Energies | |
Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths | |
StephenA. Danczyk1  JohnW. Bennewitz1  WilliamA.Hargus1  MathiasC. Ross2  RichardD. Smith3  BlaineR. Bigler4  | |
[1] Air Force Research Laboratory, Edwards, CA 93524, USA;Department of Mechanical and Aerospace Engineering, UCLA, Los Angeles, CA 90095, USA;GHKN Engineering LLC., Kirkland, WA 98034, USA;Jacobs Technology Group, Air Force Research Laboratory, Edwards, CA 93524, USA; | |
关键词: rotating detonation rocket engine; detonation; counter-propagation; wave dynamics; injection recovery; | |
DOI : 10.3390/en14082037 | |
来源: DOAJ |
【 摘 要 】
A rotating detonation rocket engine (RDRE) with various convergent nozzles and chamber lengths is investigated. Three hundred hot-fire tests are performed using methane and oxygen ranging from equivalence ratio equaling 0.5–2.5 and total propellant flow up to 0.680 kg/s. For the full-length (76.2 mm) chamber study, three nozzles at contraction ratios
【 授权许可】
Unknown