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| 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 | : James W. Wiggins |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1954 |
| Genre | : Airplanes |
| ISBN | : |
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
| Author | : James W. Wiggins |
| Publisher | : |
| Total Pages | : 692 |
| Release | : 1956 |
| Genre | : Airplanes |
| ISBN | : |
An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. The results indicate that, in a general, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
| Author | : Bennie W. Cocke (Jr.) |
| Publisher | : |
| Total Pages | : 62 |
| Release | : 1958 |
| Genre | : Aerodynamic load |
| ISBN | : |
Summary: An investigation has been conducted in the Langley full-scale tunnel to determine the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane over a range of test velocities from minimum stall speed up to speeds giving load factors for wing buckling. Tests were conducted over a range of speeds from approximately 41 to 70 mph with wing-guy-cable loads, wing-distortion photographs, and aerodynamic-force data recorded at each speed for a full range of angle of attack.
| Author | : Arthur Henderson |
| Publisher | : |
| Total Pages | : 94 |
| Release | : 1956 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the X-1E has been conducted in the Langley 9-inch supersonic tunnel. Tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete model configurations. Detailed analysis of the test results has not been made.
| Author | : Edward C. Polhamus |
| Publisher | : |
| Total Pages | : 90 |
| Release | : 1955 |
| Genre | : Aerodynamics |
| ISBN | : |
A summary and analysis has been made of results obtained in a systematic research program concerned with the effects of wing sweep, aspect ratio, taper ratio, and dihedral on the rolling moment due to sideslip characteristics of wing-fuselage configurations up to Mach numbers of about 0.95. Other test results are presented to show trends of rolling moment due to sideslip with Mach number for a few wings in the transonic and supersonic speed range.
| Author | : Rodger L. Naeseth |
| Publisher | : |
| Total Pages | : 88 |
| Release | : 1963 |
| Genre | : Aerodynamics |
| ISBN | : |
An investigation has been made in the Langley 300-MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a related series of parawings in which wing sweep was the primary variable. The leading-edge sweep angles varied from 400 to 750 and the three basic parawings had flat-planform sweep angles of 350, 450, and 550. The canopies of the wings were made of fabric. Tests were made at an airspeed of 38.6 mph and a Reynolds number of approximately 1.5 X 106. The maximum angle-of-attack range was from 140 to 530 for the wings having a canopy of 350 flat-planform sweep. A limited investigation of lateral characteristics was made for sideslip angles from approximately -50 to 160 for two angles of attack, and lateral stability derivatives were obtained for some configurations through a angle-of-attack range. Forces and moments acting on the wing and apex hinge moments were measured.
| Author | : Wendy B. Lessard |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 2000 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
The present study was performed to determine how significant the interference effects of the wind-tunnel model support system and tunnel walls can be for a high-speed configuration during takeoff and landing conditions. A 5-percent scale model of the Technology Concept Airplane was recently tested in the Langley 14- by 22-Foot Subsonic Tunnel. The model was numerically modeled with and without the support and tunnel walls and compared with experimental data. Detailed analysis of the flow provided additional insight concerning what effects the postsupport and tunnel walls had on the flow field. This study revealed that although the overall forces and moments could be experimentally accounted for, the detailed flow features, such as the surface pressure distributions, could not be accurately simulated without including the post in the computations.
| Author | : John E. Lamar |
| Publisher | : |
| Total Pages | : 332 |
| Release | : 1971 |
| Genre | : Airplanes |
| ISBN | : |
The experimental balance and pressure data obtained from tests of an untwisted variable-sweep wing with an outboard pivot exhibited nonlinearities in both total normalforce-coefficient and pitching-moment-coefficient curves for all sweep angles and fuselage conditions. These total effects have been traced back through the section data and pressure distributions to find the causes. The causes of these nonlinearities were found to be (1) separation of flow on the outer panel and (2) a leading-edge vortex flow on the inner panel. A fuselage added to the wing had little effect on the aerodynamic characteristics. Predictions of wing loadings and performance characteristics were made by using the modified Multhopp method and a comparison with experimental results indicated reasonable agreement. The changes in span loading as a result of leading-edge shed-vortex formation and flow separation at the higher angles of attack caused an increase in the induced-drag parameter.
