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An investigation of the low-speed stability and control characteristics of a 1/10-scale model of the McDonnell XF3H-1 airplane

Description: Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date: October 11, 1951
Creator: Draper, John W.
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

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

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

Effects of symmetric and asymmetric thrust reversal on the aerodynamic characteristics of a model of a twin-engine airplane

Description: Report presenting an investigation using a twin-engine airplane model in the 300 mph 7- by 10-foot tunnel to determine the magnitude of the changes in aerodynamic forces and moments resulting from propeller pitch reversal. The effects of both positive and negative thrust coefficients were investigated at Reynolds number 550,000. Results regarding the analysis of effects of symmetric and asymmetric thrust on the aerodynamic characteristics and typical performance and control estimates are provided.
Date: September 1953
Creator: Goodson, Kenneth W. & Draper, John W.
Partner: UNT Libraries Government Documents Department

The effects of stability of spin-recovery tail parachutes on the behavior of airplanes in gliding flight and in spins

Description: Note presenting an investigation with airplane models in the free-flight and 20-foot free-spinning tunnels to determine whether a stable parachute could be safely towed behind an airplane in flight and whether it would be effective as a spin-recovery device. Results regarding the parachute characteristics, behavior in gliding flight, spin-recovery effectiveness, and effect of increasing towline length are provided.
Date: May 1950
Creator: Scher, Stanley H. & Draper, John 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

Free-Flight-Tunnel Investigation of the Effect of the Fuselage Length and the Aspect Ratio and Size of the Vertical Tail on Lateral Stability and Control

Description: Report presenting tests in the free-flight tunnel to determine the effect of the fuselage length and the aspect ratio and size of the vertical tail on lateral stability and control. Fuselages of two different lengths and various vertical tail surfaces were used on a powered model in the investigation. Results regarding the test conditions, flight tests, and force tests are provided.
Date: April 1943
Creator: Shortal, Joseph A. & Draper, John W.
Partner: UNT Libraries Government Documents Department

Investigation of the Stability and Control Characteristics of a 1/10-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley Free-Flight Tunnel, TED No. NACA DE306

Description: At the request of the Bureau of Aeronautics, Navy Department, a stability and control investigation of a 1/10-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley free-flight tunnel. Results of force end flight tests to determine the power-off stability and control characteristics of the model with slats retracted and extended are presented herein. The longitudinal and lateral stability characteristics were satisfactory for both the slats retracted and extended conditions over the lift range up to the stall. With the slats retracted, the stall was fairly gentle but the model rolled off out of control. With the slats extended, control could be maintained at the stall so that the wings could be kept level even as the model dropped.
Date: 1948
Creator: Draper, John W. & Hewes, Donald E.
Partner: UNT Libraries Government Documents Department

An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane : TED No. NACA DE 344

Description: At the request of the Bureau of Aeronautics, Navy Department, an investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the McDonnell XF3H-1 airplane has been made in the Langley free-flight tunnel. Flight tests of the model in the clean and in the slats-and-flaps-extended conditions were made over a lift-coefficient range from about 0.5 through the stall. Only low-altitude conditions were simulated and no attempt was made to determine the effect on the stability characteristics of freeing the controls. Static force tests were made to determine the static longitudinal and lateral stability derivatives and rotary force tests were made to determine the dynamic rolling derivatives. Calculations were also made to determine the damping of the lateral oscillation for correlation with the flight results.
Date: October 11, 1951
Creator: Draper, John W.
Partner: UNT Libraries Government Documents Department