Question

Fluid Mechanics- Number four

Oon 11 Not yet wered Marked out of 18.00 Remove the Arocket has a throat area 12 and exit area 22 and is held down by a test stand Irvide the combustion chamber, P150 ps and T-1700 R. MW-15 Ibmbno and k-14. Assume the flow through the nozzle to be steady and sentropic DOWNLOAD EQUATION SHEET 1) Calculate the Mach number at the exit 022 012 1.7 00.5 2) If the Mach number at the exit is 1.3. calculate the velocity at the exit infus. 1204 Us 2597 us 4978 Us 3595 3) Cakulate the exhaust flowrate in bus 220 m/s 20 mis 320 lbs 120 lbs 4) if the Mach number at the exitis 1.8, exhaust flowrate is 320 bms and exit velocity is 1204, calculate the thrust of the rocketinin 00:5*10-31 3.5'10 1.5 104

Answer 1

F = m ve + (P.-P.) A Pe р = (1 + * - 1 meg T Te P A e Me Ae Pe

aft = psia 12 inch / 1 dbf = 32.179 (Webm. (pound-fonce/inch?) Уль! absolute F = 385280 lom.ft st 32.174 dom.lt 52 + 22.8082 (1 h) x (127inen)? - 15259.267 (lol) = 1.525 X (ubf) 104 Answen & Lili) is connect.