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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Collection: Technical Report Archive and Image Library
Transonic investigation of effects of spanwise and chordwise external store location and body contouring on aerodynamic characteristics of 45 degree sweptback wing-body configuration

Transonic investigation of effects of spanwise and chordwise external store location and body contouring on aerodynamic characteristics of 45 degree sweptback wing-body configuration

Date: September 25, 1957
Creator: Pearson, Albin O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic investigation of internal-flow characteristics of a square-shaped scoop inlet mounted at three chordwise positions above a high 45 degree sweptback wing and body combination

Transonic investigation of internal-flow characteristics of a square-shaped scoop inlet mounted at three chordwise positions above a high 45 degree sweptback wing and body combination

Date: April 17, 1957
Creator: Keith, Arvid L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A transonic investigation of the mass-flow and pressure recovery characteristics of several types of auxiliary air inlets

A transonic investigation of the mass-flow and pressure recovery characteristics of several types of auxiliary air inlets

Date: April 10, 1957
Creator: Dennard, John S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic loads characteristics of a 3-percent-thick 60 degree delta-wing-body combination

Transonic loads characteristics of a 3-percent-thick 60 degree delta-wing-body combination

Date: May 28, 1957
Creator: Swihart, John M & Foss, Willard E , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic Wind-Tunnel Investigation of Static Longitudinal Stability and Control Characteristics and Drag of a 0.05-Scale Model of the Chance Vought XF8U-3 Airplane : TED No. NACA AD 3133

Transonic Wind-Tunnel Investigation of Static Longitudinal Stability and Control Characteristics and Drag of a 0.05-Scale Model of the Chance Vought XF8U-3 Airplane : TED No. NACA AD 3133

Date: September 20, 1957
Creator: Pierpont, P Kenneth
Description: A transonic wind-tunnel investigation was made in the Langley 8-foot transonic pressure tunnel at the request of the Bureau of Aeronautics, Department of the Navy, of the static longitudinal stability and control characteristics and drag of a 0.05-scale model of the Chance Vought XF8U-3 airplane at Mach numbers from 0.80 to 1.20 with an average Reynolds number of 2.6 x 10(exp 6). The investigation included effects of the addition of the ventral fins, extension and removal of the missiles, deflection of the speed brake, addition of a fuselage fairing near the wing leading edge, and longitudinal control effectiveness. The model was statically stable throughout most of the range of positive lift coefficients, but some loss in horizontal-tail effectiveness may be expected near zero lift and a Mach number of 1.0. Installation of the ventral fins Increased the longitudinal stability from 2 to percent at a small drag-coefficient penalty. The speed-brake drag increment decreased with increasing angle of attack, and trim changes of about 2deg at low angles of attack may be expected at supersonic speeds. The increase in subsonic drag coefficient caused by extension of the three missiles to firing position was more than three times as great as the ...
Contributing Partner: UNT Libraries Government Documents Department
Transonic wind-tunnel investigation of static-pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane

Transonic wind-tunnel investigation of static-pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane

Date: August 6, 1957
Creator: Brooks, Joseph D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic wind-tunnel investigation of static- pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane

Transonic wind-tunnel investigation of static- pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane

Date: August 6, 1957
Creator: Brooks, J. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic wind-tunnel investigation of the low-lift aerodynamic characteristics, including the effects of leading edge droop and thickness, of a thin trapezoidal wing in combination with basic and indented bodies

Transonic wind-tunnel investigation of the low-lift aerodynamic characteristics, including the effects of leading edge droop and thickness, of a thin trapezoidal wing in combination with basic and indented bodies

Date: October 16, 1957
Creator: Kelly, Thomas C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transonic wind tunnel tests of the launch, jettison, and longitudinal characteristics of an airplane and missile model combination

Transonic wind tunnel tests of the launch, jettison, and longitudinal characteristics of an airplane and missile model combination

Date: November 20, 1957
Creator: Cleary, J. W.; Dewey, C. F., Jr. & Frank, J. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Turbulence in the Wake of a Thin Airfoil at Low Speeds

Turbulence in the Wake of a Thin Airfoil at Low Speeds

Date: January 1, 1957
Creator: Campbell, George S.
Description: Experiments have been made to determine the nature of turbulence in the wake of a two-dimensional airfoil at low speeds. The experiments were motivated by the need for data which can be used for analysis of the tail-buffeting problem in aircraft design. Turbulent intensity and power spectra of the velocity fluctuations were measured at a Reynolds number of 1.6 x 10(exp 5) for several angles of attack. Total-head measurements were also obtained in an attempt to relate steady and fluctuating wake properties. Mean-square downwash was found to have nearly the same dependence on vertical position in the wake as that shown by total-head loss. For this particular wing, turbulent intensity, integrated across the wake, increased roughly as the 3/2 power of the drag coefficient. Power-spectrum measurements indicated a decrease in frequency as wing angle of attack was increased. The average frequency in the wake was proportional to the ratio of mean wake velocity to wake width.
Contributing Partner: UNT Libraries Government Documents Department