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AERO-THERMODYNAMIC ASPECTS OF HIGH SPEED FLIGHT
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English
Abstract
The efficient utilization of modern rocket engines leads to very high speed rocket vehicles. In particular, the velocities encountered lead to very high stagnation temperatures and potentially high test transfer rates. These aero-thermodynamic effects are investigated for both glide and ballistic vehicles, and the design limitations are discussed.
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Citation
RADCLIFFE, W., "AERO-THERMODYNAMIC ASPECTS OF HIGH SPEED FLIGHT," SAE Technical Paper 580152, 1958, https://doi.org/10.4271/580152.Also In
References
- Romig Mary F. Dore Frank J. “Solutions of the Compressible Laminar Boundary Layer Including the Case of a Dissociated Free Stream” Convair Report ZA-7-012” 1954
- Romig Mary F. “Stagnation Point Heat Transfer for Hypersonic Flow” Jet Propulsion 26 Dec. 1956 1098 1101
- Lees Lester “Laminar Heat Transfer over Blunt Nosed Bodies at Hypersonic Speeds” Jet Propulsion 26 1956 259 269
- Ferris Antonio Feldman Lewis Daskin Walter “The Use of Lift of Re-entry from Satellite Trajectories” Jet Propulsion 27 November 1957 1184 1191
- Allen Julian H. Eggers Alfred J. Jr. “A Study of the Motion and Aero-dynamic Heating of Missiles Entering the Earth’s Atmosphere at High Supersonic Speeds NACA Technical Note 4047 October 1957