An Extension of the Local Momentum Theory to a Distorted Wake Model of a Hovering Rotor1981 - 112 pages |
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airfoil American Helicopter Society analytical angle of attack apparent mass blade element theory blade span blade tip blade under consideration calculated spanwise lift coefficient input mode collective pitch input Comparison of measured cyclic pitch distributions in hover downwash elliptical wing equation 20 EXPERIMENT NACA TN EXPERIMENT NASA extended Local Momentum fixed wing following blade forward flight given by equation Helicopter Rotor hovering rotor induced velocity distribution Kocurek and Tangular Local Momentum Theory measured and calculated Momentum Theory NON-DIMENSIONAL AIRLOADING number of blade pitch input mode preceding blade PRESCRIBED WAKE THEORY prescribed wake vortex PRESENT THEORY K-T recurrence equation rotary wing rotor blade rotor rotational plane shown in Fig spanwise lift distributions spanwise partitions station Tangular wake model THEORY K-T WAKE thrust coefficient input time-wise variation tip vortex tip vortices uniform attenuation coefficient UTRC code vortex ring wake deformation WAKE THEORY K-T wake vortex theory wing span