An upper stage of a launch vehicle propulsion unit fails to meet expectations during sea-level testing. This unit consists of a chamber at 4.052 MPa feeding hot propellant to a supersonic nozzle of area ratio ϵ= 20. The local atmospheric pressure at the design condition is 20 kPa. The propellant has a k = 1.2 and the throat diameter of the nozzle is 9 cm.
(a) Calculate the ideal thrust at the design condition.
(b) Calculate the ideal thrust at the sea-level condition.
(c) State the most likely source of the observed nonideal behavior.
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