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Investigation of effectiveness of a wing equipped with a 50-percent-chord sliding flap, a 30-percent-chord slotted flap, and a 30-percent-chord slat in deflecting propeller slipstreams downward for vertical take-off

Description: Results are presented of an investigation of the effectiveness of a wing equipped with a 50-percent-chord sliding flap and a 30-percent-chord slotted flap in deflecting a propeller slipstream downward for vertical take-off. Tests were conducted at zero forward speed in a large room and included the effects of flap deflection, proximity to the ground, a leading-edge slat, and end plates. A turning angle of about 70 degrees and a resultant force of about 100 percent of the thrust were achieved near the ground. Out of the ground-effect region, the turning angle was also about 70 degrees but the resultant force was reduced to about 86 percent of the thrust.
Date: January 1957
Creator: Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Investigation of the effects of ground proximity and propeller position on the effectiveness of a wing with large-chord slotted flaps in redirecting propeller slipstreams downward for vertical take-off

Description: Report presenting an investigation of the effects of ground proximity and propeller position on the effectiveness of a wing equipped with large-chord slotted flaps in redirecting the slipstreams from large-diameter propellers downward for vertical take-off. Results regarding the characteristics of basic configuration in the ground-effect region, effect of propeller position, comparison of characteristics of one- and two-propeller models, characteristics of modified configuration, and effect of ground on propeller characteristics are provided.
Date: March 1956
Creator: Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Investigation at zero forward speed of a leading-edge slat as a longitudinal control device for vertically rising airplanes that utilize the redirected-slipstream principle

Description: Report presenting an investigation of a leading-edge slat as a possible longitudinal control device for vertically rising airplanes that utilize the redirected-slipstream principle at zero forward speed in a static-thrust facility. A semispan wing model equipped with large-chord slotted flaps and two large-diameter overlapping propellers was used. Results regarding the effect of slat position, effect of propeller position, characteristics of the modified model, and a comparison of characteristics with one or two propellers are provided.
Date: May 1956
Creator: Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Description: An investigation has been made at high subsonic speeds of the aerodynamic'characteristics in pitch and sideslip of a l/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for small sideslip angles at Mach numbers above 0.8; however, the instability was eliminated by several different modifications.
Date: 1953~
Creator: Kuhn, Richard E. & Draper, John W.
Partner: UNT Libraries Government Documents Department

The effect of tip tanks on the rolling characteristics at high subsonic Mach numbers of a wing having an aspect ratio of 3 with quarter-chord line swept back 35 degrees

Description: Report presenting an investigation of the effect of wing-tip mounted tanks on the rolling characteristics of a wing, aspect ratio 3 with the quarter-chord line swept back 35 degrees, through a range of Mach numbers and angles of attack using the free-roll method.
Date: January 17, 1950
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department

Estimated transonic flying qualities of a tailless airplane based on a model investigation

Description: Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date: June 8, 1949
Creator: Donlan, Charles J. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Effects of Mach number and sweep on the damping-in-roll characteristics of wings of aspect ratio 4

Description: An investigation of the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, three sweep angles at the quarter chord line, and the NACA 65A006 section as determined through a range of Mach numbers and angles of attack.
Date: June 27, 1949
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department

High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0.6

Description: Report presenting an investigation of the damping-in-roll characteristics of a 35 degree sweptback wing, with and without vertical fins, through a range of Mach numbers in the high speed 7- by 10-foot tunnel utilizing a free-to-roll technique. The damping-in-roll coefficient increased in magnitude with Mach number in the manner indicated by theory and generally was found to increase in magnitude with angle of attack over the range tested.
Date: May 10, 1949
Creator: Myers, Boyd C., II & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Investigation of the aerodynamic characteristics of a model wing-propeller combination and of the wing and propeller separately at angles of attack up to 90 degrees

Description: This report presents the results of an investigation conducted in the Langley 300 mph 7- by 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
Date: 1956
Creator: Kuhn, Richard E. & Draper, John W.
Partner: UNT Libraries Government Documents Department

An investigation of a wing-propeller configuration employing large-chord plain flaps and large-diameter propellers for low-speed flight and vertical take-off

Description: Report presenting an investigation of the effectiveness of a wing equipped with large-chord plain flaps and auxiliary vanes in rotating the thrust vector of two large-diameter propellers through the large angles required for vertical take off and low-speed flight. The semispan model was equipped with a 60-percent-chord flap, a 30-percent-chord flap, and two large-diameter overlapping propellers. Results regarding static thrust conditions, tests with forward speed, and application of results are provided.
Date: December 1954
Creator: Kuhn, Richard E. & Draper, John W.
Partner: UNT Libraries Government Documents Department

Investigation of effectiveness of large-chord slotted flaps in deflecting propeller slipstreams downward for vertical take-off and low-speed flight

Description: Report presenting an investigation of the effectiveness of a wing equipped with large-chord slotted flaps in rotating the thrust vector of propellers through the angles required for vertical take-off and for flight at very low speeds in the 300 mph 7- by 10-foot tunnel. Results regarding static-thrust condition, tests with forward speed, and comparison of results for plain-flap and slotted-flap configurations are provided.
Date: January 1955
Creator: Kuhn, Richard E. & Draper, John W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combination at high subsonic speeds: Sweep series

Description: Report that is part of a program to investigate the aerodynamic characteristics in pitch, yaw, and steady roll of various model configurations with variations in the wing geometric parameters. The paper presents the aerodynamic characteristics in pitch of wing-fuselage combinations with wings of aspect ratio 4, taper ratio of 0.6, and sweep angles varying from 3.6 degrees to 60 degrees. Results regarding lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratios are provided.
Date: July 2, 1952
Creator: Wiggins, James W. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of bomb-bay configurations intended to minimize the tumbling of light-weight bombs

Description: Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine what modifications could be made to conventional bomb bays to reduce the tumbling difficulties experienced with light-weight bombs. The investigation indicated that there is a definite region of reversed flow inside the bomb bay which must be weakened or destroyed if good drops are to be obtained.
Date: June 25, 1947
Creator: Kuhn, Richard E. & Polhamus, Edward C.
Partner: UNT Libraries Government Documents Department

Some effects of propeller operation and location on ability of a wing with plain flaps to deflect propeller slipstreams downward for vertical take-off

Description: Report presenting an investigation to determine the effects of several factors associated with the propeller installation on the ability of a wing with plain flaps to deflect a propeller slipstream downward as a means for achieving vertical take-off. Some of the factors considered were propeller blade angle, mode of propeller rotation, propeller location, and ratio of wing chord to propeller diameter.
Date: January 1955
Creator: Draper, John W. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds: Aspect-ratio series

Description: Report presenting an investigation in the 7- by 10-foot tunnel to determine the effect of aspect ratio on the aerodynamic characteristics in pitch of wing-fuselage combinations with 45 degrees sweepback at the quarter-chord line and 0.6 taper ratio at high subsonic speeds. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratios are provided.
Date: April 1, 1952
Creator: Kuhn, Richard E. & Wiggins, James W.
Partner: UNT Libraries Government Documents Department

Investigation of the effectiveness of boundary-layer control by blowing over a combination of sliding and plain flaps in deflecting a propeller slipstream downward for vertical take-off

Description: An investigation was conducted in order to determine the effectiveness of blowing a jet of air over the flaps of a wing equipped with a 50-percent-chord sliding flap and a 25-percent-chord plain flap in deflecting a propeller slipstream downward for vertical take-off and the results are presented herein. The effects of a leading-edge slat, ground proximity, end plate, and propeller position were also investigated. The tests were conducted in a static-thrust facility at the Langley Aeronautical Laboratory.
Date: December 1956
Creator: Spreemann, Kenneth P. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the effectiveness of a sliding flap in deflecting a propeller slipstream downward for vertical take-off

Description: An investigation of the effectiveness of a wing equipped with a sliding flap and a leading-edge slat in deflecting a propeller slipstream downward for vertical take-off was conducted in a static-thrust facility. Results regarding the characteristics with leading-edge slat and with extended flap chord are provided.
Date: May 1956
Creator: Kuhn, Richard E. & Spreemann, Kenneth P.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation to determine the aerodynamic characteristics in steady roll of a model at high subsonic speeds

Description: Report presenting aerodynamic characteristics in steady roll on a complete model and its component parts. The model consisted of a wing and horizontal tail with a 45 degree sweepback at the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding rolling moment due to rolling, yawing moment due to rolling, and lateral force due to rolling are provided.
Date: January 21, 1953
Creator: Kuhn, Richard E. & Wiggins, James W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effects of geometric dihedral on the aerodynamic characteristics in pitch and sideslip of an unswept- and a 45 degree sweptback-wing-fuselage combination at high subsonic speeds

Description: Report presenting an investigation to determine the effects of geometric dihedral on the aerodynamic characteristics of wing-fuselage combinations with wings of aspect ratio 4, taper ratio 0.6, and angles of sweep of 3.6 and 45 degrees at the quarter-chord line. Little analysis is provided, but the results indicate that the effect of geometric dihedral on the effective-dihedral parameter is slightly larger than predicted at angles of attack of about 6 degrees.
Date: July 29, 1953
Creator: Kuhn, Richard E. & Draper, John W.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high subsonic speeds: Sweep series

Description: Report presenting an investigation in the high-speed tunnel to determine the effect of sweep on the static lateral stability characteristics of wing-fuselage combinations with wings of aspect ratio 4 and taper ratio 0.6 at high subsonic speeds. Results regarding rolling-moment characteristics and lateral-force and yawing-moment characteristics are also provided.
Date: September 9, 1952
Creator: Kuhn, Richard E. & Fournier, Paul G.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of effect of propeller slipstreams on aerodynamic characteristics of a wing equipped with a 50-percent-chord sliding flap and a 30-percent-chord slotted flap

Description: Report presenting an investigation of the aerodynamic characteristics of a wing equipped with a 50-percent-chord sliding flap and a 30-percent-chord slotted flap operating in the slipstreams of two large-diameter propellers in the 300 mph 7- by 10-foot tunnel. Large tunnel-wall effects for which there are no known correction methods were encountered in the tests. Stalling was found to occur in conditions approaching steady level flight at high-power conditions,but a leading-edge slat effectively delayed the stall.
Date: February 1957
Creator: Kuhn, Richard E. & Hayes, William C., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic loading characteristics in sideslip of a 45 degree sweptback wing with and without a fence at high subsonic speeds

Description: Report presenting an investigation of the effects of sideslip on the aerodynamic loading characteristics of a 45 degree sweptback wing of aspect ratio 4 for a range of angles of attack, angles of sideslip, and Mach numbers. The load distributions, root bending-moment coefficient, and rolling moment due to sidestep were explored.
Date: January 28, 1955
Creator: Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

A Wind-Tunnel Investigation to Determine the Effect of Various Head Designs on the Aerodynamic Characteristics in Pitch of the Army Ordnance Corps T205 3.5-Inch Heat Rocket

Description: The aerodynamic characteristics in pitch of the Army Ordnance Corps T205 3.5-inch HEAT rocket with various head designs and one fin modification have been determined at velocities of 500, 700 and 900 feet per second in the Langley high-speed 7- by 10-foot tunnel. The results presented are those of the full-scale model. Comparison of results obtained at 500 feet per second shows, in general, that for changes on the forward portion of the head the missile configurations having the greatest stability - most rearward center-of-loads location - were those having the highest drag. However, very limited comparisons indicate that the shape of the rear position of the head may be an important factor in reducing the drag and increasing the restoring moments. Generally, large increases in drag were noted for the various head designs with an increase in Mach number from 0.62 to 0.82. Pitching-moment-curve slopes increased with Mach number on all models except those having reasonably well-faired forward sections. These models showed a decrease in stability with increases in Mach number.
Date: 1952
Creator: Morrison, William D., Jr. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part I - Basic Longitudinal Stability Characteristics, TED No. NACA DE308, Part 1, Basic Longitudinal Stability Characteristics, TED No. NACA DE308

Description: The stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane have been investigated over a Mach number range from 0.40 to 0.91. Results of the basic longitudinal tests of the complete model with undeflected control surfaces are given in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Kuhn, Richard E. & Goodson, Kenneth W.
Partner: UNT Libraries Government Documents Department