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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15291 - 15300 of 18,906
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Static Stability and Control of Hypersonic Gliders

Static Stability and Control of Hypersonic Gliders

Date: July 7, 1958
Creator: Rainey, R. W.
Description: Static stability and control of hypersonic gliders.
Contributing Partner: UNT Libraries Government Documents Department
Attenuation in Water of Radiation from the Bulk Shielding Reactor: Measurements of the Gamma-Ray Dose Rate, Fast Neutron Dose Rate, and Thermal-Neutron Flux

Attenuation in Water of Radiation from the Bulk Shielding Reactor: Measurements of the Gamma-Ray Dose Rate, Fast Neutron Dose Rate, and Thermal-Neutron Flux

Date: July 8, 1958
Creator: Oak Ridge National Laboratory
Description: Report issued by the Oak Ridge National Laboratory displaying a single chart showing measurements of the gamma-ray, fast-neutron, and thermal-neutron dose rates.
Contributing Partner: UNT Libraries Government Documents Department
Effects of vertical location of the wing and horizontal tail on the static lateral and directional stability of a trapezoidal-wing airplane model at Mach numbers of 1.41 and 2.01

Effects of vertical location of the wing and horizontal tail on the static lateral and directional stability of a trapezoidal-wing airplane model at Mach numbers of 1.41 and 2.01

Date: July 9, 1958
Creator: Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic characteristics of outboard ailerons on a 4-percent-thick 30 degree sweptback wing, including some effects of aileron trailing-edge thickness and aerodynamic balance

Transonic characteristics of outboard ailerons on a 4-percent-thick 30 degree sweptback wing, including some effects of aileron trailing-edge thickness and aerodynamic balance

Date: July 9, 1958
Creator: Whitcomb, Charles F & Critzos, Chris C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of boattail area contouring and simulated turbojet exhaust on the loading and fuselage-tail component drag of a twin-engine fighter-type airplane model

Effects of boattail area contouring and simulated turbojet exhaust on the loading and fuselage-tail component drag of a twin-engine fighter-type airplane model

Date: July 14, 1958
Creator: Foss, W. E., Jr.; Lee, E. E., Jr. & Runckel, J. F.
Description: Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.
Contributing Partner: UNT Libraries Government Documents Department
Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model

Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model

Date: July 14, 1958
Creator: Foss, Willard E , Jr; Runckel, Jack F & Lee, Edwin E , Jr
Description: An investigation of a twin-engine fighter-type airplane model has been conducted in the Langley 16-foot transonic tunnel to determine the effect on drag of a fuselage volume addition incorporating streamline contouring and more extensive boattailing of the engine shrouds. The effect of hot exhausts from the turbojet engines was simulated with hydrogen peroxide gas generators using scaled nonafterburning engine nozzles. Afterbody pressure distributions, base drag coefficients, and forces on the fuselage-tail configurations are presented at Mach numbers from 0.80 to 1.05 angles of attack of 0 degree and 4 degrees for jet pressure ratios from 1 to 7. The effect of jet operation on both the basic and modified models was generally to decrease base pressures but to increase most other afterbody pressures and, therefore, to result in an overall decrease in fuselage-tail component drag. The addition of volume to the basic model reduced the base drag coefficient by 0.0010 with the jets off and 0.0018 at a typical cruise operating condition of a jet pressure ratio of 3, a Mach number of 0.85, and an angle of attack of 4 degrees. The overall jet-off reduction in fuselage-tail component drag due to the volume addition was a maximum of 0.0040 ...
Contributing Partner: UNT Libraries Government Documents Department
Hydrodynamic characteristics of a model of a proposed six-engine hull-type seaplane designed for supersonic flight

Hydrodynamic characteristics of a model of a proposed six-engine hull-type seaplane designed for supersonic flight

Date: July 14, 1958
Creator: Coffee, Claude W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Hydrodynamic characteristics of a model of a proposed six-engine hull-type seaplane designed for supersonic flight

Hydrodynamic characteristics of a model of a proposed six-engine hull-type seaplane designed for supersonic flight

Date: July 14, 1958
Creator: Coffee, C. W., Jr.
Description: Hydrodynamic characteristics of six-engine hull-type seaplane model designed for supersonic flight.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile with Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51

Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile with Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51

Date: July 14, 1958
Creator: Presnell, John G., Jr.
Description: A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected. Directional stability data were obtained at M=3.51 for angles of attack of approximately 0 deg and 10 deg. These data, with summary data and typical schlieren photographs, are presented with only a brief analysis. The data indicate that the controls are effective throughout the Mach number range and lift-coefficient range (CL = -0.15 to 0.7, approximately) of the tests. There is a severe break in the pitching-moment curve at M=2.29 which might result in a pitch-up condition in flight, and also a large forward movement of the aerodynamic center with increasing Mach number that produces neutral longitudinal stability at ...
Contributing Partner: UNT Libraries Government Documents Department
Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research              airplane at transonic speeds

Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research airplane at transonic speeds

Date: July 15, 1958
Creator: Keener, Earl R; Mcleod, Norman J & Taillon, Norman V
Description: None
Contributing Partner: UNT Libraries Government Documents Department