NDLI: Mach 5 inlet cfd and experimental results

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Mach 5 inlet cfd and experimental results

Content Provider	NASA Technical Reports Server (NTRS)
Author	Rupp, George D. Reddy, D. R. Weir, Lois J.
Copyright Year	1989
Description	An experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft supersonic wind tunnel. The 2-D inlet model was designed to study the Mach 3.0 to 5.0 speed range for an over-under turbojet plus ramjet propulsion system. The model was extensively instrumented to provide both analytical code validation data as well as inlet performance information. Support studies for the program include flow field predictions with both 3-D parabolized Navier-Stokes (PNS) and 3-D full Navier-Stokes (FNS) analytical codes. Analytical predictions and experimental results are compared.
File Size	6125459
Page Count	16
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890018299
Archival Resource Key	ark:/13960/t0rr6rc3z
Language	English
Publisher Date	1989-07-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Navier-stokes Equation Ramjet Engines Computational Fluid Dynamics Engine Inlets Flow Distribution Wind Tunnel Tests Two Dimensional Models Propulsive Efficiency Propulsion System Configurations Hypersonic Inlets Turbojet Engines Mach Number 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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