NDLI: Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations. volume 1: computational technique

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Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations. volume 1: computational technique

Content Provider	NASA Technical Reports Server (NTRS)
Author	Marconi, F. Salas, M. Yaeger, L.
Copyright Year	1976
Description	A numerical procedure has been developed to compute the inviscid super/hypersonic flow field about complex vehicle geometries accurately and efficiently. A second order accurate finite difference scheme is used to integrate the three dimensional Euler equations in regions of continuous flow, while all shock waves are computed as discontinuities via the Rankine Hugoniot jump conditions. Conformal mappings are used to develop a computational grid. The effects of blunt nose entropy layers are computed in detail. Real gas effects for equilibrium air are included using curve fits of Mollier charts. Typical calculated results for shuttle orbiter, hypersonic transport, and supersonic aircraft configurations are included to demonstrate the usefulness of this tool.
File Size	4190511
Page Count	102
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19760015406
Archival Resource Key	ark:/13960/t5gb6w386
Language	English
Publisher Date	1976-04-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Heat Transfer Supersonic Flow Computer Programming Aerospace Vehicles Three Dimensional Flow Finite Difference Theory Flow Distribution Inviscid Flow Hypersonic Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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