On supersonic combustion

Some basic concepts and features of supersonic combustion are explained fro m the view point of macroscopic aerodynamics. Two kinds of interpretations of supersonic combustion are proposed. The difference between supersonic co mbustion and subsonic combustion is discussed, and the mechanism of superso nic combustion propagation and the limitation of heat addition in supersoni c flow are pointed out. The results of the calculation of deflagration in s upersonic flow show that the entropy increment and the total pressure loss of the combustion products may decrease with the increase of combustion vel ocity. It is also demonstrated that the oblique detonation wave angle may n ot be controlled by the wedge angle under weak underdriven solution conditi ons and be determined only by combustion velocity. Therefore, the weak unde rdriven solution may become self-sustaining oblique detonation waves with a constant wave angle.