A rocket engine has the following design parameters:
- Combustion chamber stagnation temperature of 3000 ◦K,
- molecular weight of combustion products of 25 kg/kmol
- ideal conditions and γ = 1.2
- Nozzle exit Mach number Me = 3.758 and pe = 101.3
kPa,
- the throat diameter of 0.1m.
Determine the thrust Γ at:
(1a) At sea level, where ambient pressure pa =
pe
(1b) At 60 km, where pa = 0
A rocket engine has the following design parameters: - Combustion chamber stagnation temperature of 3000 ◦K, - molecular
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A rocket engine has the following design parameters: - Combustion chamber stagnation temperature of 3000 ◦K, - molecular
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