THERMAL AND AERODYNAMIC PERFORMANCES OF THE SUPERSONIC MOTION
Generally speaking, Mach number of 4 can be taken as a boundary value for transition from conditions for supersonic, into the area of hypersonic flow, distinguishing two areas: area of supersonic in which the effects of the aerodynamic heating can be neglected and the area of hypersonic, in which th...
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| Format: | Article |
| Language: | English |
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VINCA Institute of Nuclear Sciences
2010-01-01
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| Series: | Thermal Science |
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| Online Access: | http://thermalscience.vinca.rs/2010/4/20 |