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Transonic and Hypersonic Flows topics include: Hypersonic flow, mach number independence, hypersonic similarity, hypersonic flow newtonian theory, transonic similarity, murman and cole methods, euler equations and full velocity potential equation solutions.
Transonic flow is between Mach 0.8 and 1.2, or about 965 to 1236 km/h (600 to 900 mph). Hypersonic flow is Mach 5 and above, or about 6,150-12,300 (4,000 miles per hour).
Transonic flow is when air flows above, at, and below the speed of sound at the same time at different points on an object. For example, the air on a wing flows faster, so that air could be supersonic while the air flowing over the body of an airplane could be subsonic.
Hypersonic flows require other similarity parameters than transonic and compressible flow.
The governing equations for hypersonic flows include: Mass conservation Momentum conservation Internal energy conservation Total energy conservation
The source terms for these equations include: Nitrogen dissociation Vibrational energy relaxation
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