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:
The resistance is 24.9 Ω
Explanation:
The resistivity is equal to:
The area is:
A = 60 * 60 = 3600 um² = 0.36x10⁻⁴cm²
If NA is greater, then, the term 1/NA can be neglected, thus the equation:
Where
V = 0.44 V
E = 11.68*8.85x10¹⁴ f/cm
The length is:
L = 10 - 0.335 = 9.665 um
The resistance is: