Data from the - National Advisory Committee for Aeronautics
Chartered in 1915, operational from 1917-1958.



Vultee Airfoil Usage

On designations: many of the airfoils listed here have "mod" at the end of their designation. Typically, this means that either the camber line has been modified, the leading edge contour has been modified or that the trailing edge thickness has been changed.

  Aircraft  Wing Root Airfoil Wing Tip Airfoil
 Vultee 48 P-66 Vanguard  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 51 BC-3 Valiant  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 54 BT-13 Valiant  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 61 P-66 Vanguard  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 63 BT-13 Valiant  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 70 (74) L-1 Vigilant  Curtiss C-72 Curtiss C-72
 Vultee 74 BT-15 Valiant  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 74 SNV Valiant  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 79 BT-15 Valiant  NACA 0018-64 mod NACA 0009-64 mod
 Vultee 79 SNV Valiant  NACA 0018-64 mod NACA 0009-64 mod


NACA - the US National Advisory Committee for Aeronautics

Tests of NACA 0009, 0012, and 0018 airfoils in the full-scale tunnel
Goett, Harry J Bullivant, W Kenneth
NACA Report 647
1939

An investigation was conducted in the NACA full-scale wind tunnel to determine the aerodynamic characteristics of the NACA 0009, 0012, and 0018 airfoils, with the ultimate purpose of providing data to be used as a basis for comparison with other wind-tunnel data, mainly in the study of scale and turbulence effects. Three symmetrical 6 by 36-foot rectangular airfoils were used. The Reynolds number range for minimum drag was form 1,800,000 to 7,000,000 and for maximum lift, from 1,700,000 to 4,500,000. The effect of rounded tips was determined for each of the airfoils. Tests were also made of the NACA 0012 airfoil equipped with a 0.20c full-span split flap hinged at 0.80c. Tuft surveys were included to show the progressive breakdown of flow near maximum lift. Momentum surveys were made in conjunction with force measurements at zero lift as an aid in converting force-test data to section coefficients.


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