NDLI: Simulation of hypersonic scramjet exhaust. [pressure distribution on afterbody/nozzle sections of vehicle

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Simulation of hypersonic scramjet exhaust. [pressure distribution on afterbody/nozzle sections of vehicle

Content Provider	NASA Technical Reports Server (NTRS)
Author	Hopkins, H. B. Leng, J. Foreman, K. M. Oman, R. A.
Copyright Year	1975
Description	A plan and some preliminary analysis for the accurate simulation of pressure distributions on the afterbody/nozzle portions of a hypersonic scramjet vehicle are described. The objectives fulfilled were to establish the standards of similitude for a hydrogen/air scramjet exhaust interacting with a vehicle afterbody, determine an experimental technique for validation of the procedures that will be used in conventional wind tunnel facilities, suggest a program of experiments for proof of the concept, and explore any unresolved problems in the proposed simulation procedures. It is shown that true enthalpy, Reynolds number, and nearly exact chemistry can be provided in the exhaust flow for the flight regime from Mach 4 to 10 by a detonation tube simulation. A detailed discussion of the required similarity parameters leads to the conclusion that substitute gases can be used as the simulated exhaust gas in a wind tunnel to achieve the correct interaction forces and moments.
File Size	2908959
Page Count	73
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19750009272
Archival Resource Key	ark:/13960/t8vb2xb0m
Language	English
Publisher Date	1975-03-01
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Aerospace Vehicles Nozzle Flow Gas Flow Exhaust Gases Supersonic Combustion Ramjet Engines Wind Tunnel Tests Pressure Distribution Flow Characteristics Hypersonic Vehicles Flight Simulation 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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