- 6 The Nozzle Of A Supersonic Wind Tunnel Has An Exit To Throat Area Ratio Of 6 79 When The Tunnel Is Running A Pitot 1 (171.45 KiB) Viewed 38 times
6. The nozzle of a supersonic wind tunnel has an exit-to-throat area ratio of 6.79. When the tunnel is running, a Pitot
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6. The nozzle of a supersonic wind tunnel has an exit-to-throat area ratio of 6.79. When the tunnel is running, a Pitot
6. The nozzle of a supersonic wind tunnel has an exit-to-throat area ratio of 6.79. When the tunnel is running, a Pitot tube mounted in the test section measures 1.448 atm (see schematics below). What is the reservoir pressure for the tunnel? [Ans: 6.8 atm). Refer to the Compressible Flow Tables. I Shock wave M> 1 P1 Ti M2 <M p2 > Pi T2 > T V2 <V البه) TO Pitot tube Роз Tos PO 2 < Poj 102 = To,
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