Science and Technology of Energetic Materials

Vol.77, No.5 (2016)

Research paper

Numerical simulation of the effects of nozzle on thrust performance of rotating detonation engine
Seiichiro Eto, Yusuke Watanabe, Nobuyuki Tsuboi, Takayuki Kojima, and A.Koichi Hayashi


The effects of the converging-diverging (CD) nozzle on the thrust performance of the rotating detonation engine(RDE) were estimated by using the three-dimensional numerical simulations with the detailed chemical reaction model.The nozzle geometry is based on the reference of Rankin et al . The nozzle is composed of the long constant cross section, the short converging section, and the diverging section. The periodic exhaust oscillation is considerably reduced by the present CD nozzle. The pressure difference from the averaged value is approximately 1.2 % and the difference in Mach number is approximately 0.4 %. The increment of Isp using the CD nozzle is approximately 15s. The nozzle performance is estimated via the thrust coefficient. The thrust coefficient of the CD nozzle used this study is nearly corresponded with the ideal value. The combustion efficiency of C*ηc* are obtained 92-98 % between the combustion chamber pressure of 1.2 and 2.9 MPa.


shock wave, detonation engine, numerical simulation

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