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The effect of leading-edge extensions on the longitudinal characteristics at Mach numbers up to 0.92 of a wing-fuselage-tail combination having a 40 degree sweptback wing with NACA 64A thickness distribution

Description: Report presenting a wind-tunnel investigation to determine the effects of leading-edge extensions on the longitudinal characteristics of a wing-fuselage and wing-fuselage-tail combination with a wing of 40 degrees sweepback and NACA 64A thickness distribution.
Date: January 20, 1956
Creator: Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B. & Martin, Andrew
Partner: UNT Libraries Government Documents Department

The effect of body contouring on the longitudinal characteristics at Mach numbers up to 0.92 of a wing-fuselage-tail and several wing-fuselage combinations having sweptback wings of relatively high aspect ratio

Description: Report presenting an investigation to determine the effect of a K├╝chemann type fuselage modification designed to reduce the interference velocities at the wing-fuselage junctures on the longitudinal characteristics of a wing-fuselage-tail combination and several wing-fuselage combinations. The tests were made through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million. Results regarding the 64A wing-fuselage-tail combination, four-digit wing-fuselage combinations, and effects of Mach number are provided.
Date: January 17, 1957
Creator: Sutton, Fred B. & Lautenberger, J. Walter, Jr.
Partner: UNT Libraries Government Documents Department

Effects of wing-tip turrets on the aerodynamic characteristics of a typical bomber-wing model

Description: Report presenting wind-tunnel tests up to a Mach number of 0.85 to determine the effects of wing-tip gun turrets on the aerodynamic characteristics of a typical bomber-wing model. Lift, drag, and pitching-moment data are presented for the wing alone; for the wing with the turrets in the clean condition; and for the wing and the turrets with guns and sighting equipment. The turrets had negligible effect on the lift and pitching-moment characteristics of the wing.
Date: March 28, 1949
Creator: Boddy, Lee E. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

The longitudinal characteristics at Mach numbers up to 0.92 of several wing-fuselage-tail combinations having sweptback wings with NACA four-digit thickness distributions

Description: Report presenting a wind-tunnel investigation to determine the effects of various wing-fence arrangements on the longitudinal characteristics of several wing-fuselage and wing-fuselage-tail combinations with sweptback wings with NACA four-digit thickness distributions. Testing occurred with wings of several degrees of sweepback and a horizontal tail at several tail heights. Results regarding fence development, wing-fuselage combinations, and wing-fuselage-tail combinations are provided.
Date: March 24, 1955
Creator: Sutton, Fred B. & Dickson, Jerald K.
Partner: UNT Libraries Government Documents Department

A comparison of the longitudinal aerodynamic characteristics at Mach numbers up to 0.94 of swept back wings having NACA 4-digit or NACA 64A thickness distributions

Description: Report presenting a wind-tunnel investigation on two series of twisted and cambered wings, which were identical except for wing section, to compare the effects of NACA 4-digit and NACA 64A chordwise distributions of thickness on the longitudinal aerodynamic characteristics of the wings. Results regarding the low-speed results, high-speed results, and flow studies are provided.
Date: August 23, 1954
Creator: Sutton, Fred B. & Dickson, Jerald K.
Partner: UNT Libraries Government Documents Department

The effect of wing height on the longitudinal characteristics at high subsonic speeds of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and NACA four digit thickness distribution

Description: Report presenting an investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. Testing occurred at a range of Mach and Reynolds numbers.
Date: May 25, 1955
Creator: Dickson, Jerald K. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

The Effect of Wing Fences on the Longitudinal Characteristics at High Subsonic Speeds of a Wing-Fuselage-Tail Combination Having a Wing With 40 Degrees of Sweepback and NACA Four-Digit Thickness Distribution

Description: Report presenting a wind-tunnel investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and a wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. The effects of wing height on the longitudinal characteristics of the model were small.
Date: May 25, 1955
Creator: Dickson, Jerald K. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

The Effects of Operating Propellers on the Longitudinal Characteristics at High Subsonic Speeds of a Four-Engine Tractor Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10

Description: Report presenting an investigation at high subsonic speeds to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Testing was conducted at a range of angles of attack, propeller thrust coefficients, Mach numbers, and Reynolds numbers.
Date: January 7, 1954
Creator: Sutton, Fred B. & Demele, Fred A.
Partner: UNT Libraries Government Documents Department

The Effects of Increasing the Leading-Edge Radius and Adding Forward Camber on the Aerodynamic Characteristics of a Wing With 35 Degrees of Sweepback

Description: Report presenting a wind-tunnel investigation to determine the effects of a section modification on the aerodynamic characteristics of a wing with 35 degrees of sweepback. The wing was modified by increasing the leading-edge radius of the NACA 64A010 section and adding a small amount of camber to the forward portion of the chord. Lift, drag, pitching-moment, and trailing-edge-flap hinge-moment characteristics of the modified wing are compared with results from the original wing.
Date: February 9, 1951
Creator: Demele, Fred A. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

The Effect of an Operating Propeller on the Aerodynamic Characteristics of a 1/10-Scale Model of the Lockheed XFV-1 Airplane at High Subsonic Speeds (TED No. NACA DE-377)

Description: "An investigation was conducted in the Ames 12-foot pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a 1/19-scale model of the Lockheed XFV-1 airplane. Several full-scale power conditions were simulated at Mach numbers from 0.50 to 0.92; the.Reynolds number was constant at 1.7 million. Lift, longitudinal force, pitch, roll, and yaw characteristics, determined with and without power, are presented for the complete model and for various combinations of model components" (p. 1).
Date: May 6, 1952
Creator: Sutton, Fred B. & Buell, Donald A.
Partner: UNT Libraries Government Documents Department

The Effect of an Operating Propeller on the Aerodynamic Characteristics at High Subsonic Speeds of a Model of a Vertical-Rising Airplane Having an Unswept Wing of Aspect Ratio 3

Description: Report presenting an investigation in the pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a model of a vertical-rising airplane with an unswept wing with an aspect ratio of 3. Lift, longitudinal force, pitch, and roll characteristics, with and without power, are presented for the complete model and various combinations of model components.
Date: November 15, 1954
Creator: Sutton, Fred B. & Buell, Donald A.
Partner: UNT Libraries Government Documents Department

Analysis of Wind-Tunnel Tests to a Mach Number of 0.90 of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10

Description: Report presenting an investigation at speeds of up to Mach number 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration with a 40 degree swept wing with an aspect ratio of 10. Results regarding low-speed conditions, high-speed conditions, components of lift, effect of configuration changes, longitudinal stability, and the reduction of adverse effects of propellers on stability are provided.
Date: September 1956
Creator: Edwards, George G.; Buell, Donald A.; Demele, Fred A. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10

Description: Report presenting a wind-tunnel investigation to provide data for the study of the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration with a wing of 40 degrees of sweepback and an aspect ratio of 10. Coefficients of lift, longitudinal force, pitching moment, propeller thrust, and propeller power are presented in tabular form for various values of advance ratio at constant angles of attack.
Date: September 1956
Creator: Edwards, George G.; Dickson, Jerald K.; Sutton, Fred B. & Demele, Fred A.
Partner: UNT Libraries Government Documents Department