Question

a wind tunnel nozzle is designed to operate at mach number of 5. to check the flow velocity, a pitot probe is placed at the nozzle exit. since the probe tip is blunt, a normal shock stans off the tip of the probe

KARNIVA ifolio- Ma X &Microsoft & 447745 &Senarai Ru 84) Whats x 427301 X ny course/68145/content/447745 1/1 KKKM3223 Fluid Dynamics Question on Compressible Flow (for students not attending the PBL session on 10 and 13 May 2019) A wind tunnel nozzle is designed to operate at a Mach number of 5. To check the flow velocity, a pitot probe is placed at the nozzle exit. Since the probe tip is blunt, a normal shock stands off the tip of the probe. a) If the nozzle exit static pressure is 10 kPa (abs), calculate absolute pressure should the pitot probe measure. b) If the stagnation temperature before the nozzle is 1450 K, determine the nozzle exit velocity

Answer 1

Fxst let us tate the Popesuties at STP Gonditdong R 286.4 ie K Mach nunbe at the dowy streans o the normal Shock Lwave 2 2K M K-I 2 2 2メ14 .s2- o.124 Ma Mo ニ0·4152- Static Pxegewie aftero Shockk is 1K 2K P2 Kt 2メ14 |レク) P 2-90 1Pa pitot tube hag to Absolute Preesnove Weaswre K- Po will be Ma 2 Pn .47DnI52 24D Po 2 326 K Pa

ca be founod by 02zle exit tepervatuse K- Tol 2- 4 TI 2416 K VI ve Locity of the nozzle exit is VI C) K RT 6.933×クト x 24.