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
1 answer:
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Answer:
Resolving Power=625000
Explanation:
See attached picture.
Answer:
a) W = 25.5 lbf
b) W = 150 lbf
Explanation:
Given data:
Mass of astronaut = 150 lbm
local gravity = 5.48 ft/s^2
a) weight on spring scale
it can be calculated by measuring force against local gravitational force which is equal to weight of body
W = mg
b) As we know that beam scale calculated mass only therefore no change in mass due to variation in gravity
thus W= 150 lbf