NASA NTRS · 19660063505
Including re-entry heating in rocket engine thermal analyses.
Abstract
Reentry heat flux condition transformation into specified convective coefficients and temperatures, accounting for variation of flux with wall temperature
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Fineman, S., Glick, R. L.. 1966-10-01. Including re-entry heating in rocket engine thermal analyses.. https://ntrs.nasa.gov/citations/19660063505
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