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| Author | : Donald D. Arabian |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1954 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : Donald D. Arabian |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1961 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : Donald D. Arabian |
| Publisher | : |
| Total Pages | : 49 |
| Release | : 1954 |
| 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 | : William C. Sleeman |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1949 |
| Genre | : Aerofoils |
| ISBN | : |
This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
| Author | : James W. Schmeer |
| Publisher | : |
| Total Pages | : 42 |
| Release | : 1955 |
| Genre | : Aerodynamic load |
| ISBN | : |
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The leading edge of the wing was drooped 6 degrees about the 19-percent chord line from 0.15 semispan to the wing tip. Data were obtained at Mach numbers of 0.80 to 1.03 with average Reynolds numbers of 5,700,000 to 6,300,000, respectively. The results of this investigation are compared with the pressure data obtained with the undrooped or basic wing of a previous investigation.
| Author | : John A. Kelly |
| Publisher | : |
| Total Pages | : 706 |
| Release | : 1954 |
| Genre | : Aerodynamic load |
| ISBN | : |
A previous report, NACA TN 3007, gave force and moment data for the NACA 64A010 airfoil section equipped alternately with a flap and a slat at the leading edge, and with a split flap and a double-slotted flap at the trailing edge. The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA 3007. The pressure data for the leading-edge flap and slat have been converted into coefficients of normal force, chord force, and moment based on the geometry of the leading-edge device.
| Author | : Jones F. Cahill |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1952 |
| Genre | : |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 130 |
| Release | : 1977 |
| Genre | : |
| ISBN | : |
| Author | : Kenneth P. Spreemann |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
