A theory is developed for calculation of the induced veloc-ity field of a helicopter rotor in forward flight. The rotor is approximated by a disk of continuous thrust and in-plane force distributions, which are assumed to be known. Its wake is represented by a semi-infinite cylinder of distributed vorticity. It is also suggested how this theory can be used for solving the full rotor problem, when the inflow data are given but the force distribution of the rotor is unknown. A numerical example is calculated. (Author)
Disk Approximation for a Helicopter Rotor in Forward Flight
1972
66 pages
Report
No indication
English
Disk approximation for a helicopter rotor in forward flight
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