PLEASE DO NOT USE THE SAME ANSWER THAT SOMEONE ALREADY USED ON CHEGG. I POSTED S

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PLEASE DO NOT USE THE SAME ANSWER THAT SOMEONE ALREADY USED ON CHEGG. I POSTED SAME QUESTIONS AND THEY JUST COPIED FROM ANOTHER ONE ON CHEGG AND DIDNT RELIZE THAT THE QUESTIONS WHERE COMPLETLY DIFFRENT FROM WHAT I WAS AKING. BUT PLEASE ANSWER ALL QUESTIONS AND INDICATE A,B,C,D,E... SO PLEASE DO NOT COPY SOMEONE ELSES WORK IF YOU CAN'T ANWER ALL OF THEM CORRECTLY. THEN LET SOMEONE ELSE WHO CAN. I CANT KEEP POSTING BECUASE I RAN OF OF POSTS.

Problem 2 Converging-diverging nozzle with shock wave inside nozzle Consider flow through a converging-diverging nozzle. The exit area of the nozzle is 40cm2, and the throat area of the nozzle is 10cm2. The air entering the nozzle has stagnation conditions: P, 120kPa, and To-280K. A normal shock wave stands in the diverging portion of the nozzle, where M 2 Hints: Use Figs. D.1 and D.S. (a) Calculate the area at the shock location. Hint: Use Fig. D.1 (b) Calculate the Mach after the shock wave, M2. Hint: use Fig. D.S. (c) Calculate static pressures before and after the shock, Pand P2. Hint: Use D.1 for P1 and use D.S for P2 (d) Calculate the stagnation pressure after the shock, Po2 (e Find the Mach number, static pressure, static temperature and velocity at the nozzle exit. Hint: Use D.1

Explanation / Answer

a)

From A/A* plot in figure D.1, we get that at M1 = 2, corresponding A/A* = 1.55

Area at shock location A = 1.55 * 10 = 15.5 cm^2

b)

Using figure D.S, at Max = 2, we get May = 0.58

Hence, M2 = 0.58

c)

Using D.1, for Ma = 2, we get p/p0 = 0.125

Hence P1 = 0.125 * 120 = 15 kPa

From figure D.S, we get for Ma = 2, corresponding py/px = 4.5

Hence, P2 = 4.5 * 15 = 67.5 kPa

d)

From figure D.S, for Max = 2, we get p0y / px = 5.5

p02 = 5.5 * 15 = 82.5 kPa

e)

For Ma1 = 2, we get A2* / A1* = 1.3872

A2* = 1.3872 * 10 = 13.872 cm^2

Aexit / A2* = 40 / 13.872 = 2.88

From figure D.1, for A/A* = 2.88, we get Max = 0.2

For Max = 0.2, we get P/ P0 = 0.9725 and T / T0 = 0.9921

P = 0.9725 * 82.5 = 80.23 kPa

T = 0.9921 * 280 = 277.8 K

V = Ma * (kRT)^0.5

= 0.2 * (1.4 * 287 * 277.8)^0.5

= 66.8 m/s

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