Preliminary Design Guide for Predicting Rotor Performance.
ARMY MATERIEL COMMAND TEXARKANA TEX INTERN TRAINING CENTER
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A modified momentum aerodynamic model of a helicopter was used to determine the power required to hover out of ground effect and for level flight at specified velocities. Computations were made for a range of gross weight from 500 to 30,000 pounds, and a range of equivalent flat plate drag areas from 3 to 18 square feet. The results are presented in a graphical format.