Method is presented for computing downwash field due to vortex wake of lifting rotor in forward flight; formulation permits calculation of velocities at arbitrary points in space; suitable choice of computation points thus permits treatment of isolated or tandem rotor problems; calculations have been carried out for single and tandem rotors tested by NASA, and computed airloads are compared to experimental data; reasonable agreement is shown.
Aerodynamic characteristics of model helicopter rotor operating under nominally stalled conditions in forward flight
Am Helicopter Soc -- J
American Helicopter Society -- Journal ; 9 , n 3
1964
8 pages
Aufsatz (Zeitschrift)
Englisch
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Engineering Index Backfile | 1948
|Engineering Index Backfile | 1947
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DOAJ | 2017
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