46 research outputs found
Theoretical and experimental data for a number of NACA 6A-series airfoil sections
Get PDFThe NACA 6a-series airfoil sections were designed to eliminate the trailing-edge cusp which is characteristic of the NACA 6a-series sections. Theoretical data are presented for NACA 6a-series basic thickness forms having the position of minimum pressure of 30, 40, and 50 percent chord and with thickness ratios varying from 6 percent to 15 percent. Also presented are data for a mean line designed to maintain straight sides on the cambered sections
Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)
Get PDFNote on the accuracy of a method for rapidly calculating the increments in velocity about an airfoil due to angle of attack
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Aerodynamic Characteristics of 15 NACA Airfoil Sections at Seven Reynolds Numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)
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Two-dimensional Aerodynamic Characteristics of 34 Miscellaneous Airfoil Sections
Get PDFThe aerodynamic characteristics of 34 miscellaneous airfoils tested in the Langley two-dimensional low-turbulence tunnels are presented. The data include lift, drag, and in some cases, pitching-moment characteristics, for Reynolds numbers between 3.0 x 10 (exp 6) and 9.0 x 10 (exp 6)
Aerodynamic Characteristics of Several NACA Airfoil Sections at Seven Reynolds Numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)
Get PDFExperimental Investigation of Boundary-layer Suction Through Slots to Obtain Extensive Laminar Boundary Layers on a 15-percent-thick Airfoil Section at High Reynolds Numbers
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