At the inlet to the combustor of a supersonic combustion ramjet (or scramjet), the flow Mach number is supersonic. For a fuel-ai
r mass ratio of .03 and a combustor exit temperature of 4800 degr, calculate the inlet Mach number above which the flow will be unchoked. Assume one- dimensional frictionless flow with y = 1.4, with heat release per slug of fuel equal to 4.5 x 108 ft-lbf. (Anderson 3.11) The temperatures for the above combustion problems are pretty high. A more representative value of the heat capacity ratio for products of combustion at these temperatures is y = 1.28 The value of the specific gas constant R may still be approximated as equal to that of air. b) For problem #2, calculate the inlet Mach number above which the flow will be unchoked, based on y = 1.28
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Answer:
Stat PVC = Stat(82+98.5)
Stat PVT = Stat(59+71.5)
Explanation
PVI = 71 + 35
Let G1 = Grade 1; G2 = Grade 2
G1 = +2.1% ; G2 = -3.4%
Highest point of curve at station = 74 + 10
General equation of a curve:
At highest point of the curve
Station PVT