Mc conkey 10-pb

This document contains solutions to multiple problems related to nozzles and jet propulsion. Problem 10.8 asks the reader to calculate the required nozzle exit area, net thrust developed, air-fuel ratio, and specific fuel consumption for a turbojet aircraft given various parameters such as air mass flow rate, compressor pressure ratio, maximum cycle temperature, efficiencies, and fuel calorific value. Diagrams are provided to illustrate the problem.