Actions for Calibration of HYPULSE for hypervelocity air flows corresponding to flight Mach numbers 13.5, 15, and 17.

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Calibration of HYPULSE for hypervelocity air flows corresponding to flight Mach numbers 13.5, 15, and 17.

Author
Calleja, John
Published
Dec 1, 1993.
Physical Description
1 electronic document
Additional Creators
Tamagno, Jose
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
A series of air calibration tests were performed in GASL's HYPULSE facility in order to more accurately determine test section flow conditions for flows simulating total enthalpies in the Mach 13 to 17 range. Present calibration data supplements previous data and includes direct measurement of test section pitot and static pressure, acceleration tube wall pressure and heat transfer, and primary and secondary incident shock velocities. Useful test core diameters along with the corresponding free-stream conditions and usable testing times were determined. For the M13.5 condition, in-stream static pressure surveys showed the temporal and spacial uniformity of this quantity across the useful test core. In addition, finite fringe interferograms taken of the free-stream flow at the test section did not indicate the presence of any 'strong' wave system for any of the conditions investigated.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19940019091.
Accession ID: 94N23564.
TR-335.
NAS 1.26:191578.
NASA-CR-191578.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15660824