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|Title:||Effect of nozzle shapes on the performance of continuously rotating detonation engine|
|Source:||Yi, T.-H.,Lou, J.,Turangan, C.,Khoo, B.C.,Wolanski, P. (2010). Effect of nozzle shapes on the performance of continuously rotating detonation engine. 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition : -. ScholarBank@NUS Repository.|
|Abstract:||The effect of nozzle shape, angle and length on the propulsive performance of continuously rotating detonation engine is numerically investigated in a three-dimensional annular chamber with the one-step chemical kinetics of a hydrogen and air mixture. The thrust and specific impulse of the rotating detonation engine with four different nozzles are evaluated to find out the best performance nozzle shape. This chosen nozzle shape is used as a baseline nozzle. In addition to the description of a detailed flowfield structure in the chamber with the baseline nozzle, the changes in flowfield properties at the chamber inlet and nozzle exit due to nozzle shapes are also investigated. With the baseline nozzle, the evaluation on the effect of nozzle angle and length is performed. The best engine performance and less total pressure loss are achieved in the divergent nozzle with the nozzle angle of 10° and the nozzle length of 0.04 m. However, the rotating detonation engine has the negligible nozzle effect on the propulsive performance, compared with that for pulse detonation engine. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc.|
|Source Title:||48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition|
|Appears in Collections:||Staff Publications|
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