Ok. Let's suppose the next imaginary experiment. I encouragely promise that I don't know anything about nowadays supersonic combustion problems. I want to continue with the discussion spread in the "rocket thrust" thread, and what Enigma and Russ Waters said. There is a supersonic flow at the entrance of combustion chamber, due to the intake of air. Why it does not possible generate a combustion steady wave (i.e. a detonation wave) in the combustion chamber. A weak detonation causes a supersonic flow behind it. I heard the Chapman-Jouguet detonations are possible oftenly. How could I generate a steady detonation?, I mean a detonation that no moves in the laboratory reference axes. I have another idea: what about heating the supersonic inlet current?. The Mach number will decrease, but would it descent below M=1?. In this case would occur a shock wave at the intake?.