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Unformatted text preview: FILE: A BIZ. CF’Ia..jh‘l' Example Problem: 1} ﬁt normal shock forms in a convergent divergent nozzle at a location where the area is
approximatelv 2 emf. The nozzle throat area is 1 cm2 and the total pressure and temperature
upstream ofthe shock are 3110 kPa and 500 K respectivelv. a} Start this calculation bv assuming the shock wave is at A = 2 cm2 and calculate the
Mach number and static pressure just upstream ofthe shock. bl Calculate the total and static pressure and Mach numberjust downstream ofthis
shock. c} ﬁt the nozzle exit the area is 3 emf. Calculate Mach number and static pressure and
temperature at this location. d] If the air pressure at the area position of 3 cm2 is greater or less than atmospheric
pressure how will this affect vour assumption of the shock location. e) If you were to trv to find a newfmore accurate solution, where would vou place the
shock and whv? SoLu‘nod AL 5 AL ‘ 2 ¢ A g LQ87 =7 H=Z.l‘l
A? W5WCh¢KaA 0,44me ~ H“ Alrmujﬁumq .mwm MWQ a. buy/L be duo]: 4.0 it“ WSW
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 Spring '10
 MCLAUGHLIN
 Fluid Dynamics, Mach number, Shock wave, Nozzle, normal shock forms

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