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Stagnation Point Heat Transfer in High Enthalpy Gas Flows, Part II: Shock Layer Radiative Emission During Hypervelocity Re-Entry

Report Number: FDL TDR 64-41 Part 2
Author: Nerem, Robert M.
Corporate Author: Ohio State University
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 109
Contract: AF 33(657)-10110
Project: 1366
Task: 136615
AD Number: AD0601371

Experimental measurements of stagnation point equilibrium radiative heat transfer were performed using an arc driven shock tube facility and over the range of simulated flight velocities between 26,000 and 52,000 feet per second, and at altitudes from 100,000 to 170,000 feet. These measurements were compared with existing theoretical estimates; and wide disagreement is shown to exist at high temperatures and low densities where the continuum emission due to the deionization of N and O cations dominates the shock layer radiation. Using an approximate approach, a revised estimate is presented for the radiative emission from high temperature equilibrium air. This revised estimate is then applied to the determination of stagnation point equilibrium radiative heat transfer during re-entry at super-orbital velocities. A correlation for the shock layer emission rate useful in engineering design calculations is presented. A similar study concerning convective heat transfer appears in part I (AD-601 370) of this series.

Lockheed Martin Missiles & Fire Control
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