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机译:Numerical investigations of the nozzle performance for a rocket-based rotating detonation engine with film cooling
State Key Laboratory of Mechanics and Control of Aeronautics and Astronautics Structures, Nanjing University of Aeronautics and Astronautics. Nanjing, 210016, People's Republic of China ,Jiangsu Province Key Laboratory of Aerospace Power System, College o;
Rotating detonation engine; Nozzle design; Truncation ratio; Film cooling; Aerodynamic performance;