NDLI: Hypervelocity capability of the hypulse shock-expansion tunnel for scramjet testing

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Hypervelocity capability of the hypulse shock-expansion tunnel for scramjet testing

Content Provider	NASA Technical Reports Server (NTRS)
Author	Foelsche, Robert O. Shih, Ann T. Tsai, Ching-Yi Rogers, R. Clayton Bakos, Robert J.
Copyright Year	2001
Description	New hypervelocity capabilities for scramjet testing have recently been demonstrated in the HYPULSE Shock-Expansion Tunnel (SET). With NASA's continuing interests in scramjet testing at hypervelocity conditions (Mach 12 and above), a SET nozzle was designed and added to the HYPULSE facility. Results of tests conducted to establish SET operational conditions and facility nozzle calibration are presented and discussed for a Mach 15 (M15) flight enthalpy. The measurements and detailed computational fluid dynamics calculations (CFD) show the nozzle delivers a test gas with sufficiently wide core size to be suitable for free-jet testing of scramjet engine models of similar scale as, those tested in conventional low Mach number blow-down test facilities.
File Size	507947
Page Count	10
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20010059583
Archival Resource Key	ark:/13960/t8wb0482q
Language	English
Publisher Date	2001-01-01
Access Restriction	Open
Subject Keyword	Research And Support Facilities (air) Free Jets Test Facilities Computational Fluid Dynamics Calibrating Enthalpy Supersonic Combustion Ramjet Engines Mach Number Shock Tunnels Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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