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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
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
Criticality survey of hydroxides as coolant moderators for aircraft nuclear reactors

Criticality survey of hydroxides as coolant moderators for aircraft nuclear reactors

Date: October 27, 1953
Creator: Bogart, Donald & Soffer, Leonard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of initial rate of subsonic diffusion on the stable subcritical mass-flow range of a conical shock diffuser

The effect of initial rate of subsonic diffusion on the stable subcritical mass-flow range of a conical shock diffuser

Date: July 22, 1953
Creator: Nettles, J C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet air and fuel parameters on smoking characteristics of a single tubular turbojet engine combustor

Effect of inlet air and fuel parameters on smoking characteristics of a single tubular turbojet engine combustor

Date: April 17, 1952
Creator: Butze, Helmut F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-air-flow-distortions on steady-state performance of J65-B-3 turbojet engine

Effect of inlet-air-flow-distortions on steady-state performance of J65-B-3 turbojet engine

Date: January 25, 1956
Creator: Smith, Ivan D; Braithwaite, W M & Calvert, Howard F
Description: The effects of inlet-air-flow distortions on the performance of the J65-B-3 turbojet engine were determined over a range of altitudes from 15,000 to 50,000 feet at a flight Mach number of 0.8. Radial inlet-air-flow distortions apparently do not affect the radial distribution of pressure after the first few compressor stages, while the circumferential inlet-air-flow distortion carried completely through the engine. For the distortions investigated, at rated exhaust-gas temperature and fixed-area exhaust-nozzle operation, the primary effect of the radial inlet-air-flow distortions was to reduce the engine air flow, and the primary effect of the circumferential distortion was to impose a temperature profile on the turbine, both resulting in reduction of thrust.
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-air baffles on rotating-stall and stress characteristics of an axial-flow compressor in a turbojet engine

Effect of inlet-air baffles on rotating-stall and stress characteristics of an axial-flow compressor in a turbojet engine

Date: January 10, 1955
Creator: Huntley, S C; Huppert, Merle C & Calvert, Howard F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-air temperature on performance of a 16-inch ram-jet combustor

Effect of inlet-air temperature on performance of a 16-inch ram-jet combustor

Date: October 29, 1953
Creator: Cervenka, A J; Dangle, E E & Friedman, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-air parameters on combustion limit and flame length in 8-inch-diameter ram-jet combustion chamber

Effect of inlet-air parameters on combustion limit and flame length in 8-inch-diameter ram-jet combustion chamber

Date: July 22, 1948
Creator: Miller, R C & Cervenka, A J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-duct length in uniform-flow field on turbojet-engine operation

Effect of inlet-duct length in uniform-flow field on turbojet-engine operation

Date: April 11, 1956
Creator: Lubick, Robert J; Chelko, Louis J & Wallner, Lewis E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet flow distortion on compressor stall and acceleration characteristics of a J65-B-3 turbojet engine

Effect of inlet flow distortion on compressor stall and acceleration characteristics of a J65-B-3 turbojet engine

Date: November 18, 1955
Creator: Fenn, David B & Sivo, Joseph N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-annulus area blockage on over-all performance and stall characteristics of an experimental 15-stage axial-flow compressor

Effect of inlet-annulus area blockage on over-all performance and stall characteristics of an experimental 15-stage axial-flow compressor

Date: May 11, 1954
Creator: Lucas, James G; Finger, Harold B & Filippi, Richard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department