Author: H. J. FivelPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 130
Book Description
Analytical Comparison of Hypersonic Flight and Wind Tunnel Viscous/inviscid Flow Fields
Author: H. J. FivelPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 130
Book Description
Analytical Comparison of Hypersonic Flight and Wind Tunnel Viscous
Author: H.J. FivelAnalysis of the Three-dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow
Author: John C. AdamsPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 98
Book Description
An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
NASA Technical Note
Author: Scientific and Technical Aerospace Reports
Author: Monthly Catalog of United States Government Publications
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 2834
Book Description
Analysis of Post-support and Wind-tunnel Wall Interference on Flow Field about Subsonic High-lift High-speed Research Configuration
Author: Wendy B. LessardPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48
Book Description
The present study was performed to determine how significant the interference effects of the wind-tunnel model support system and tunnel walls can be for a high-speed configuration during takeoff and landing conditions. A 5-percent scale model of the Technology Concept Airplane was recently tested in the Langley 14- by 22-Foot Subsonic Tunnel. The model was numerically modeled with and without the support and tunnel walls and compared with experimental data. Detailed analysis of the flow provided additional insight concerning what effects the postsupport and tunnel walls had on the flow field. This study revealed that although the overall forces and moments could be experimentally accounted for, the detailed flow features, such as the surface pressure distributions, could not be accurately simulated without including the post in the computations.
Aeronautical Engineering
Author: Advances in Hypersonics: Computing hypersonic flows
Author: John J. BertinPublisher: Birkhauser
ISBN: 9780817636722
Category : Science
Languages : en
Pages : 0
Book Description
Approximate Two Layer (Inviscid/Viscous) Methods to Model Aerothermodynamic Environments.- Second-Order Effects in Hypersonic Boundary Layers.- Unstructured-Grid Algorithms for High-Speed CFD Analysis.- Numerical Simulation of Three-Dimensional Hypersonic Viscous Flows.- Numerical Simulation of Entry Flow over Blunt Swept-Wing Planes.- Viscous Nonequilibrium Flow Calculations.- The Finite Pointset Method for Hypersonic Flows in the Rarefied Gas Regime.- Computation of Flowfields for Hypersonic Flight at High Altitudes.
Monthly Catalog of United States Government Publications, Cumulative Index
Author: United States. Superintendent of DocumentsPublisher:
ISBN:
Category : United States
Languages : en
Pages : 1408
Book Description