This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Insulation-Radiation Temperature Control of Inflatable Hypersonic Vehicles
Annotation ability available
Sector:
Language:
English
Abstract
This paper presents the theory of an insulation-radiation cooling method applicable to expandable hypersonic vehicles; two simple configurations, a sphere and a cylinder, are analyzed to illustrate this method. Use of internal radiation and thin layers of insulation can reduce hot spot temperatures by as much as 33% compared to a 12% reduction possible by the use of internal radiation alone.
Citation
Ginter, R. and Cerreta, L., "Insulation-Radiation Temperature Control of Inflatable Hypersonic Vehicles," SAE Technical Paper 620331, 1962, https://doi.org/10.4271/620331.Also In
References
- Lees L. “Laminar Heat Transfer Over Blunt Bodies at Hypersonic Flight Speeds” Jet Propulsion April 1956
- Eckert E.R. G. Drake R. M. Jr. “Heat and Mass Transfer.” 1959
- Hankey W. L. Jr. Neumann R. D. Flinn E. H. “Design Procedures for Computing Aerodynamic Heating at Hypersonic Speeds,” WADC TR 59-610 June 1960