一种CARET进气道超音速特性试验研究

Experimental Studies of a Caret Inlet at Supersonic Speed

对一种Caret进气道进行了试验研究,给出了该型进气道超音速基本气动特性。该进气道在Ma=1.6～2.0范围总压恢复急剧下降。在Ma=2.0时,由于亚临界防喘余量较小,在放气门关闭情况下将无进/发匹配点;在喘振点处,稳态周向畸变相对于临界状态在减小,而动态紊流度急剧增加;临界至超临界情况,在两个压缩斜板的交角后管道内出现流动分离。

A Caret inlet was studied by testing.Basic aerodynamic characteristics of the inlet at supersonic speed are presented.The total pressure recovery rapidly drops from Mach 16 to 20.No inlet/engine match point at Mach 20 without bypass was found due to the fact that the surge margin happened to be too narrow.Steady circumferential distortion declines from surge to critical state,nevertheless,dynamic turbulence intensity increases rapidly.Flow separations are visible in duct from critical to supercritical states,these separations stem from the intersection of two ramps and lowoutboard.