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A comparison of the aerodynamic characteristics at transonic speeds of four wing-fuselage configurations as determined from different test techniques

Description: Report presenting a comparison of the high-speed aerodynamic characteristics of a family of four wing-fuselage configurations with four different degrees of sweepback as determined from transonic-bump model tests in the 7- by 10-foot tunnel, sting-supported model tests in the 8-foot tunnel, and the 7-foot by 10-foot tunnel.
Date: October 4, 1950
Creator: Donlan, Charles J.; Myers, Boyd C., II & Mattson, Axel T.
Partner: UNT Libraries Government Documents Department
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An experimental investigation of boundary interference on force and moment characteristics of lifting models in the Langley 16- and 8-foot transonic tunnels

Description: Report presenting testing of a wing-fuselage force model configuration and the fuselage alone at angles of attack up to 32 degrees in the 16-foot transonic tunnel. Results regarding the force and moment characteristics, base pressures, and shadowgraph pictures are provided.
Date: February 24, 1953
Creator: Whitcomb, Charles F. & Osborne, Robert S.
Partner: UNT Libraries Government Documents Department
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A transonic wind-tunnel investigation of the characteristics of a twisted and cambered 45 degree sweptback wing-fuselage configuration

Description: Report presenting an investigation in the 8-foot transonic tunnel to determine the effects of twist and camber on the aerodynamic characteristics of a sweptback wing-fuselage configuration. The wing had 45 degrees sweepback of the 0.25 chord, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A-series airfoil sections with 6-percent thickness distribution parallel to the plane of symmetry. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics … more
Date: December 19, 1952
Creator: Harrison, Daniel E.
Partner: UNT Libraries Government Documents Department
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Tests in the Ames 40- by 80-Foot Wind Tunnel of Two Airplane Models Having Aspect Ratio 2 Trapezoidal Wings of Taper Ratios 0.33 and 0.20

Description: Memorandum presenting tests of two airplane models with trapezoidal wings of aspect ratio 2 and taper ratios of 0.33 and 0.20. For each model, a fuselage with a fineness ratio of 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail was used. Tests of the wing-fuselage vertical-tail configuration and of the complete airplane model were made for both models.
Date: February 16, 1953
Creator: Franks, Ralph W.
Partner: UNT Libraries Government Documents Department
open access

Method of Estimating the Stick-Fixed Longitudinal Stability of Wing-Fuselage Configurations Having Unswept or Swept Wings

Description: Memorandum presenting a method for calculating the stick-fixed longitudinal stability of a wing-fuselage configuration at subcritical Mach numbers. The method applies to unswept- and swept-wing configurations. The stability parameters estimated by the method show reasonable agreement with the experimental values for the 23 configurations used in the comparison.
Date: January 22, 1952
Creator: McLaughlin, Milton D.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation at High Subsonic Speeds to Determine the Rolling-Stability Derivatives of Three Wing-Fuselage Configurations

Description: Memorandum presenting rolling-stability derivatives for three wing configurations, which were tested on the same fuselage, over a range of Mach numbers and angles of attack. The wings were assorted plan-form configurations of current interest and were not part of a geometrically related series of plan forms. Results regarding basic damping-in-roll results, estimation of rolling derivatives, and estimated effects of Reynolds number are provided.
Date: October 27, 1954
Creator: Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department
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Effects of wing elasticity on the aerodynamic characteristics of a 45 degree sweptback-wing-fuselage combination measured in the Langley 8-foot transonic tunnel

Description: Report presenting testing of a wing-fuselage configuration with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections in aluminum and steel at a range of Mach numbers and angles of attack to determine effects of wing elasticity. Results regarding the relative effects of bending and torsion, wing-tip twist, aerodynamic characteristics, and some theoretical considerations are provided.
Date: September 17, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wing Investigation in the Langley 8-Foot High-Speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-Fuselage Configuration Having a Wing of 35 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Description: Report presenting an investigation to determine the aerodynamic characteristics of a wing-fuselage configuration with a wing with quarter-chord line swept back 35 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Lift, drag, and pitching-moment characteristics, downwash angles, and wake characteristics for various angles of attack and Mach numbers are provided.
Date: November 15, 1950
Creator: Henry, Beverly Z., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Distribution of Lift, Drag, and Pitching Moment Between the Wing and Fuselage of a 1/30-Scale Semispan Model of the Bell X-5 Airplane at a Mach Number of 1.24 by the NACA Wing-Flow Method

Description: Report presenting an investigation at a Mach number of 1.24 to determine the distribution of lift, drag, and pitching moment between the wing and fuselage of a scale semispan model of the Bell X-5 airplane. Lift, drag, pitching moments, and wing bending moments were obtained for various angles of attack for 40 through 60 degrees sweptback duralumin wings in the presence of, but detached from, the fuselage.
Date: January 16, 1952
Creator: Silsby, Norman S. & Morris, Garland J.
Partner: UNT Libraries Government Documents Department
open access

Effect on Transonic and Supersonic Drag of a Fuselage Protuberance of an Essential Unswept Wing-Fuselage Combination

Description: "An investigation of the effect on transonic and supersonic drag of a fuselage protuberance designed to improve the overall longitudinal distribution of cross-sectional area of an essentially unswept wing-fuselage combination has been made with free-flight rocket models. The wing-fuselage configuration was tested with and without a fuselage protuberance designed to relieve the steep area gradient over the rear portion of the wing" (p. 1).
Date: January 5, 1954
Creator: Sandahl, Carl A.
Partner: UNT Libraries Government Documents Department
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