A lifting surface theory was developed for a helicopter rotor in forward flight for compressible and incompressible flow. The method utilizes the concept of the linearized acceleration potential and makes use of the vortex lattice procedure. Calculations demonstrating the application of the method are given in terms of the lift distribution on a single rotor, a two-bladed rotor, and a rotor with swept-forward and swept-back tips. In addition, the lift on a rotor which is vibrating in a pitching mode at 4/rev is given. Compressibility effects and interference effects for a two-bladed rotor are discussed.
Lifting surface theory for a helicopter rotor in forward flight
Decennial Specialists'' Meeting on Rotorcraft Dyn. ; 1984 ; Moffett Field, CA, United States
1984-09-01
Conference paper
No indication
English