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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 | : 1961 |
| 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 | : Charles F. Whitcomb |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1956 |
| Genre | : Aerodynamics, Transonic |
| ISBN | : |
An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
| 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 | : 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 | : William Solomon |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1953 |
| Genre | : Aerodynamics, Transonic |
| ISBN | : |
| Author | : Jack F. Runckel |
| Publisher | : |
| Total Pages | : 104 |
| Release | : 1956 |
| Genre | : Aerodynamic load |
| ISBN | : |
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
| Author | : |
| Publisher | : |
| Total Pages | : 130 |
| Release | : 1977 |
| Genre | : |
| ISBN | : |
