Several examples of three-dimensional boundary layers on helicopter rotors are analyzed within framework of small-crossflow and quasi-steady approximations; assumptions are shown to be mutually consistent and to have wide range of applicability; in laminar flow, crossflow can be separated into components due to rotation and instantaneous yawing of rotor blade relative to direction of flight; third-order perturbation expansions for flat-plate blade show relative importance of rotational and translational motion, and analysis of flow over several blade sections with thickness demonstrates role of chordwise pressure gradients; results indicate that crossflow tends to delay separation on retreating side of rotor disk. (06652)
Laminar boundary layers on helicopter rotors in forward flight
AIAA J
AIAA Journal ; 6 , n 10
1968
8 pages
Article (Journal)
English
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