Stagnation Point Heat Transfer in High Enthalpy Gas Flows, Part II: Shock Layer Radiative Emission During Hypervelocity Re-Entry
Item
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Title
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Stagnation Point Heat Transfer in High Enthalpy Gas Flows, Part II: Shock Layer Radiative Emission During Hypervelocity Re-Entry
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Date
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1964
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Index Abstract
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Coming Soon
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Photo Quality
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Complete
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Report Number
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FDL TDR 64-41 Part 2
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Creator
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Nerem, Robert M.
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Corporate Author
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Ohio State University
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Laboratory
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Flight Dynamics Laboratory
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Extent
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109
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Identifier
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AD0601371
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Access Rights
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OTS
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Distribution Classification
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1
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Contract
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AF 33(657)-10110
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DoD Project
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1366
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DoD Task
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136615
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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None
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Abstract
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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.
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Report Availability
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Full text available
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Date Issued
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1964-03
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Provenance
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Lockheed Martin Missiles & Fire Control
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Type
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report
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Format
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1 online resource
FDLTDR64-041part02.pdf