机译:RBCC嵌入式火箭发动机的气-液剪切同轴喷射器在连续变化的混合比下具有极高的富燃料燃烧特性
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China;
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China;
Science and Technology on Scramjet Laboratory, National University of Defense Technology, 410073 Changsha, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China;
Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China;
RBCC; rocket engine; shear coaxial injector; continuously varying mixture ratio; extreme fuel-rich; combustion characteristics;
机译:极富油量节气火箭发动机在连续节流过程中的燃烧动力学
机译:富燃料燃烧中双旋流同轴喷油器的稳定性
机译:双旋流同轴喷油器的富油燃烧特性
机译:同轴剪切GH2 / GO2喷油器的单火箭燃烧室湍流燃烧特性分析
机译:剪切同轴液体火箭喷射器的流体力学。
机译:液 - 气同轴注射器液体射流分解长度的研究 - 火箭发动机喷射器雾化特性 -
机译:sanso-methan(中心点)nenryo富含preburner no nensho tokusei。 (用于分级燃烧循环火箭发动机的LO(sub 2)/ GCH(sub 4)富燃料预燃器的燃烧特性)。