Research on Model Helicopter Rotor Blade Slap at Moderate Tip Speeds

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Abstract
A parametric study of model helicopter rotor blade slap has been conducted in the Massachusetts Institute of Technology 5 by 71/2 ft anechoic wind tunnel test facility. Previous studies of blade slap in this facility did not exceed tip Mach numbers of 0.40. In order to more closely simulate tip speeds of real helicopters, advancing tip Mach numbers of up to 0.58 were achieved. Blade slap contours are presented and discussed. The study of the shaft angle effect on the blade slap reveals two distinct regions of blade slap connected by a transition region. A peak blade slap Mech number scaling law is described and compared with the results. The prediction shows good correlation with the measured values for shaft angles greater than or equal to negative two degrees. Finally, a secondary blade slap phenomenon was observed which had not previously been shown to exist.

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