and does not require any sublayer approximation. This three-dimensional PNS scheme has been used to predict hypersonic flowfields over various blunt conical configurations under either flight or wind-tunnel conditions. The test cases cover a Mach number range of 6.9-20 and an angle-of-attack range from zero to 27 deg. The resulting predictions of wall heat-transfer rate are compared with flight or experimental wind-tunnel data and are found to be in excellent agreement under laminar and fully turbulent conditions. The predictions of the transition model of Dhawan-Narasimha, however, significantly differ from the observed flight data. Numerical results for large angle-of-attack conditions show that accurate modeling of the leeward crossflow separated region is essential for accurately predicting the associated leeward wall heating rates.
Databáze:	OpenAIRE
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