An investigation was conducted to compare the performance of two 25- ft-diam rotors which had identical dimensions and were similar in construction but different in blade airfoil-sections. Tests were conducted at indicated blade pitch angles from 3 degrees to 11.5 degrees and rotor speeds of 200, 290, and 371 rpm. The 23012.6 rotor required 2 percent less power to hover than the 0012.6. At thrust coefficients above design, the performance of the 23012.6 became better than the 0012.6 rotor.
Static Thrust Investigation of Full-Scale PV-2 Helicopter Rotors Having NACA 0012.6 and 23012.6 Airfoil Sections
1946
25 pages
Report
Keine Angabe
Englisch
Hovering performance of helicopter rotor using NACA 8-H-12 airfoil sections
Engineering Index Backfile | 1954
|Engineering Index Backfile | 1960
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