Pressure data at 90 percent blade radius were obtained for a helicopter main rotor with 10-64C blade sections during flight. Concurrent measurements ere made of vehicle flight state, performance and some rotor loads. The test envelope included hover, level flight from about 65 to 162 knots, climb and descent, and collective fixed maneuvers. Good agreement is shown between some sets of airfoil pressure distributions obtained in flight and those from two-dimensional wind-tunnel tests or theoretical calculations.
A Flight Investigation of Blade-Section Aerodynamics for a Helicopter Main Rotor Having 10-64C Airfoil Sections
1981
181 pages
Report
Keine Angabe
Englisch