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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine

Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine

Date: June 12, 1957
Creator: Stepka, Francis S; Richards, Hadley T & Hickel, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Carbon deposition from AN-F-58 fuels in a J33 single combustor

Carbon deposition from AN-F-58 fuels in a J33 single combustor

Date: June 24, 1949
Creator: Wear, Jerrold D & Douglass, Howard W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuel volatility on altitude starting limits of a turbojet engine

Effect of fuel volatility on altitude starting limits of a turbojet engine

Date: September 11, 1950
Creator: Wilsted, H D & Armstrong, J C
Description: The effect of fuel volatility on altitude starting limits of an axial-flow-compressor-type turbojet engine was investigated using fuels with Reid vapor pressures of 1.1 and 5.4 pounds per square inch. At flight Mach numbers from 0.40 to 0.85, the AN-F-58 fuel allowed consistent windmilling at altitudes 2000 to 8000 feet higher than was obtained with the 1.1-pound Reid vapor pressure fuel. At a flight Mach number of 0.25, ignition could not be established at any altitude with the lower-volatility fuel.
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuel volatility on performance of tail-pipe burner

Effect of fuel volatility on performance of tail-pipe burner

Date: April 30, 1951
Creator: Barson, Zelmar & Sargent, Arthur F , Jr
Description: Fuels having Reid vapor pressures of 6.3 and 1.0 pounds per square inch were investigated in a tail-pipe burner on an axial-flow-type turbojet engine at a simulated flight Mach number of 0.6 and altitudes from 20,000 to 45,000 feet. With the burner configuration used in this investigation, having a mixing length of only 8 inches between the fuel manifold and the flame holder, the low-vapor-pressure fuel gave lower combustion efficiency at a given tail-pipe fuel-air ratio. Because the exhaust-nozzle area was fixed, the lower efficiency resulted in lower thrust and higher specific fuel consumption. The maximum altitude at which the burner would operate was practically unaffected by the change in fuel volatility.
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuels on combustion efficiency of 5-inch ram-jet-type combustor

Effect of fuels on combustion efficiency of 5-inch ram-jet-type combustor

Date: May 22, 1953
Creator: Reynolds, Thaine W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuel volatility characteristics on ignition-energy requirements in a turbojet combustor

Effect of fuel volatility characteristics on ignition-energy requirements in a turbojet combustor

Date: January 13, 1953
Creator: Foster, Hampton H & Straight, David M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag data for 16-inch-diameter ram-jet engine with double-cone inlet in free flight at Mach numbers from 0.7 to 1.8

Drag data for 16-inch-diameter ram-jet engine with double-cone inlet in free flight at Mach numbers from 0.7 to 1.8

Date: October 25, 1954
Creator: Jones, Merle L; Rabb, Leonard & Simpkins, Scott H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Downwash in vortex region behind trapezoidal-wing tip at Mach number 1.91

Downwash in vortex region behind trapezoidal-wing tip at Mach number 1.91

Date: November 10, 1949
Creator: Cummings, J L & Baughman, L E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drop burning rates of hydrocarbon and nonhydrocarbon fuels

Drop burning rates of hydrocarbon and nonhydrocarbon fuels

Date: August 6, 1957
Creator: Smith, Arthur L & Graves, Charles C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A drop test for the evaluation of the impact strength of cermets

A drop test for the evaluation of the impact strength of cermets

Date: March 15, 1955
Creator: Pinkel, B; Deutsch, G C & Katz, N H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chemical and Physical Properties of Hi-Cal-2

Chemical and Physical Properties of Hi-Cal-2

Date: January 1, 1955
Creator: Spakowski, A. E.; Allen, Harrison, Jr. & Caves, Robert M.
Description: As part of the Navy Project Zip to consider various boron-containing materials as possible high-energy fuels, the chemical and physical properties of Hi-Cal-2 prepared by the Callery Chemical Company were evaluated at the NACA Lewis laboratory. Elemental chemical analysis, heat of combustion, vapor pressure and decomposition, freezing point, density, self ignition temperature, flash point, and blow-out velocity were determined for the fuel. Although the precision of measurement of these properties was not equal to that obtained for hydrocarbons, this special release research memorandum was prepared to make the data available as soon as possible.
Contributing Partner: UNT Libraries Government Documents Department
Chemical igniters for starting jet fuel - nitric acid rockets

Chemical igniters for starting jet fuel - nitric acid rockets

Date: October 8, 1957
Creator: Morrell, Gerald & Ladanyi, Dezso J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

Date: March 29, 1954
Creator: Hammond, Alexander D & Keffer, Barbara M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Coking of JP-4 fuels in electrically heated metal tubes

Coking of JP-4 fuels in electrically heated metal tubes

Date: November 20, 1956
Creator: Smith, Arthur L; Cook, William P & Hlavin, Vincent F
Description: A limited exploratory investigation of the rate of coking of four JP-4 fuels in electrically heated metal tubes was conducted in order to provide design information for fuel prevaporizers for turbojet-engine combustors. The fuels tested included two production and two minimum-quality JP-4 type fuels. The heating tube was operated at fuel pressures of approximately 500, 400, and 50 pounds per square inch. The operating fuel temperature was varied between approximately 600 degrees and 1200 degrees F.
Contributing Partner: UNT Libraries Government Documents Department
Cold-air investigation of a turbine with nontwisted rotor blades suitable for air cooling

Cold-air investigation of a turbine with nontwisted rotor blades suitable for air cooling

Date: March 18, 1952
Creator: Heaton, Thomas R; Slivka, William R & Westra, Leonard F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of perforated diffusers at free-stream Mach number 1.90

Characteristics of perforated diffusers at free-stream Mach number 1.90

Date: May 8, 1950
Creator: Hunczak, Henry R & Kremzier, Emil J
Description: An investigation was conducted at Mach number 1.90 to determine pressure recovery and mass-flow characteristics of series of perforated convergent-divergent supersonic diffusers. Pressure recoveries as high as 96 percent were obtained, but at reduced mass flows through the diffuser. Theoretical considerations of effect of perforation distribution on shock stability in converging section of diffuser are presented and correlated with experimental data. A method of estimating relative importance of pressure recovery and mass flow on internal thrust coefficient basis is given and a comparison of various diffusers investigated is made.
Contributing Partner: UNT Libraries Government Documents Department
Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle

Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle

Date: May 16, 1949
Creator: Dietz, Robert O , Jr & Krebs, Richard P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Date: March 15, 1954
Creator: VonGlahn, Uwe H. & Gray, Vernon H.
Description: The effects of primary and runback ice formations on the section drag of a 36 deg swept NACA 63A-009 airfoil section with a partial-span leading-edge slat were studied over a range of angles of attack from 2 to 8 deg and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.39 to 1.23 grams per cubic meter and datum air temperatures from 10 to 25 F. The results with slat retracted showed that glaze-ice formations caused large and rapid increases in section drag coefficient and that the rate of change in section drag coefficient for the swept 63A-009 airfoil was about 2-1 times that for an unswept 651-212 airfoil. Removal of the primary ice formations by cyclic de-icing caused the drag to return almost to the bare-airfoil drag value. A comprehensive study of the slat icing and de-icing characteristics was prevented by limitations of the heating system and wake interference caused by the slat tracks and hot-gas supply duct to the slat. In general, the studies showed that icing on a thin swept airfoil will result in more detrimental aerodynamic characteristics than on a thick unswept airfoil.
Contributing Partner: UNT Libraries Government Documents Department
Effect of ignitor design and ignitor spark-gap environment on ignition in a turbojet combustor

Effect of ignitor design and ignitor spark-gap environment on ignition in a turbojet combustor

Date: April 1, 1954
Creator: Foster, Hampton H & Straight, David M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor

Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor

Date: June 21, 1954
Creator: Reynolds, Thaine W & Male, Donald W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuels on screaming in 200-pound-thrust liquid-oxygen - fuel rocket engine

Effect of fuels on screaming in 200-pound-thrust liquid-oxygen - fuel rocket engine

Date: June 22, 1956
Creator: Pass, Isaac & Tischler, Adelbert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuselage circumferential inlet location on diffuser-discharge total-pressure profiles at supersonic speeds

Effect of fuselage circumferential inlet location on diffuser-discharge total-pressure profiles at supersonic speeds

Date: October 29, 1956
Creator: Kremzier, Emil J & Wasserbauer, Joseph F
Description: An experimental investigation of the effect of angle of attack and inlet corrected air flow on diffuser-discharge total-pressure profiles of inlets located in various circumferential positions on a fuselage was conducted at supersonic speeds. Results indicated that the diffuser total-pressure profiles for a bottom inlet were least affected by angle of attack on distortion level was obtained with a side inlet. Variation in distortion for top inlets with angle of attack was confined to the supercritical range of inlet operation.
Contributing Partner: UNT Libraries Government Documents Department
Effect of geometry on secondary flows in blade rows

Effect of geometry on secondary flows in blade rows

Date: October 16, 1952
Creator: Hansen, A G; Costello, G R & Herzig, H Z
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuselage fences on the angle-of-attack supersonic performance of a top-inlet - fuselage

Effect of fuselage fences on the angle-of-attack supersonic performance of a top-inlet - fuselage

Date: January 19, 1955
Creator: Kremzier, Emil J & Campbell, Robert C
Description: None
Contributing Partner: UNT Libraries Government Documents Department