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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Collection: Technical Report Archive and Image Library
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
Turbulence measurements in multiple interfering air jets

Turbulence measurements in multiple interfering air jets

Date: December 1, 1957
Creator: Laurence, James C & Benninghoff, Jean M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two-dimensional airfoil characteristics  of four NACA 6A-series airfoils at transonic Mach numbers up to 1.25

Two-dimensional airfoil characteristics of four NACA 6A-series airfoils at transonic Mach numbers up to 1.25

Date: August 6, 1957
Creator: Ladson, Charles L
Description: A two-dimensional wind-tunnel investigation of the flow and force characteristics of four NACA 6A-series airfoils with thickness ratios of 4, 6, and 9 percent has been conducted in the Langley airfoil test apparatus at at transonic Mach numbers between 0.8 and 1.25. The Reynolds number range for these tests varied from 2.6 x 10(6) to 2.8 x 10(6). As was expected, the airfoils exhibited a smooth transition in force coefficients from a Mach number of 1.0 to the values obtained at the higher speeds. Lift-curve slope and maximum lift-drag ratio correlated very well on a basis of the transonic similarity laws at Mach numbers above 1.0, but below that value the correlation was not good. The measured effect of thickness on the drag coefficient at supersonic speeds was less than that predicted by the transonic similarity laws. Good correlation of the drag coefficients was obtained by reducing the exponent of the thickness term from the theoretical value of 1.67 to 1.50. This change did not affect the correlation at subsonic speeds, which was good for either case.
Contributing Partner: UNT Libraries Government Documents Department
Two-dimensional cascade tests of NACA 65-(C(sub zeta)(sub o))A(sub 10))10 blade sections at typical compressor hub conditions for speeds up to choking

Two-dimensional cascade tests of NACA 65-(C(sub zeta)(sub o))A(sub 10))10 blade sections at typical compressor hub conditions for speeds up to choking

Date: October 23, 1957
Creator: Emery, James C & Dunavant, James C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two-dimensional transonic investigation of flows and forces on a 9-percent-thick airfoil with 30-percent-chord flap

Two-dimensional transonic investigation of flows and forces on a 9-percent-thick airfoil with 30-percent-chord flap

Date: February 19, 1957
Creator: Lindsey, Walter F & Pitts, Robert G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two factors influencing temperature distributions and thermal stresses in structures

Two factors influencing temperature distributions and thermal stresses in structures

Date: June 1, 1957
Creator: Brooks, William A , Jr; Griffith, George E & Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
United States Earthquakes, 1957

United States Earthquakes, 1957

Date: 1957
Creator: unknown
Description: Report discussing earthquake activity in the United States during 1957. The report is broken down by regions and has sections for specific earthquakes.
Contributing Partner: UNT Libraries Government Documents Department