Screen LibraryThe effects of an inverse-taper leading-edge flap on the aerodynamic characteristics in pitch of a wing-body combination having an aspect ratio of 3 and 45 degrees of sweepback at Mach numbers to 0.92 /
An investigation has been made to detemnine the effects of an inverse-taper leading-edge flap on the drag and on the static-longitudinal characteristics of a swept-wing-body conibination. The wing had 45 degrees of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or...
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| Literature type: | Book |
| Language: | English |
| Series: |
Technical note / National Advisory Committee for Aeronautics ;
4366 |
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| Summary: |
An investigation has been made to detemnine the effects of an inverse-taper leading-edge flap on the drag and on the static-longitudinal characteristics of a swept-wing-body conibination. The wing had 45 degrees of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or twist. However, with the flap deflected, the wing had a camber and twist distribution similar to that resulting from the incorporation of conical camber in the forward portion of a plane wing. The tests were conducted over a range of Mach numbers from 0.25 to 0.92 at a Reynolds number of 3.2 million, and over a Reynolds number range of 3.2 million to 15 million at a Mach number of 0.25 with flap deflections to 16 degrees. |
| Item Description: | NACA TN No. 4366. |
| Carrier Form: | 57 p. : ill. ; 27 cm. |
| Bibliography: | Includes bibliographical references. |
| CLC: | V224 |
| Call Number: | V224/D376 |