Answered: Falcon 9 rocket engine, fuel mixture…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

Falcon 9 rocket engine, fuel mixture LOX/RP1 is combusted in a large tank and exhausts
through a converging-diverging (C-D) nozzle. The combustion gas (k = 1.221, R = 0.3885
kJ/kg.K) in the large tank has a temperature of 3500 K and pressure 9 MPa (abs). The throat
diameter of the C-D nozzle is 0.5334 m and the nozzle operates at design condition at 20
km altitude. The flow in the C-D nozzle is steady and isentropic.
Air pressure above sea level can be calculated as :
p = 101325 (1 – H x 2.25577 x 10-5)5.25588
where
101325 = normal temperature and pressure at sea level (Pa)
p = air pressure (Pa)
H = altitude above sea level (m)

Express ALL answers in 4 significant figures.

(a) Calculate : Velocity at the Exit and the diameter of the EXIT.

(b) Calculate the Thrust produced.

Help me to solve a and b please im stuck

Table of Equation 1:
Compressible Flow
O Ma =
VKRT
P = pRT, P, = P,RT, -
k+1 a-1)
1+
:+1 a-1)
P.
p'
%3D
(R-1)
1+
Pe
k-1
5,
(A-1)
Ma
k
AMAP,
°V RT,
(k+1)
12(k-1)
6) m =
k -1
(k+1)
2 12(k-1)
k
(7)m A'P.
RT. Ik + 1
k - 1
(k+1)
12(k-1)
1 1+
2
Ma?
A
A
Ма
k+1

Table of Equation 2:
(12) Re =
pVD
15) Thrust = mV. + (Pe- Patm)A.
16 NPSH = P4V P.
7 2g Y
(P1-P,
(17) NPSHA
+(Z,- Zs)- his
(18 PV
12
2g
+hp
P2
+
+ zz + hy +hL
2g
(19MLMajor
LMinor
D 2g
2g
20 Pump Power Output, P, = yhQ

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