Results of an investigation, conducted on the Langley helicopter test tower, of a rotor having an NACA 632A015 airfoil thickness distribution in combination with an NACA 230 mean line are presented. Comparison with a previously reported test of a symmetrical rotor blade efficiency was substantially improved over a wide range of tip Mach numbers. The maximum mean lift coefficient was essentially unchanged from that obtained with uncambered blades. Some data showing the effect of a distributed type of leading-edge roughness are also included.
Hovering Characteristics of a Rotor having an Airfoil Section Designed for Flying-Crane Type of Helicopter
1961-04-01
Sonstige
Keine Angabe
Englisch
Engineering Index Backfile | 1961
|Engineering Index Backfile | 1959
|Hovering performance of helicopter rotor using NACA 8-H-12 airfoil sections
Engineering Index Backfile | 1954
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