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| Author | : Jack F. Runckel |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1953 |
| Genre | : |
| ISBN | : |
| Author | : John A. Kelly |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1951 |
| Genre | : Aerodynamic load |
| ISBN | : |
The data presented in this report were obtained by North American Aviation, Inc., from an investigation conducted in the Southern California Cooperative Wind Tunnel. Tests were made over a range of Mach numbers from 0.300 to 0.883 to determine the aerodynamic characteristics of a semispan model of a 35 degree swept-back wing equipped with a leading-edge slat and to gain additional knowledge of the aerodynamic loads and automatic operation of the slat. Lift, drag, and pitching-moment characteristics of a model wing in the presence of a fuselage were measured as well as pressures acting on the slat in the retracted and the full-open positions. The pressure data were analyzed to ascertain the opening characteristics of the slat for two possible circular-arc slat tracks which could be used for automatic operation of the slat.
| Author | : Kenneth P. Spreemann |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1953 |
| Genre | : |
| ISBN | : |
| Author | : Clarence L. Gills |
| Publisher | : |
| Total Pages | : 442 |
| Release | : 1957 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Donald D. Arabian |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1961 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : Fred A. Demele |
| Publisher | : |
| Total Pages | : 112 |
| Release | : 1959 |
| Genre | : |
| ISBN | : |
| Author | : Kenneth P. Spreemann |
| Publisher | : |
| Total Pages | : 644 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
| Author | : Kenneth P. Spreemann |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : Donald D. Arabian |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1954 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : F.E. Jr West |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1953 |
| Genre | : |
| ISBN | : |
