登入選單

返回Google圖書搜尋

Starting and Operating Limits of Two Supersonic Wind Tunnels Uitlizing Auxiliary Air Injection Downstream of the Test Section

Henry R. Hunczak

出版	National Advisory Committee for Aeronautics, 1954
URL	http://books.google.com.hk/books?id=TLcBaAEACAAJ&hl=&source=gbs_api

註釋

Data are presented for tunnels operating at Mach numbers 3.85, 3.05, and 2.87 over a range of injector-to-tunnel mass-flow ratios of 0.5 to 1.35. At Mach number 3.85, the starting pressure ratio of 9.8 without injectors but with a fixed second throat was reduced to 4.68 with injectors operating at an injector-to-tunnel mass-flow ratio of 1.27. The running pressure ratio was lowered from 8.3 to 4.5. Corresponding reductions at Mach number 3.05 were from 4.5 to 2.71 for starting from 4.5 to 2.37 for running at a mass-flow ratio of 0.9.