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| Author | : Richard E. Kuhn |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1955 |
| Genre | : Aerodynamic load |
| ISBN | : |
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
| Author | : James W. Wiggins |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1954 |
| Genre | : Aerodynamic load |
| ISBN | : |
| Author | : Paul G. Fournier |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1953 |
| Genre | : Airplanes |
| ISBN | : |
The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.
| Author | : Douglas R. Lord |
| Publisher | : |
| Total Pages | : 52 |
| Release | : 1957 |
| Genre | : Aerodynamics |
| ISBN | : |
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.
| 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 | : Atwood R. Heath |
| Publisher | : |
| Total Pages | : 92 |
| Release | : 1960 |
| Genre | : Mach number |
| ISBN | : |
| Author | : John D. Bird |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1949 |
| Genre | : Aeronautics |
| ISBN | : |
The 7-point method of Weissinger is used to calculate the span loading in roll, lateral center of pressure, and damping in roll for wings having various aspect ratios, sweep angles, and taper ratios. The applicability of the method to the determination of certain other aerodynamic derivatives is investigated, and corrections for the first-order effects of compressibility are indicated.
| Author | : Edward C. Polhamus |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1958 |
| Genre | : Airplanes |
| ISBN | : |
A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.
