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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Month: February
 Collection: Technical Report Archive and Image Library
Additional experiments with flat-top wing- body combinations at high supersonic speeds

Additional experiments with flat-top wing- body combinations at high supersonic speeds

Date: February 19, 1957
Creator: Gloria, H. R.; Syvertson, C. A. & Wong, T. J.
Description: Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a full-scale turbojet engine using pentaborane fuels

Altitude performance of a full-scale turbojet engine using pentaborane fuels

Date: February 28, 1957
Creator: Useller, James W; Kaufman, Warner B & Jones, William L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability

An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability

Date: February 19, 1957
Creator: Creer, Brent Y
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical and experimental investigation of the effects of compressor interstage air bleed on performance characteristics of a 13-stage axial-flow compressor

Analytical and experimental investigation of the effects of compressor interstage air bleed on performance characteristics of a 13-stage axial-flow compressor

Date: February 8, 1957
Creator: Lucas, James G; Geye, Richard P & Calvert, Howard F
Description: Air was bled over the fifth-and tenth-stage rotor-blade rows through ports designed to pass 11 and 9 percent of the inlet flow, respectively, at 80 percent speed. Along the rated operating line the maximum speed at which rotating stall was encountered was lowered by either of these bleeds, and the stall patterns below these speeds were altered so that no dangerous resonant rotor-blade bending vibrations were excited. The combination of the two bleeds completely eliminated rotating stall to at least 50 percent speed. The compressor-discharge weight flow was decreased only at intermediate speeds, and the overall pressure ratio was affected only at intermediate speeds, and the overall pressure ratio was affected only by the combination bleed at intermediate speeds. Fifth-stage bleed increased compressor efficiency at low speeds, and tenth-stage bleed decreased efficiency at intermediate speeds.
Contributing Partner: UNT Libraries Government Documents Department
Approximate solution for streamlines about a lifting rotor having uniform loading and operating in hovering or low-speed vertical-ascent flight conditions

Approximate solution for streamlines about a lifting rotor having uniform loading and operating in hovering or low-speed vertical-ascent flight conditions

Date: February 1, 1957
Creator: Castles, Walter, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Beneficiation of Iron-Copper Ores from Kasaan Peninsula, Prince of Wales Island, Alaska

Beneficiation of Iron-Copper Ores from Kasaan Peninsula, Prince of Wales Island, Alaska

Date: February 1957
Creator: Wells, R. R.; Erspamer, E. G. & Sterling, F. T.
Description: Report issued by the Bureau of Mines over studies conducted on the beneficiation of iron-copper ores. As stated in the summary, "this report summarizes the results of laboratory testing of copper-bearing magnetite ore from the Poorman, Rush and Brown, and Copper Center deposits, Kasaan Peninsula, Prince of Wales Island, southeastern Alaska" (p. 1). This report includes tables, maps, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics and Analyses of Ninety-Two Colorado Crude Oils

Characteristics and Analyses of Ninety-Two Colorado Crude Oils

Date: February 1957
Creator: Wenger, W. J.; Whisman, M. L.; Lanum, W. J. & Ball, J. S.
Description: Report issued by the Bureau of Mines over the characteristics and properties of many different crude-oil samples from Colorado. The properties of each sample are presented. This report includes table, maps, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of combustion reactivity of ethyldecaborane fuels with typical hydrocarbon fuels on basis of spray flammability limits of fuel-rich mists and calculated lean-limit flame temperatures for fuel vapor-air systems

Comparison of combustion reactivity of ethyldecaborane fuels with typical hydrocarbon fuels on basis of spray flammability limits of fuel-rich mists and calculated lean-limit flame temperatures for fuel vapor-air systems

Date: February 27, 1957
Creator: Wise, Paul H & Lipschitz, Abraham
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of the Combustion Performance of Shell UMF, Grade C, MIL-F-5624C, Grade JP-5, Fuels in a Heavy-Duty XRJ47-W-9 Ram-Jet Engine

Comparison of the Combustion Performance of Shell UMF, Grade C, MIL-F-5624C, Grade JP-5, Fuels in a Heavy-Duty XRJ47-W-9 Ram-Jet Engine

Date: February 19, 1957
Creator: Ranscht, W. G. & Farley, J. M.
Description: Comparable combustion performance data for Shell UMF, grade C, and MIL-F-5624C, grade JP-5, fuels were obtained using a heavy-duty version of the XRJ47-W-9 ram-jet engine operated in a 2.75 Mach number free-jet facility. Data were obtained for the two fuels over a range of fuel-air ratios, engine airflows, and engine-inlet temperatures. The test conditions were selected to provide combustor-inlet temperatures. The test conditions were selected to provide combustor-inlet conditions approximately representative of those which would be encountered over a range of altitudes and flight Mach numbers. The variation of combustion efficiency with fuel-air ratio for the two fuels is compared at the several inlet conditions. The pilot-burner ignition and operating limits with both fuels are also included. In general, the combustion efficiency with Shell UMF, grade C, fuel was 1 to 4 points lower than with MIL-F-5624C, grade JP-5, fuel.
Contributing Partner: UNT Libraries Government Documents Department
Design and test of mixed-flow impellers VIII : comparison of experimental results for three impellers with shroud redesigned by rapid approximate method

Design and test of mixed-flow impellers VIII : comparison of experimental results for three impellers with shroud redesigned by rapid approximate method

Date: February 27, 1957
Creator: Osborn, Walter M; Smith, Kenneth J & Hamrick, Joseph T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Ditching investigations of dynamic models and effects of design parameters on ditching characteristics

Ditching investigations of dynamic models and effects of design parameters on ditching characteristics

Date: February 1, 1957
Creator: Fisher, Lloyd J & Hoffman, Edward L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Dynamic stability investigation of two right circular cylinders in axial free flight at Mach numbers from 0.4 to 1.7 fineness-ratio- 2.56 cylinder and fineness-ratio-4.0 cylinder with flared afterbody

Dynamic stability investigation of two right circular cylinders in axial free flight at Mach numbers from 0.4 to 1.7 fineness-ratio- 2.56 cylinder and fineness-ratio-4.0 cylinder with flared afterbody

Date: February 28, 1957
Creator: Mc Fall, J. C., Jr.
Description: Dynamic longitudinal stability of right circular cylinders in axial free flight.
Contributing Partner: UNT Libraries Government Documents Department
Effect of fiber orientation on ball failures under rolling-contact conditions

Effect of fiber orientation on ball failures under rolling-contact conditions

Date: February 1, 1957
Creator: Butler, Robert H; Bear, H Robert & Carter, Thomas L
Description: The rolling-contact fatigue spin rig was used to test bails of a bearing steel at maximum Hertz stresses of 600,000 to 750,000 psi. The effect of fiber orientation was observed with the ball track restricted to passing directly over the poles, coincident with the equator, or randomly around the ball. The polar areas were found to be weaker in fatigue than the nonpolar areas. This resulted in a much greater portion of the failures occurring in the polar areas than would be expected from a homogeneous material. The early failures are discussed.
Contributing Partner: UNT Libraries Government Documents Department
Effect of frequency and temperature on fatigue of metals

Effect of frequency and temperature on fatigue of metals

Date: February 1, 1957
Creator: Valluri, S R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effectiveness at transonic speeds of flap-type ailerons for several spanwise locations on a 4-percent-thick sweptback-wing-fuselage model with and without tails

Effectiveness at transonic speeds of flap-type ailerons for several spanwise locations on a 4-percent-thick sweptback-wing-fuselage model with and without tails

Date: February 26, 1957
Creator: Hieser, Gerald & Whitcomb, Charles F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of conical camber on the lift, drag, and pitching-moment characteristics of a triangular wing of aspect ratio 3.0

Effects of conical camber on the lift, drag, and pitching-moment characteristics of a triangular wing of aspect ratio 3.0

Date: February 19, 1957
Creator: Peterson, Victor, L & Boyd, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Equation of State and Heat Content of Uranium

Equation of State and Heat Content of Uranium

Date: February 20, 1957
Creator: Brout, Robert H.
Description: Report issued by the APDA over studies conducted on the state of uranium at different temperature and pressure. Calculations are presented for the differing pressures of uranium. This report includes tables.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers IV : performance of tapered-tip rotor configuration with reset blade angles

Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers IV : performance of tapered-tip rotor configuration with reset blade angles

Date: February 28, 1957
Creator: Montgomery, John C & Glaser, Frederick
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a method of wave-drag reduction for combinations employing quasicylindrical bodies and swept wings at supersonic speeds

Experimental investigation of a method of wave-drag reduction for combinations employing quasicylindrical bodies and swept wings at supersonic speeds

Date: February 19, 1957
Creator: Hickey, Daniel P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of ejector-nozzle metal temperatures

Experimental investigation of ejector-nozzle metal temperatures

Date: February 27, 1957
Creator: Shillito, Thomas B & Koffel, William K
Description: Metal temperatures were obtained on a full-scale ejector nozzle installed on an afterburner operating at exhaust-gas temperatures up to 3450 degrees R. A favorable afterburner-outlet temperature profile helped keep the primary-jet nozzle components cool. The ejector shroud temperatures were much more sensitive to secondary airflow than were temperatures on the primary-jet nozzle.
Contributing Partner: UNT Libraries Government Documents Department
Experimental study of the effects of scale on the absolute values of zero-lift drag of aircraft configurations at transonic speeds

Experimental study of the effects of scale on the absolute values of zero-lift drag of aircraft configurations at transonic speeds

Date: February 8, 1957
Creator: Howell, Robert R & Braslow, Albert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Exploratory investigation of the effect of wing slots and leading-edge slats on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage configuration

Exploratory investigation of the effect of wing slots and leading-edge slats on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage configuration

Date: February 8, 1957
Creator: Critzos, Chris C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight experience of the lateral stability characteristics at low lift of a 45 degree swept-wing rocket-propelled model equipped with a nonlinear yaw-rate damper system at Mach numbers from 0.76 to 1.73

Free-flight experience of the lateral stability characteristics at low lift of a 45 degree swept-wing rocket-propelled model equipped with a nonlinear yaw-rate damper system at Mach numbers from 0.76 to 1.73

Date: February 8, 1957
Creator: D'Aiutolo, Charles T; Willoughby, William W & Coltrane, Lucille C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-jet tests of a 1.1-inch-diameter supersonic ram-jet engine

Free-jet tests of a 1.1-inch-diameter supersonic ram-jet engine

Date: February 1, 1957
Creator: Judd, Joseph H & Trout, Otto F , Jr
Description: Results are presented of free-jet tests of a 1.1-inch-diameter hydrogen-burning ram-jet engine over a Mach number range from 1.42 to 2.28 and a Reynolds number range from 6.01 times 10 to the 6th power to 15.78 times 10 to the 6th power. Tests demonstrated the reliability and wide operating range of the engine and showed its suitability for installation on wind-tunnel models of airplane and missile configurations. A comparison of engine operation with combustion-chamber lengths of 3.33 and 1.51 engine diameters was made at a Mach number of 2.06. A maximum test thrust coefficient of 0.905 was obtained at fuel-air ratio of 0.034 and a Mach number of 2.06 for the engine with the 3.33-diameter combustion chamber.
Contributing Partner: UNT Libraries Government Documents Department
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