NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Viscous shock-layer solutions for the low-density hypersonic flow past long slender bodiesResults are obtained for the surface pressure, drag, heat-transfer, and skin-friction coefficients for hyperboloids and sphere cones. Body half angles from 5 to 22.5 degrees are considered for various low-density flow conditions. Recently obtained surface-slip and shock-slip equations are employed to account for the low-density effects. The method of solution employed for the viscous shock-layer (VSL) equations is a partially coupled spatial-marching implicit finite-difference technique. The flow cases analyzed include highly cooled long slender bodies in high Mach number flows. The present perfect-gas VSL calculations compare quite well with available experimental data. Results have also been obtained from the steady-state Navier-Stokes (NS) equations by successive approximations. Comparison between the NS and VSL results indicates that VSL equations even with body and shock-slip boundary conditions may not be adequate in the stagnation region at altitudes greater than about 75 km for the cases analyzed here.
Document ID
19890040880
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gupta, R. N.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Moss, J. N.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Zoby, E. V.
(NASA Langley Research Center Hampton, VA, United States)
Tiwari, S. N.
(Old Dominion University Norfolk, VA, United States)
Lee, K. P.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 88-0460
Accession Number
89A28251
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available