机译:氢引爆冲压发动机模型在4至8马赫数进风气流下的风洞试验
Russian Acad Sci, Semenov Inst Chem Phys, Moscow 119991, Russia|Natl Res Nucl Univ MEPhI, Moscow 115409, Russia;
Russian Acad Sci, Inst Theoret & Appl Mech, Siberian Branch, Novosibirsk 630090, Russia;
Russian Acad Sci, Semenov Inst Chem Phys, Moscow 119991, Russia;
Russian Acad Sci, Semenov Inst Chem Phys, Moscow 119991, Russia|Natl Res Nucl Univ MEPhI, Moscow 115409, Russia;
Russian Acad Sci, Semenov Inst Chem Phys, Moscow 119991, Russia|Natl Res Nucl Univ MEPhI, Moscow 115409, Russia;
Russian Acad Sci, Inst Theoret & Appl Mech, Siberian Branch, Novosibirsk 630090, Russia;
Russian Acad Sci, Inst Theoret & Appl Mech, Siberian Branch, Novosibirsk 630090, Russia;
Russian Acad Sci, Semenov Inst Chem Phys, Moscow 119991, Russia;
Russian Acad Sci, Inst Theoret & Appl Mech, Siberian Branch, Novosibirsk 630090, Russia;
Detonation ramjet model; Wind tunnel; Supersonic airflow; Spinning detonation; Pulsed detonation; Fuel-based specific impulse;
机译:氢燃料爆震冲压发动机模型:进风气流马赫数5.7和停滞温度1500 K下的风洞试验
机译:在接近空气流Mach编号5.7处的爆轰拉动模型的风洞测试和1500 k的停滞温度
机译:连续爆炸空气呼吸Ramjet示意图:风洞数据
机译:氢气爆炸式爆炸式拉姆喷射模型:风洞测试
机译:风冷冷凝器的不利风影响的实验研究:模型电厂的风洞测试。
机译:对城市环境中空气中有害释放物的短期最大个人暴露进行建模。第II部分:使用风洞实验数据验证确定性模型
机译:氢气爆炸式爆炸式拉姆喷射模型:风洞测试
机译:大型柔性超音速巡航飞机Cxb-70-1气动特性的风洞/飞行关联研究(The。 1:0.03比例模型的风洞试验,马赫数为0.6至2.53。