Publication Date:
2019-06-28
Description:
A comparatively rapid method is presented for determining theoretically the bending stresses of helicopter rotor blades in forward flight. The method is based on the analysis of the properties of a vibrating beam, and its uniqueness lies in the simple solution of the differential equation which governs the motion of the bent blades.
Type:
NACA-TM-1312
Format:
application/pdf
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