A TABULATION OF SECTION AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS OF 1.61 AND 2.01 FOR FOUR SWEPT WINGS HAVING THE SAME PLATFORM BUT DIFFERENT SURFACE SHAPES.
A TABULATION OF SECTION AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS OF 1.61 AND 2.01 FOR FOUR SWEPT WINGS HAVING THE SAME PLATFORM BUT DIFFERENT SURFACE SHAPES.

Author:

Publisher:

Published: 1962

Total Pages: 41

ISBN-13:

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The section normal-force and pitching-moment coefficients for four sweepback wings with different surface shapes are tabulated. All the wings had NACA 65A005 thickness distributions, 50 degrees of sweepback at the quarter chord, a taper ratio of 0.20, and an aspect ratio of 3.5. There were three twisted wings and one flat wing. The twisted wings had 6 degrees of washout at the tip, but the twist variation along the span was either linear, quadratic, or cubic. The wings were tested at Mach numbers of 1.61 and 2.01 with fixed and free transition through a Reynolds number range of 1.7 to 3.6 x 10 to the 6th power. Angle-of-attack range was from -20 to 20 degrees.

Calculation of Tunnel-induced Upwash Velocities for Swept and Yawed Wings
Calculation of Tunnel-induced Upwash Velocities for Swept and Yawed Wings

Author: S. Katzoff

Publisher:

Published: 1948

Total Pages: 670

ISBN-13:

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The tunnel-induced upwash for a wing of any plan form and load distribution in a rectangular tunnel may be found with the aid of only two charts. One is given in the present paper. The second must be computed for each tunnel. The second chart is given for an open tunnel of 2:1 width-height ratio, a closed tunnel of 2:5 width-height ratio, and a closed tunnel of 10:7 width-height ratio.

Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9
Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9

Author: Harold Mirels

Publisher:

Published: 1949

Total Pages: 28

ISBN-13:

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An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.