Computation of Subsonic Flow Region
For numerical solutions of problems on steady supersonic flow around blunt-nosed bodies in USSR the method suggested by G.F. Telenin  and usually called the method of straight lines is widely used. In a series of papers [7–12] this method has been developed for application to combustible gas mixture flows. For the model of infinitely thin detonation wave the method of straight lines applies completely analogous to adiabatic gas flows, the only difference being that in the energy conservation law across the shock the heat release term Q appears.
KeywordsShock Wave Steady Flow Detonation Wave Node Point Combustion Front
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