【摘要】 介绍三维进气道和超声速燃烧冲压式喷气发动机 (SCRAMJET)模型一项实验研究的结果。Scramjet模型由进气道和燃烧室组成 ,此模型组件的设计是为了研究流动结构以获得进气道的特性 ,以及研究燃烧室和进气道、燃料 (氢及碳氢燃料 )点火和燃烧的相互影响。这些试验是在下吹式风洞(M =2 ～ 6,Reunit=( 8～ 54) × 1 0 6)和热射式风洞 (M =6及 7 2 ,Reunit =( 1 0 ～ 32 )× 1 0 6,Tt =1 50 0 ～ 2 50 0K)中进行的。更多还原

【Abstract】 Results of an experimental study of 3D inlets and the scramjet module are presented.The scramjet module consists of an inlet and a combustion chamber.The module is designed to study the flow structure,to obtain the inlet characteristics, and to study the mutual effects of the combustor and the inlet,fule ignition and combustion (hydrogen and hydrocarbon fuels). The tests was conducted in the blowdown wind tunnel at Mach numbers from 2 to 6 and unit Reynolds numbers from 8 to 54 million and in the hot shot wind tunnel at Mach numbers M=6 and 7.2 and unit Reynolds numbers from 10 to 32 million (T t =1500～2500K).更多还原