Flight Investigation of Effects of Rotor-Blade Twist on Helicopter Performance in the High-Speed and Vertical-Autorotative-Descent Conditions

Note presenting flight-performance measurements made on an untwisted, plywood-covered rotor in the high-speed and vertical-autorotative-descent conditions. The results were compared with measurements on a similar rotor with 8 degrees of linear washout and with theoretical calculations in order to determine the effects of rotor-blade twist on helicopter performance.