A comparative study of supersonic aerofoil theories /
A comparative study on three theroetical methods for prediction of aerodynamic characteristics of steadu supersonic flow at Mach number form 1.2 to 5.0, over simple thin aerofoil has been conducted. These theories are Shock_Expansion Theory. Ackeret's Theory and Busemann;s Theory. The scope inc...
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Sekudai : UTM,
1993
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