Control effectiveness and hinge-moment measurements at a Mach number of 1.9 of a nose flap and trailing-edge flap on a highly tapered low- aspect-ratio wing
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Mitchell, Meade H , Jr↗
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Results for “WINGS - DESIGN WING, TAPERED”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Wing-flow Measurements of Longitudinal Stability and Control Characteristics of a Supersonic Airplane Configuration Having a 42.8 Degree Sweptback Circular Arc Wing with Aspect Ratio 4.0, Taper Ratio 0.50, and Sweptback Tail Surfaces
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Crane, Harold L↗
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane 45 degree swept-back wing of aspect ratio 3, taper ratio 0.4 with 3-percent-thick, biconvex section
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Heitmeyer, John C↗
Small-scale investigation at transonic speeds of the effects of thickening the inboard section of a 45 degrees sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section
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Spreemann, Kenneth P↗
Transonic aerodynamic characteristics of three W-plan-form wings having aspect ratio 8, taper ratio 0.45, and NACA-63A-series airfoil sections
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Morrison, William D , Jr↗
Effects of a series of inboard plan-form modifications on the longitudinal characteristics of two 47 degree sweptback wings of aspect ratio 3.5, taper ratio 0.2, and different thickness distributions at Mach numbers of 1.61 and 2.01
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Cooper, Morton↗
Effect of nose shape and trailing-edge bluntness on the aerodynamic characteristics of an unswept wing of aspect ratio 3.1, taper ratio 0.4, and 3-percent thickness
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Heitmeyer, John C↗
Pressure Distributions on Plug-and Semaphore-type Spoiler Ailerons on a 35 Degree Sweptback Wing of Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section at High Subsonic Speeds
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Hammond, Alexander D↗
Investigation at Transonic Speeds of Loading over a 30 Degree Sweptback Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a Body
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Arabian, Donald D↗
Effect of linear spanwise variations of twist and circular-arc camber on low-speed static stability, rolling, and yawing characteristics of a 45 degree sweptback wing of aspect ratio 4 and taper ratio 0.6
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Jaquet, Byron M↗
Effect of High-lift Devices on the Static-lateral-stability Derivatives of a 45 Degree Sweptback Wing of Aspect Ratio 4.0 and Taper Ratio 0.6 in Combination with a Body
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Lichtenstein, Jacob H↗
Investigation of Wing Characteristics at a Mach Number of 1.53 III : Unswept Wings of Differing Aspect Ratio and Taper Ratio
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Nielsen, Jack N↗
Effect of Airfoil Section and Tip Tanks on the Aerodynamic Characteristics at High Subsonic Speeds of an Unswept Wing of Aspect Ratio 5.16 and Taper Ratio 0.61
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SILVERS H NORMAN↗
Low-speed Static Longitudinal and Lateral Stability Characteristics of a Model with Leading-edge Chord-extensions Incorporated on a 40 Degree Sweptback Circular-arc Wing of Aspect Ratio 4 and Taper Ratio 0.50
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Goodson, Kenneth W↗
Effect of leading-edge sweepback on lift, drag, and pitching-moment characteristics of thin wings of aspect ratio 3 and taper ratio 0.4 at subsonic and supersonic speeds
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Wetzel, Benton E↗
Theoretical Additional Span Loading Characteristics of Wings with Arbitrary Sweep, Aspect Ratio, and Taper Ratio
The Weissinger method for determining additional span loading has been used to find the lift-curve slope, spanwise center of pressure, aerodynamic center location, and span loading coefficients of untwisted and uncambered wings having a wide range of plan forms characterized by various combinations of sweep, aspect ratio, and taper ratio. The results are presented as variations of the aerodynamic characteristics with sweep angle for various values of aspect ratio and taper ratio. Methods are also included for determining induced drag and the approximate effects of compressibility. Despite the limitations of a lifting line method such as Weissinger's, the good agreement found between experimentally and theoretically determined characteristics warrants confidence in the method. In particular, it is believed that trends observed in results of the Weissinger method should be reliable. One of the most significant results showed that for each angle of sweep there is a taper ratio for which aspect ratio has little effect on the span loading and for which the loading is practically elliptical. This elliptic loading is approached at a taper ratio of 1.39 for 30 degree of sweepforward, 0.45 for zero degree of sweepback. (author)
Deyoung, John↗
Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-body Combinations Having Cambered Wings with an Aspect Ratio of 3.5 and a Taper Ratio of 0.2 : Effect at M = 2.01 of Nacelle Shape and Position on the Aerodynamic Characteristics in Pitch of Two Wing-body Combinations with 47 Deg Sweptback Wings
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Driver, Cornelius↗
Effect of Taper Ratio on the Low-speed Rolling Stability Derivatives of Swept and Unswept Wings of Aspect Ratio 2.61
Results of tests conducted in the 6-foot-diameter rolling-flow test section of the Langley stability tunnel to determine the effects of varying taper ratio on the rolling and static stability characteristics of a swept wing are presented; results are also given for the effects of varying taper ratio on an unswept wing and for the effects of sweep on a tapered wing. All the models were of aspect ratio 2.61 and had NACA 0012 sections normal to the quarter-chord line. Taper ratios of 1.00, 0.50, and 0.25 and sweep angles of 0 degrees and 45 degrees were investigated.
WINGS, COMPLETE - SWEEP↗