Aerodynamic Characteristics Of A Spoiler Slot Deflector Control On A 45c Sweptback Wing At Mach Numbers Of 161 And 201
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Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45© Sweptback Wing at Mach Numbers of 1.61 and 2.01
Author | : Douglas R. Lord |
Publisher | : |
Total Pages | : 52 |
Release | : 1957 |
Genre | : Aerodynamics |
ISBN | : |
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An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.
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