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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Month: May
 Collection: Technical Report Archive and Image Library
An air-borne target simulator for use with scope-presentation type fire-control systems

An air-borne target simulator for use with scope-presentation type fire-control systems

Date: May 10, 1957
Creator: Foster, John V; Fulcher, Elmer C & Heinle, Donovan R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a turbojet engine using pentaborane fuel

Altitude performance of a turbojet engine using pentaborane fuel

Date: May 20, 1957
Creator: Sivo, Joseph N
Description: A full-scale turbojet engine having a two-stage turbine was operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. The specific fuel consumption was initially reduced 32 percent below that obtained with gasoline fuel; however, the occurrence of a 25-percent reduction in net thrust after 8 minutes of operation resulted in a subsequent increase in specific fuel consumption to a value only 11.5 percent lower than that for gasoline.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a turbojet engine using pentaborane fuel

Altitude performance of a turbojet engine using pentaborane fuel

Date: May 20, 1957
Creator: Sivo, J. N.
Description: Altitude performance of turbojet engine using pentaborane fuel.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Date: May 7, 1957
Creator: Slone, Henry O & Donoughe, Patrick L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of vertical-tail loads measured in flight on a swept-wing bomber airplane

An analysis of vertical-tail loads measured in flight on a swept-wing bomber airplane

Date: May 7, 1957
Creator: Mcgowan, William A & Cooney, T V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The application of matrix methods to coordinate transformations occurring in systems studies involving large motions of aircraft

The application of matrix methods to coordinate transformations occurring in systems studies involving large motions of aircraft

Date: May 1, 1957
Creator: Doolin, Brian F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Appraisal of the hazards of friction-spark ignition of aircraft crash fires

Appraisal of the hazards of friction-spark ignition of aircraft crash fires

Date: May 1, 1957
Creator: Campbell, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bonded lead monoxide films as solid lubricants for temperatures up to 1250 F

Bonded lead monoxide films as solid lubricants for temperatures up to 1250 F

Date: May 7, 1957
Creator: Sliney, Harold E & Johnson, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cascade investigation of a related series of 6-percent-thick guide-vane profiles and design charts

Cascade investigation of a related series of 6-percent-thick guide-vane profiles and design charts

Date: May 1, 1957
Creator: Dunavant, James C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a 40 degree cone for measuring Mach number, total pressure, and flow angles at supersonic speeds

Characteristics of a 40 degree cone for measuring Mach number, total pressure, and flow angles at supersonic speeds

Date: May 1, 1957
Creator: Centolanzi, Frank J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for the analysis of flow in a whirling duct

Charts for the analysis of flow in a whirling duct

Date: May 1, 1957
Creator: Makofski, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The EBWR: Experimental Boiling Water Reactor

The EBWR: Experimental Boiling Water Reactor

Date: May 1957
Creator: Argonne National Laboratory
Description: Report issued by the Argonne National Laboratory discussing the Experimental Boiling Water Reactor (EBWR) power plant. Designs of the final EBWR power plant are presented. This report includes tables, illustrations, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
Effect of bluntness on transition for a cone and a hollow cylinder at Mach 3.1

Effect of bluntness on transition for a cone and a hollow cylinder at Mach 3.1

Date: May 1, 1957
Creator: Brinich, Paul F & Sands, Norman
Description: Bluntness was more effective in displacing transition downstream on a cylinder than on a cone. The downstream displacement of transition is related to the formation of a shock layer within which the Reynolds and Mach numbers are reduced and to pressure gradients that exist over the forward part of the model. Round bluntness in general had a favorable effect, whereas sharp-cornered flat bluntness above a certain size had unfavorable effects on the location of the transition point.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Fatigue Crack on Static Strength: 2014-T6, 2024-T4, 6061-T6, 7075-T6 Open-Hole Monobloc Specimens

Effect of Fatigue Crack on Static Strength: 2014-T6, 2024-T4, 6061-T6, 7075-T6 Open-Hole Monobloc Specimens

Date: May 1, 1957
Creator: Nordmark, Glenn E. & Eaton, Ian D.
Description: Static tensile test results are presented for specimens of 2014-T6, 2024-T4, 6061-T6, and 7075-T6 aluminum alloy containing fatigue cracks. The results are found to be in good agreement with the results reported for similar tests from other sources. The results indicate that the presence of a fatigue crack reduced the static strength, in all cases, by an amount larger than the corresponding reduction in net area; the 6061-T6 alloy specimens were least susceptible to the crack and the 7075-T6 alloy specimens were most susceptible. It is indicated that a 7075-T6 specimen may develop as little as one-third of the expected static tensile strength when the fatigue crack was consumed only one-fourth of the original area. It was found that the static strength was substantially higher for specimens which had stop holes drilled at the end of the fatigue crack.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Some External Crosswise Stiffeners on the Heat Transfer and Pressure Distribution on a Flat Plate at Mach Numbers of 0.77, 1.39, and 1.98. Coord. No. AF-AM-69

Effect of Some External Crosswise Stiffeners on the Heat Transfer and Pressure Distribution on a Flat Plate at Mach Numbers of 0.77, 1.39, and 1.98. Coord. No. AF-AM-69

Date: May 14, 1957
Creator: Carter, Howard S.
Description: The heat transfer and pressures on the surfaces of several flat-plate models with various external crosswise stiffener arrangements are presented. The tests were made in a free jet at Mach numbers of 0.77, 1.39, and 1.98 for Reynolds numbers of 3 x 10(exp 6), 7 x 10(exp 6), and 14 x 10(exp 6), respectively, based on a length of 1 foot. The addition of external crosswise stiffeners to the flat-plate models caused large pressure and heat-transfer variations on the surfaces of the models.
Contributing Partner: UNT Libraries Government Documents Department
Effect of standing transverse acoustic oscillations on fuel-oxidant mixing in cylindrical combustion chambers

Effect of standing transverse acoustic oscillations on fuel-oxidant mixing in cylindrical combustion chambers

Date: May 1, 1957
Creator: Mickelsen, William R
Description: Vapor fuel-oxidant mixing is analyzed for standing transverse acoustic fields simulating those existing in screeching or screaming combustors. The additional mixing due to the acoustic field is shown to be a function of sound pressure and frequency, stream velocity, and turbulence. The effects of these parameters are shown graphically for a realistic range of combustor conditions. The fuel-oxidant ratio at various combustor stations is shown to have a cyclic fluctuation which is in phase with the pressure fluctuations. Possible mechanisms contributing to screech and scream are discussed.
Contributing Partner: UNT Libraries Government Documents Department
Evaluation of Various Types of Personnel Shelters Exposed to an Atomic Explosion

Evaluation of Various Types of Personnel Shelters Exposed to an Atomic Explosion

Date: May 10, 1957
Creator: Vortman, Luke J.
Description: Report describing experiments to evaluate the effectiveness of various kinds of shelters to protect occupants from nuclear and thermal radiation and blast effects.
Contributing Partner: UNT Libraries Government Documents Department
Experimental evaluation of swirl can elements for hydrogen fuel combustor

Experimental evaluation of swirl can elements for hydrogen fuel combustor

Date: May 13, 1957
Creator: Friedman, R.; Jones, R. E. & Rayle, W. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental evaluation of 'swirl-can' elements for hydrogen-fuel combustor

Experimental evaluation of 'swirl-can' elements for hydrogen-fuel combustor

Date: May 13, 1957
Creator: Rayle, Warren, D; Jones, Robert E & Friedman, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental influence coefficients and vibration modes of a built-up 45 degree delta-wing specimen

Experimental influence coefficients and vibration modes of a built-up 45 degree delta-wing specimen

Date: May 1, 1957
Creator: Kordes, Eldon E; Kruszewski, Edwin T & Weidman, Deene J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a five-stage axial-flow research compressor with transonic rotors in all stages IV : blade-element performance

Experimental investigation of a five-stage axial-flow research compressor with transonic rotors in all stages IV : blade-element performance

Date: May 7, 1957
Creator: Sandercock, Donald M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of deposition by boron-containing fuels in turbojet combustor

Experimental investigation of deposition by boron-containing fuels in turbojet combustor

Date: May 10, 1957
Creator: Kaufman, Warner B; Branstetter, J Robert & Lord, Albert M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental study of heat transfer to small cylinders in a subsonic, high-temperature gas stream

Experimental study of heat transfer to small cylinders in a subsonic, high-temperature gas stream

Date: May 1, 1957
Creator: Glawe, George E & Johnson, Robert C
Description: A Nusselt-Reynolds number relation for cylindrical thermocouple wires in crossflow was obtained from the experimental determination of time constants. Tests were conducted in exhaust gas over a temperature range of 2000 to 3400 R, a Mach number range of 0.3 to 0.8, and a static-pressure range from 2/3 to 1-1/3 atmospheres, yielding a Reynolds number range of 450 to 3000. The correlation obtained is Nu=(0.428 plus or minus 0.003) times the square root of Re* with average deviations of a single observation of 8.5 percent. This relation is the same as one previously reported for room-temperature conditions.
Contributing Partner: UNT Libraries Government Documents Department
Extended operation of turbojet engine with pentaborane

Extended operation of turbojet engine with pentaborane

Date: May 22, 1957
Creator: Useller, James W & Jones, William L
Description: A full-scale turbojet engine was operated with pentaborane fuel continuously for 22 minutes at conditions simulating flight at a Mach number of 0.8 at an altitude of 50,000 feet. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1.3 with JP-4 fuel to 0.98 with pentaborane, a 13.2-percent reduction in net thrust was also encountered. A portion of this thrust loss is potentially recoverable with proper design of the engine components. The boron oxide deposition and erosion processes within the engine approached an equilibrium condition after approximately 22 minutes of operation with pentaborane.
Contributing Partner: UNT Libraries Government Documents Department
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