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Aerodynamic characteristics of two all-movable wings tested in the presence of a fuselage at a Mach number of 1.9

Description: Report presenting testing of half-span models of two wings of different plan form as both all-movable and fixed surfaces in the presence of a half fuselage. All-movable surfaces are being considered for supersonic aircraft as possible angle-of-attack indicators, control surfaces, and all-movable wings. Results regarding the lift characteristics, center of pressure, and drag of the wings are provided.
Date: October 28, 1948
Creator: Conner, D. William
Partner: UNT Libraries Government Documents Department

Effect of reflex camber on the aerodynamic characteristics of a highly tapered moderately swept-back wing at Reynolds numbers up to 8,000,000

Description: Report presenting testing at Reynolds numbers up to 8,000,000 to determine the effectiveness of a reflex-cambered mean line in shifting the low-drag range of a sweptback wing without affecting the longitudinal stability. Two models were tested, one with symmetrical airfoil sections and one with a reflex-cambered mean line. Results regarding the effect of camber, roughness, and variation of aerodynamic characteristics with Reynolds number are provided.
Date: March 1947
Creator: Conner, D. William
Partner: UNT Libraries Government Documents Department

Investigation of high-lift and stall-control devices on a NACA 64-series 42 degree sweptback wing with and without fuselage

Description: Report presenting an investigation of a 42 degree sweptback wing of aspect ratio 4, taper ratio 0.625, and NACA 64-series airfoil sections to study several proposed devices for increasing the maximum lift coefficient and improving the longitudinal stability characteristics of sweptback wings at the stall. Some of the devices tested included leading-edge flaps and slats, trailing-edge split and extended split flaps, upper-surface split flaps, and upper-surface fences. The results regarding the characteristics of the devices and the wing-fuselage combinations are described.
Date: October 14, 1947
Creator: Graham, Robert R. & Conner, D. William
Partner: UNT Libraries Government Documents Department

Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing

Description: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Date: December 19, 1947
Creator: Conner, D. William & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Preliminary investigation at a Mach number of 1.9 and a Reynolds number of 2,200,000 of three ailerons applicable to the Bell XS-2 airplane design

Description: Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.
Date: May 25, 1948
Creator: Sivells, James C. & Conner, D. William
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Description: Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date: May 23, 1947
Creator: Neely, Robert H. & Conner, D. William
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of a 0.6-scale model of Hughes MX-904 tail surface at supersonic speeds: Several combinations of the tail with each of two foreshortened body segments

Description: An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone.
Date: July 14, 1950
Creator: Guy, Lawrence D. & Conner, D. William
Partner: UNT Libraries Government Documents Department

Effects of spoiler on airfoil pressure distribution and effects of size and location of spoilers on the aerodynamic characteristics of a tapered unswept wing of aspect ratio 2.5 at a Mach number of 1.90

Description: Report presenting an investigation in the supersonic blowdown tunnel of spoilers on two unswept wing arrangements at Mach numbers of 1.90 and 1.96. The effect of pressure-distribution tests on an unswept airfoil in the presence of a fuselage but without tip effects indicated that spoilers could be oppositely deflected in a manner similar to flap-type ailerons to obtain roll effectiveness without loss in lift. Results regarding force and moment tests are also provided.
Date: January 24, 1951
Creator: Conner, D. William & Mitchell, Meade H., Jr.
Partner: UNT Libraries Government Documents Department

Control effectiveness and hinge-moment characteristics of a tip control surface on a low-aspect-ratio pointed wing at a Mach number of 1.9

Description: Report presenting a wind-tunnel investigation of a semispan pointed wing of aspect ratio 1.7 with 60 degree leading-edge sweepback and 30 degree trailing-edge sweepforward with a control surface. The purpose of the investigation was to determine the effectiveness of flap-type controls at transonic and supersonic speeds. Results regarding the wing characteristics and control-surface characteristics are provided.
Date: October 5, 1949
Creator: Conner, D. William & May, Ellery B., Jr.
Partner: UNT Libraries Government Documents Department

Control effectiveness load and hinge-moment characteristics of a tip control surface on a delta wing at a Mach number of 1.9

Description: Report presenting a wind-tunnel investigation of a semispan delta wing with the leading-edge swept back 60 degrees. A half-delta control surface was used and testing was performed with and without fences. Results regarding the rolling effectiveness, wing characteristics, and control-surface characteristics are provided.
Date: October 7, 1949
Creator: Conner, D. William & May, Ellery B., Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of a 0.6-scale model of Hughes MX-904 tail surface at supersonic speeds: tail attached to a segment of the foreshortened body

Description: From Summary: "An investigation has been made of a partial-span model of the tail surface designed for use on the Hughes Falcon (MX-904) missile to determine the aerodynamic characteristics of the tail and elevator including elevator hinge moment. Data obtained at Mach numbers of 1.62 and 1.96 in the Langley 9- by 12-inch supersonic blowdown tunnel are presented for the condition where the tail was attached to a segment of the foreshortened body."
Date: May 4, 1950
Creator: Conner, D. William & Guy, Lawrence D.
Partner: UNT Libraries Government Documents Department

Effects of a fuselage and various high-lift and stall-control flaps on aerodynamic characteristics in pitch of an NACA 64-series 40 degree swept-back wing

Description: Report presenting wind-tunnel testing to determine the low-speed lift, drag, and pitching-moment characteristics of a 40 degree sweptback wing with high-lift and stall-control flaps and a fuselage with a fineness ratio of 10.2 to 1. Low, medium, and high-wing-fuselage combinations were tested at high Reynolds numbers. Results regarding the high-lift and stall-control flaps and wing-fuselage combinations are provided.
Date: May 26, 1947
Creator: Conner, D. William & Neely, Robert H.
Partner: UNT Libraries Government Documents Department

Effects of wing and nacelle modifications on drag and wake characteristics of a bomber-type airplane model

Description: Report presenting an investigation of a model of a large four-engine bomber to determine the effects of several wing and nacelle modifications on drag characteristics and airflow characteristics at the tail. Leading-edge gloves, trailing-edge extensions, and modified nacelle afterbodies were all tested. Results regarding flow characteristics at the wing during flight and at the landing condition, flow characteristics at the tail, and longitudinal stability characteristics are provided.
Date: December 1945
Creator: Neely, Robert H.; Fairbanks, Richard W. & Conner, D. William
Partner: UNT Libraries Government Documents Department

Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000

Description: Wind-tunnel investigations were made in pitch and yaw with and without split flaps. Presence of the fuselage had negligible effect on values of maximum lift coefficient and slope of lift curve, but caused a destabilizing shift in the rate of change of pitching moment with lift. Effects of fuselage position on drag characteristics were small for wings without flaps, but were appreciable when split flaps were on.
Date: June 10, 1947
Creator: Salmi, Reino J.; Conner, D. William & Graham, Robert R.
Partner: UNT Libraries Government Documents Department