Question

Concorde The Concorde supersonic transport flew at M = 2.2 at 20 km altitude. Air is decelerated isentropically by the engine inlet system to a local Mach number of 1.3. The air passed through a normal shock and was decelerated further to M = 0.4 at the engine compressor section. Assume, as a first approximation, that this subsonic diffusion process was isentropic and use standard atmosphere data for freestream conditions. -Determine the temperature, pressure and stagnation pressure of the air entering the engine compressor. Why should the pressure be reduced at the compressor inlet?

Answer 1

copressen Inlet to Inlet M= 2 2 online the 275 1 = 275 K romal shock CPI = 7.15, 10"han Properties I Ti=8c at 20km altitudi 12. = 1.007kgh T Isonhopie for M: 2.2 7:14 cair) Stagmation Pressure Pipo, = 0.093522 Por= loi = 85.0067 x 10" = 8.50067 x 10 sh. 7.95410" 0.093522 * 541.2000 Y Isenpopic flow Tor = To T/Toi = 0.50813 7 Too = 2758813 = St At section 2-2 Por= Poi & Isenpopie poor - 12/po2 = 0.360914 = P2 = 0.36094x 85 0067x04 P₂ = 30.6801x10" N/m2 13 T2/Tor = 0.747384 => T2 = 0.7479847 S41.200 Across N.S To = 404.4842 K Ishropic flow for Mach=1.3 Tz / Toz = 0.. PS3 Mala / Toz Note across Nis stagnation To ponture vremains constit ie Tosa Tor= To, = s4.20k şinct stagntion top? for pressor Across N.S 13/12 = 1190873 Po/P2 = 1.805 = - T = 404.4842 1.190 873 Y - 30. 69 01x109 1. Sos T3 = 481.6893127k P = SS.3775805x10" N/m2 Required result