SOLVED: Find the thrust specific fuel consumption (TSFC) of an ideal ramjet that is being considered for flight at M = 1.5 where the atmospheric temperature and pressure are 217 K and 11.91 kPa, respectively. The maximum temperature in the engine is T04 = 2500 K. Use a conventional hydrocarbon fuel where QR = 45,000 kJ/kg and assume γ = 1.4 and Cp = 1000 J/kg K. Compute the propulsive, thermal, and overall efficiencies.

SOLVED:Consider the twin-jet airplane described in Prob. 6.3. The thrust-specific fuel consumption is 1.0  N of fuel per newton of thrust per hour, the fuel capacity is 1900 gal, and the maximum gross weight is 136,960  N. Calculate the range and endurance at a standard altitude of 8  km.

Calculate the specific thrust and the TSFC of a single-spool turbojet engine having the following peculiarities: Cruise velocity of 280  m / s at altitude of 7000  m Intake efficiency of 93 % Compressor pressure ratio of 8: 1 and efficiency of 87 % Burner efficiency of 98 % Pressure drop in the combustion chamber of 4 % of the delivery pressure of the compressor TIT of 1200  K and efficiency of 90 % Mechanical efficiency of 99 % Nozzle efficiency 95 % Fuel heating value 44,000  kJ / kg | Numerad

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NASA Tests First Full-Scale Rotating Detonation Rocket Engine