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)
Determination of the (Ideal Practical) Hover Efficiency of Circulation Control Rotors
1971
51 pages
Report
No indication
English
Aircraft , Fluid Mechanics , 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 , Circulation controlled rotor blades , High lift , Lift drag ratio , Propeller tips
ACOUSTIC SCALING FOR SMALL ROTORS IN HOVER
British Library Conference Proceedings | 2019
|Hover Performance Correlation for Full-Scale Coaxial Rotors
British Library Conference Proceedings | 2007
|Aeroelastic Analysis of Multibladed Hingeless Rotors in Hover
Online Contents | 1995
|CYLINDRICAL MESH ADAPTATION FOR ISOLATED ROTORS IN HOVER
British Library Conference Proceedings | 2002
|