A liquid propellant engine has the following characteristics: chamber pressure of 7 MPa, constant ratio of specific heats of 1.3
1 answer:
Answer:
- 1.55
- 260 N.s
- 3370 m
- 1.6
- 43.75 kg/s
Explanation:
1) Thrust coefficient at sea level.
Cfsl = TSL / Pca
TSL = Mp * Vc + ( Pc - Pa )Ac
Mp = mass flux = 43.75 kg/s
∴ Cfsl = Mp Vc / Pca + ( Pc - Pa )/Pc * ( Ac / A* )
= 1.6 - 0.04923 = 1.55
<u>2) Specific impulse at sea </u>
Isp = Vc / g = 2549.75 / 9.81
= 260 N.s
3) Altitude at optimal expansion
H = 3370 m
<u>4) thrust coefficient at optimal expansion </u>
CF = 1.6
attached below is the detailed solution
<u>5) Mass flux through the throat </u>
Mass flux = P1 * At / Cc
= ( 7*10^6 * 0.01 ) / 1600
= 43.75 kg/s
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Answer
63 %
Explanation:
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