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An investigation of the low-speed longitudinal stability characteristics of a swept-wing airplane model with two modifications to the wing-root plan form

Description: Report presenting a wind-tunnel investigation to determine the effects of two wing-root leading-edge plan-form modifications, including a notched leading-edge fillet and a rounded leading-edge fillet, on the low-speed longitudinal stability characteristics of an airplane model with a 50.7 degree sweptback wing. Results regarding stability at zero lift, variation of stability with lift coefficient, and lift and drag characteristics are provided.
Date: July 11, 1952
Creator: Kemp, William B., Jr.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of a Portion of a PV-2 Helicopter Rotor Blade

Description: From Summary: "A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the blade. Because the tunnel wall acts as a plane of symmetry, the measured aerodynamic characteristics correspond to those of an airfoil having various angles of sweepforward and sweepback. Tests were made with the vents on the lower surface open and also with the vents sealed and the internal pressure held at -20 inches of water producing an internal pressure coefficient of -1.059."
Date: March 29, 1945
Creator: Kemp, William B., Jr.
Partner: UNT Libraries Government Documents Department

Pressure distribution at low speed on a 1/4-scale Bell X-5 airplane model

Description: From Summary: "This paper contains the results of measurements at 20 degrees and 60 degrees wing sweep of the low-speed pressure distribution on the wing, wing slat, wing leading-edge fillet, and fuselage of a 1/4-scale model of a preliminary Bell X-5 airplane design. The pressure-distribution measurements were made to obtain specific aerodynamic load information for application to the Bell X-5 airplane. Some of the results, however, are useful for application to swept-wing airplanes in general."
Date: December 4, 1951
Creator: Kemp, William B., Jr. & Few, Albert G., Jr.
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

Wind-tunnel investigation of the effect of spin on the aerodynamic characteristics of a 60-millimeter T-24 mortar shell with several tail-fin configurations

Description: Report discussing an investigation to determine the effect of spin on the aerodynamic characteristics of the Army Ordnance Corps 60-millimeter T-24 mortar shell with several tail-fin configurations. Tests were performed at several airspeeds, speeds of rotation, and angles of attack. Under all test conditions, the models were statistically stable and the yawing moment increased with speed of rotation at higher angles of attack.
Date: March 21, 1957
Creator: Kemp, William B., Jr. & Hayes, William C., Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of the effect of spin on the aerodynamic characteristics of a 60-millimeter T-24 mortar shell with several tail-fin configurations

Description: Report presenting an investigation in the high-speed tunnel to determine the effect of spin on the aerodynamic characteristics of a 60-millimeter T-24 mortar shell with several different tail-fin configurations. Tests were made at a range of airspeeds, speeds of rotation, and angles of attack. Results regarding forced-spin tests, free-spin tests, and zero-spin tests are provided.
Date: March 21, 1957
Creator: Kemp, William B., Jr. & Hayes, William C., Jr.
Partner: UNT Libraries Government Documents Department

Wind-tunnel measurements of wing buffeting on 1/16-scale model of Douglas D-558-II research airplane

Description: Report presenting exploratory measurements of the fluctuations of wing bending moment during normal performance and wind-tunnel testing of a model of the Douglas D-558-II from Mach numbers 0.60 to 0.96. The effects of leading-edge chord-extensions and pylon-mounted underwing external stores were investigated. Results regarding the general nature of buffeting measurements, frequency distribution of buffeting response, interpretation of model buffeting measurements, and effects of changes in model configuration are provided.
Date: September 24, 1956
Creator: Kemp, William B., Jr. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at a Mach number of 1.38 of four wings of aspect ratio 4 having quarter-chord sweep angles of 0 degrees, 35 degrees, 45 degrees, and 60 degrees

Description: Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.
Date: October 10, 1950
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
Partner: UNT Libraries Government Documents Department

Investigation of the low-speed aerodynamic characteristics of a variable-sweep airplane model with a twisted and cambered wing

Description: Report presenting an investigation to determine the low-speed characteristics of a variable-sweep airplane model with a twisted and cambered wing. The wing was designed to have a uniform load distribution at a Mach number 1.10 and a lift coefficient of 0.25 and 50 degrees sweep. Results regarding lift characteristics, drag characteristics, lift-drag ratio, pitching-moment characteristics, dynamic pressure and downwash at the tail, effect of flaps, and lateral stability characteristics are provided.
Date: February 1, 1952
Creator: Kemp, William B., Jr.; Becht, Robert E. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

Stability and control characteristics at low speed of a 1/4-scale Bell X-5 airplane model: Longitudinal stability and control

Description: Report presenting an investigation of the low-speed longitudinal stability and control characteristics of a scale model of a Bell X-5 airplane design with various leading-edge slat and trailing-edge flap arrangements. A marked increase in stability with increasing sweep angle at low lift coefficients was noted. Results regarding the basic longitudinal characteristics, leading-edge slats, trailing-edge flaps, and longitudinal control are provided.
Date: March 14, 1950
Creator: Kemp, William B., Jr.; Becht, Robert E. & Few, Albert G., Jr.
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 II - Basic Lateral Stability Characteristics TED No. NACA DE308, Part 2, Basic Lateral Stability Charactistics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The basic lateral stability characteristics of the complete model with undeflected control surfaces are presented in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department