Accession Number : AD0902068
Title : Determination of the (Ideal Practical) Hover Efficiency of Circulation Control Rotors.
Descriptive Note : Technical note,
Corporate Author : DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATIO N AND SURFACE EFFECTS DEPT
Personal Author(s) : Williams, Robert M. ; Hemmerly, Rodney A.
Report Date : AUG 1971
Pagination or Media Count : 51
Abstract : An approximate analysis of the maximum hover performance of a Circulation Control Rotor is presented. Closed form equations are developed which conveniently show the contribution of the induced, profile, compressor and coriolis powers in terms of the basic airfoil equivalent lift to drag ratios. A range of rotor taper ratios and solidities are examined under the constraint of ideal twist distribution. A comparison is made with a conventional rotor using a NACA 0012 reference airfoil. It is demonstrated that the circulation control rotor can achieve comparable overall hover efficiencies (Figure or Merit) at significantly higher values of rotor thrust coefficient to solidity ratio than conventional rotors. The implications of these characteristics for helicopter design is then discussed briefly. (Author)
Descriptors : *JET FLAPS), (*ROTOR BLADES(ROTARY WINGS), JET FLAPS), (*HELICOPTER ROTORS, HOVERING, EQUATIONS OF MOTION, MATHEMATICAL MODELS, LIFT, DRAG, VELOCITY, CAMBER, ANGLE OF ATTACK, TWIST(AERODYNAMICS), AERODYNAMIC SLOTS, DUCTS, VORTICES, GAS FLOW, AERODYNAMIC CHARACTERISTICS, BOUNDARY LAYER CONTROL, CORIOLIS EFFECT, EFFICIENCY.
Subject Categories : Helicopters
Distribution Statement : APPROVED FOR PUBLIC RELEASE