Data for question 1 to 5 The total weight of the aircraft is given by: WTO = WAvion+WSub + Wprop + Wother + Wstruc + WPL + WEnergy/fuel where Wstruc is the structures weight, Wsub is the subsystems weights, WProp is the propulsion system weight, WAvion is the avionics weight, Wother is other weights, WPL is the payload weight, and W Energy is the weight of the stored energy. The Fixed Wing propeller powered aircraft has the following characteristics: MFStruct = 0.25 (Mass fraction of Structure, MFSub = 0.05 (Mass fraction of Subsystem, (P/W) Aircraft 0.05 hp/kg Wstruc WTO Wsub WTO Break specific fuel consumption =0.23kg/hp-hr P WTO Air Vehicle MFprop = 0.08 P WP Powerplant max = 10 at cruise condition Propeller efficiency = 0.55 Maximum range of the Aircraft=400km All avionics, payloads, and other nonvarying weights of the Aircraft =10kg
The value of fuel mass fraction is?​