The effects of aerodynamic heating and heat transfer on the surface temperature of a body of revolution in steady supersonic flight
- Scherrer, Richard
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
- An approximate method for determining the convective cooling requirement in the laminar boundary-layer region of a body of revolution in high-speed flight was developed and applied to an example body. The cooling requirement for the example body was determined as a function of Mach number, altitude, size, and a surface-temperature parameter. The maximum value of Mach number considered was 3.0 and the altitudes considered were those within the lower constant-temperature region of the atmosphere (40,000 to 120,000 ft.). The extent of the laminar boundary layer was determined approximately at each condition as a function of the variables considered.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19930091982.
Accession ID: 93R21272.
- No Copyright.
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