Inclusion of Tip Relief in the Prediction of Compressibility Effects on Helicopter Rotor Performance
AEROPHYSICS CO WASHINGTON DC
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The tip relief effect on the performance of helicopters operating at high subsonic tip Mach numbers is calculated. The theoretical method based on the complementary wing model for tip relief is applied. The method of application in complex blade element computer program is described and results are presented. Similarly, the technique and results from a simplified application for use in energy type prediction methods are given. Since tip relief is closely connected with the problem of predicting the compressible power loss of rotors, and techniques for predicting this power loss are reviewed and discussed in detail.