You limited your search to:

 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