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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
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 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
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
Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0

Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0

Date: January 30, 1953
Creator: Fradenburgh, Evan A & Campbell, Robert C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a hydraulic control determined from transient data obtained with a turbojet engine at altitude

Characteristics of a hydraulic control determined from transient data obtained with a turbojet engine at altitude

Date: June 16, 1954
Creator: Vasu, George; Hinde, William L & Craig, R T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of a wedge with various holder configurations for static-pressure measurements in subsonic gas streams

Characteristics of a wedge with various holder configurations for static-pressure measurements in subsonic gas streams

Date: September 5, 1951
Creator: Gettelman, Clarence C & Krause, Lloyd N
Description: The characteristics of a wedge static-pressure sensing element with various holder configurations were determined and compared with the characteristics of the conventional tube. The probes were tested over a range of Mach number from 0.3 to 0.95 and at various pitch and yaw angles. The investigation showed that the spike-mounted wedge sensing element has a pressure coefficient comparable with the conventional subsonic static-pressure probe and the pressure coefficient of the wedge varied less than that of the conventional probe for corresponding change of yaw angle.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of flow about axially symmetric isentropic spikes for nose inlets at Mach number 3.85

Characteristics of flow about axially symmetric isentropic spikes for nose inlets at Mach number 3.85

Date: August 19, 1954
Creator: Connors, James F & Wollett, Richard R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling performance and structural reliability of a modified corrugated-insert air-cooled turbine blade with an integrally cast shell and base

Cooling performance and structural reliability of a modified corrugated-insert air-cooled turbine blade with an integrally cast shell and base

Date: January 21, 1957
Creator: Freche, John C & Schum, Eugene F
Description: A modified corrugated-insert blade with integrally cast shell and base was developed. This blade was as light as a conventional fabricated corrugated-insert blade. Of four test blades operated in a full-scale turbojet engine, one failed after about 15 hours operation at an inlet gas temperature of 1670 degrees F, a coolant-flow ratio of 0.0064, and a 1/3-span centrifugal stress of approximately 28,000 psi. Three other test blades ran for approximately 16, 31, and 36 hours without failure at similar conditions.
Contributing Partner: UNT Libraries Government Documents Department
Correlation between hydrogen pressure and protective action of additives in the molten sodium hydroxide - nickel system

Correlation between hydrogen pressure and protective action of additives in the molten sodium hydroxide - nickel system

Date: February 9, 1956
Creator: May, Charles E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling characteristics of an experimental tail-pipe burner with an annular cooling-air passage

Cooling characteristics of an experimental tail-pipe burner with an annular cooling-air passage

Date: February 26, 1952
Creator: Kaufman, Harold R & Koffel, William K
Description: The effects of tail-pipe fuel-air ratio (exhaust-gas temperatures from approximately 3060 degrees to 3825 degrees R), radial distributiion of tail-pipe fuel flow, and mass flow of combustion gas and the inside wall were determined for an experimental tail-pipe burner cooled by air flowing through and insulated cooling-air to combustion gas mass flow from 0.066 to 0.192 were also determined.
Contributing Partner: UNT Libraries Government Documents Department
Considerations in the adaptation of low-cost fuels to gas-turbine-powered commercial aircraft

Considerations in the adaptation of low-cost fuels to gas-turbine-powered commercial aircraft

Date: October 1, 1953
Creator: Barnett, Henry C & Mccafferty, Richard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth

Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth

Date: August 19, 1954
Creator: Koffel, William K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Arrangements of jet engine and airframe for increased range

Arrangements of jet engine and airframe for increased range

Date: July 26, 1957
Creator: Luidens, Roger W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Attenuation of tangential-pressure oscillations in a liquid-oxygen - n-heptane rocket engine with longitudinal fins

Attenuation of tangential-pressure oscillations in a liquid-oxygen - n-heptane rocket engine with longitudinal fins

Date: June 28, 1956
Creator: Priem, Richard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculated heats of formation and combustion of boron compounds (boron, hydrogen, carbon, silicon)

Calculated heats of formation and combustion of boron compounds (boron, hydrogen, carbon, silicon)

Date: October 4, 1955
Creator: Altschuller, Aubrey P
Description: None
Contributing Partner: UNT Libraries Government Documents Department