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Similar solutions for viscous hypersonic flow over a slender three-fourths-power body of revolutionFor hypersonic flow with a shock wave, there is a similar solution consistent throughout the viscous and inviscid layers along a very slender three-fourths-power body of revolution The strong pressure interaction problem can then be treated by the method of similarity. Numerical calculations are performed in the viscous region with the edge pressure distribution known from the inviscid similar solutions. The compressible laminar boundary-layer equations are transformed into a system of ordinary differential equations. The resulting two-point boundary value problem is then solved by the Runge-Kutta method with a modified Newton's method for the corresponding boundary conditions. The effects of wall temperature, mass bleeding, and body transverse curvature are investigated. The induced pressure, displacement thickness, skin friction, and heat transfer due to the previously mentioned parameters are estimated and analyzed.
Document ID
19880003370
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Lin, Chin-Shun
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1987
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ICOMP-87-7
NASA-TM-100205
E-3803
NAS 1.15:100205
Accession Number
88N12752
Funding Number(s)
PROJECT: RTOP 505-62-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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