Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722063351
Category :
Languages : en
Pages : 28
Book Description
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...
An Approximate Method for Calculating Three-Dimensional Inviscid Hypersonic Flow Fields
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722063351
Category :
Languages : en
Pages : 28
Book Description
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...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722063351
Category :
Languages : en
Pages : 28
Book Description
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...
An Approximate Method for Calculating Three-Dimensional Inviscid Hypersonic Flow Fields
Author: National Aeronautics and Space Administration NASA
Publisher:
ISBN: 9781729157510
Category :
Languages : en
Pages : 27
Book Description
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...
Publisher:
ISBN: 9781729157510
Category :
Languages : en
Pages : 27
Book Description
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...
An Approximate Method for Calculating Three-dimensional Inviscid Hypersonic Flow Fields
Author: Christopher Joseph Riley
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
Book Description
An Approximate Method for Calculating Inviscid Flow Fields Over Three-dimensional Blunt-nosed Bodies in Hypersonic Flow
Author: Christopher Joseph Riley
Publisher:
ISBN:
Category :
Languages : en
Pages : 150
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 150
Book Description
NASA Technical Paper
NASA Technical Paper
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 656
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 656
Book Description
Scientific and Technical Aerospace Reports
Report
Research and Technology Objectives and Plans Summary
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 244
Book Description
"A compilation of the summary portions of each of the RTOPs used for management review and control of research currently in progress throughout NASA"--P. i.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 244
Book Description
"A compilation of the summary portions of each of the RTOPs used for management review and control of research currently in progress throughout NASA"--P. i.
Annual Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.