Oblique detonation wave engine performance prediction

The performance of an oblique detonation wave engine (ODWE) is evaluated and compared to a diffusive scramjet engine. Diffusive scramjet performance is predicted for both constant area and constant pressure combustion. Detonation wave calculations that utilize a perfect pas approximation vs a real gas model indicate the inadequacy of a perfect gas approach, Hence, a real gas model is utilized in which the flow is in chemical equilibrium after combustion, Results are provided for both frozen and equilibrium how through the expansion waves and nozzle, Performance parameters are calculated for H-2 and CH4, a range of freestream Mach numbers and fuel dow rates, various inlet configurations, and altitude, Results are for specific thrust and a normalized transverse engine size, The ODWE analysis shows the importance of including the Taylor wave, done here for the first time, An ODWE gives comparable performance to diffusive engines and offers several advantages. The smaller longitudinal size of the ODWE produces less drag and less engine heat transfer, The ODWE offers design flexibility, since the wedge angle that controls the detonation wave can be varied to provide optimum performance over the hypersonic flight envelope. Wedge angle variation also allows for an easy start and restart capability.