NASA NTRS · 19650052518
Shock tube instrumentation techniques for study of hypervelocity entry problems.
Abstract
Shock tube instrumentation to study convective and radiative heat transfer of hot gases simulating hypervelocity reentry
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Gruszczynski, J. S., Rogers, D. A.. 1965-08-01. Shock tube instrumentation techniques for study of hypervelocity entry problems.. https://ntrs.nasa.gov/citations/19650052518
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