The aerodynamic performance of rotorcraft designed for heavy-lift and high-speed cruise is examined. Configurations considered include the tiltrotor, the compound helicopter, and the lift-offset rotor. Design conditions are hover and 250-350 knot cruise, at 5k/ISA+20 degrees Celsius (civil) or 4k/95 degrees Fahrenheit (military); with cruise conditions at 4000 or 30,000 ft. The performance was calculated using the comprehensive analysis CAMRAD II, emphasizing rotor optimization and performance, including wing-rotor interference. Aircraft performance was calculated using estimates of the aircraft drag and auxiliary propulsion efficiency. The performance metric is total power, in terms of equivalent aircraft lift-to-drag ratio L/D = WV/P for cruise, and figure of merit for hover.
Performance of Advanced Heavy-Lift, High-Speed Rotorcraft Configurations
2007
29 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Laboratory & Test Facility Design & Operation , Computer Software , Aerodynamic characteristics , Helicopters , Rotary wing aircraft , Aerodynamic lift , Performance(Engineering) , Efficiency , Propulsion systems , Configurations , Aerodynamic drag , Rotors , Figure of merit , Hovering , Optimization , Symposia , Vertical takeoff aircraft , Reprints , Auxiliary , Rotorcraft , Heavy lift , Camrad-ii computer program , Tiltrotors , Compound helicopters , Lift offset , Vtol(Vertical takeoff and landing) , Jhl(Joint heavy lift) , Ria(Runway independent aircraft) , Lctr(Large civil tiltrotor) , Lctc(Larce civil tandem compoung) , Labc(Large advancing blade concept)
Civil Applications of High Speed Rotorcraft and Powered Lift Aircraft Configurations
SAE Technical Papers | 1987
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