EFFECT OF MACH NUMBER, REYNOLDS NUMBER, AND THICKNESS RATIO ON THE AERODYNAMIC CHARACTERISTICS OF NACA 63A-SERIES AIRFOIL SECTIONS.
LOCKHEED-CALIFORNIA CO BURBANK
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Force and moment data are presented from wind tunnel tests of two- dimensional symmetrical NACA 63A-Series airfoils of thickness ratios from 9 to 18 percent. The tests were conducted at Mach numbers ranging from M .30 to M .94 with Reynolds numbers varying from R 2.0 X 1,000,000 to R 9.5 X 1,000, 000 and at angles of attack as high as 29 degrees. Comparisons are made, wherever possible, with NACA tests of the same or similar airfoils. The transonic similarity rule is used to evaluate the consistency of the data.
- Fluid Mechanics