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BASELINE CONFIGURATION ANALYSIS
PROPULSION SYSTEM ANALYSIS
5 other sections not shown
200 KT Cruise advanced technology aerodynamic aircraft airfoil aspect ratio baseline airplane baseline configuration baseline mission brake horsepower canard design cd rH Composite computed by GASP cooling drag cruise altitude cruise L/D cruise specific range diesel engine drag coefficient Effect of Ming engine weight fuel cell fuel efficiency Fuel Used Specific full-span fuselage GATE Engine H rH HIPS airplane increase increment induced drag km/n knots KT Cruise Speed laminar wing leading edge lift coefficient lithium lithium carbonate Loading with 200 maximum lift coefficient NASA natural laminar flow nm/lb optimum wing loading payload percent performance propulsion system pusher engine Pusher Propeller reduction Reference 19 Reynolds number rH H rH rH Rotary Engine sea level single-slotted Fowler flaps SIR Engine specific fuel consumption specific weight stall speed Stratified charge Table takeoff total fuel true airspeed turbine turbocharger wing area