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An approximate method for calculating three-dimensional inviscid hypersonic flow fieldsAn approximate solution technique was developed for 3-D inviscid, hypersonic flows. The method employs Maslen's explicit pressure equation in addition to the assumption of approximate stream surfaces in the shock layer. This approximation represents a simplification to Maslen's asymmetric method. The present method presents a tractable procedure for computing the inviscid flow over 3-D surfaces at angle of attack. The solution procedure involves iteratively changing the shock shape in the subsonic-transonic region until the correct body shape is obtained. Beyond this region, the shock surface is determined using a marching procedure. Results are presented for a spherically blunted cone, paraboloid, and elliptic cone at angle of attack. The calculated surface pressures are compared with experimental data and finite difference solutions of the Euler equations. Shock shapes and profiles of pressure are also examined. Comparisons indicate the method adequately predicts shock layer properties on blunt bodies in hypersonic flow. The speed of the calculations makes the procedure attractive for engineering design applications.
Document ID
19900017750
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Riley, Christopher J.
(NASA Langley Research Center Hampton, VA, United States)
Dejarnette, Fred R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1990
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TP-3018
L-16745
NAS 1.60:3018
Accession Number
90N27066
Funding Number(s)
PROJECT: RTOP 506-40-91-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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