Three-dimensional Approximate Viscous Shock Layer Method for Hypersonic Flow Over Blunt-nosed Bodies
Author : M. Malekzadeh Dirin
Publisher :
Page : pages
File Size : 37,94 MB
Release : 2003
Category :
ISBN :
Author : M. Malekzadeh Dirin
Publisher :
Page : pages
File Size : 37,94 MB
Release : 2003
Category :
ISBN :
Author : Arthur C. Grantz
Publisher :
Page : 292 pages
File Size : 40,44 MB
Release : 1989
Category : Aerodynamics, Hypersonic
ISBN :
Author : F. McNeil Cheatwood
Publisher :
Page : 200 pages
File Size : 29,93 MB
Release : 1991
Category :
ISBN :
Author : F. McNeil-Cheatwood
Publisher :
Page : pages
File Size : 12,18 MB
Release : 1991
Category :
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Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 28 pages
File Size : 33,64 MB
Release : 2018-06-30
Category :
ISBN : 9781722063351
An 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. Riley, Christopher J. and Dejarnette, Fred R. Langley Research Center RTOP 506-40-91-01...
Author : F. M. Cheatwood
Publisher :
Page : pages
File Size : 32,64 MB
Release : 1992
Category :
ISBN :
Author : Hsien Kei Cheng
Publisher :
Page : 50 pages
File Size : 39,17 MB
Release : 1961
Category : Aerodynamics, Hypersonic
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Author : Roberto Vaglio-Laurin
Publisher :
Page : 54 pages
File Size : 45,69 MB
Release : 1958
Category : Aerodynamics, Hypersonic
ISBN :
Author : National Aeronautics and Space Administration NASA
Publisher :
Page : 27 pages
File Size : 35,26 MB
Release : 2018-10-23
Category :
ISBN : 9781729157510
An 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. Riley, Christopher J. and Dejarnette, Fred R. Langley Research Center RTOP 506-40-91-01...
Author : Michael E. Tauber
Publisher :
Page : 44 pages
File Size : 41,15 MB
Release : 1989
Category : Aerodynamic heating
ISBN :