You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Collection: National Advisory Committee for Aeronautics Collection
An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2

An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2

Date: February 23, 1950
Creator: Ritchie, Virgil S; Wright, Ray H & Tulin, Marshall P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Ability of pilots to control simulated short-period yawing oscillations

Ability of pilots to control simulated short-period yawing oscillations

Date: November 13, 1950
Creator: Phillips, William H & Cheatham, Donald C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Abnormal grain growth in M-252 and S-816 alloys

Abnormal grain growth in M-252 and S-816 alloys

Date: November 1957
Creator: Decker, R F; Rush, A I; Dano, A G & Freeman, J W
Description: An experimental investigation was carried out on air- and vacuum-melted M-252 and S-816 alloys to find conditions of heating and hot-working which resulted in abnormal grain growth. The experiments were mainly limited to normal conditions of heating for hot-working and heat treatment and normal temperatures of solution treatment were used to allow grain growth after susceptibility to abnormal grain growth was developed by various experimental conditions. Results indicated that small reductions of essentially strain-free metal were the basic cause of such grain growth.
Contributing Partner: UNT Libraries Government Documents Department
Abnormal grain growth in nickel-base heat-resistant alloys

Abnormal grain growth in nickel-base heat-resistant alloys

Date: December 1957
Creator: Decker, R F; Rush, A I; Dano, A G & Freeman, A G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Abnormal grain growth in S-816 alloy

Abnormal grain growth in S-816 alloy

Date: April 1952
Creator: Rush, A I; Freeman, J W & White, A E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acceleration characteristics of a turbojet engine with variable-position inlet guide vanes

Acceleration characteristics of a turbojet engine with variable-position inlet guide vanes

Date: July 7, 1955
Creator: Dobson, W F & Wallner, Lewis E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed

Date: July 3, 1953
Creator: Rebeske, John J , Jr & Dugan, James F , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics I : effect of air bleed at compressor outlet

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics I : effect of air bleed at compressor outlet

Date: March 10, 1953
Creator: Rebeske, John J , Jr & Rohlik, Harold E
Description: An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area. A relatively simple two-step area bleed gives only a small increase in acceleration time over a corresponding variable-area bleed. For the modes of operation considered, over 84 percent of the total acceleration time was required to accelerate through the low-speed range ; therefore, better low-speed compressor performance (higher pressure ratios and efficiencies) would give a significant reduction in acceleration time.
Contributing Partner: UNT Libraries Government Documents Department
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics III : effect of turbine stator adjustment

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics III : effect of turbine stator adjustment

Date: August 2, 1954
Creator: Rohlik, Harold E & Rebeske, John J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An acceleration schedule control for accelerating a turbojet engine and its use with a speed control

An acceleration schedule control for accelerating a turbojet engine and its use with a speed control

Date: May 12, 1958
Creator: Gerus, Theodore F; Powers, Albert G & Heppler, Herbert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An acceleration schedule control for accelerating a turbojet engine and its use with a speed control

An acceleration schedule control for accelerating a turbojet engine and its use with a speed control

Date: May 12, 1958
Creator: Gerus, T. F.; Heppler, H. J. & Powers, A. G.
Description: Accelerating-limiting controls for turbojet engines.
Contributing Partner: UNT Libraries Government Documents Department
Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Date: August 1953
Creator: Eiband, A Martin; Simpkinson, Scott H & Black, Dugald O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in fighter-airplane crashes

Accelerations in fighter-airplane crashes

Date: November 4, 1957
Creator: Acker, Loren W; Black, Duglad O & Moser, Jacob C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in transport-airplane crashes

Accelerations in transport-airplane crashes

Date: February 1958
Creator: Preston, G Merritt & Pesman, Gerard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accuracy of approximate methods for predicting pressures on pointed nonlifting bodies of revolution in supersonic flow

Accuracy of approximate methods for predicting pressures on pointed nonlifting bodies of revolution in supersonic flow

Date: August 1952
Creator: Ehret, Dorris M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams

The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams

Date: April 1956
Creator: Davenport, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An accurate and rapid method for the design of supersonic nozzles

An accurate and rapid method for the design of supersonic nozzles

Date: February 1955
Creator: Beckwith, Ivan E & Moore, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Achievement of continuous wall curvature in design of two-dimensional symmetrical supersonic nozzles

Achievement of continuous wall curvature in design of two-dimensional symmetrical supersonic nozzles

Date: January 1952
Creator: Evvard, J C & Marcus, Lawrence R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic analysis of ram-jet buzz

Acoustic analysis of ram-jet buzz

Date: November 1955
Creator: Mirels, Harold
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Date: August 1955
Creator: Krishnamurty, K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Date: April 1958
Creator: Ciepluch, Carl C; North, Warren J; Coles, Willard D & Antl, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Date: June 1955
Creator: Beranek, Leo L; Labate, Samuel & Ingard, Uno
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustics of a nonhomogeneous moving medium.

Acoustics of a nonhomogeneous moving medium.

Date: February 1956
Creator: Blokhintsev, D I
Description: Theoretical basis of the acoustics of a moving nonhomogeneous medium is considered in this report. Experiments that illustrate or confirm some of the theoretical explanation or derivation of these acoustics are also included.
Contributing Partner: UNT Libraries Government Documents Department
An active particle diffusion theory of flame quenching for laminar flames / Dorothy M. Simon and Frank E. Belles

An active particle diffusion theory of flame quenching for laminar flames / Dorothy M. Simon and Frank E. Belles

Date: March 4, 1952
Creator: Simon, Dorothy M & Belles, Frank E
Description: An equation for quenching distance based on the destruction of chain carriers by the surface is derived. The equation expresses the quenching distance in terms of the diffusion coefficients and partial pressures of the chain carriers and gas phase molecules, the efficiency of the surface as a chain breaker, the total pressure of the mixture, and a constant which depends on the geometry of the quenching surface. Quenching distances measured by flashback for propane-air flames are shown to be consistent with the mechanism. The derived equation is used with the lean inflammability limit and a rate constant calculated from burning velocity data to estimate quenching distances for propane-air (hydrocarbon lean) flames satisfactorily.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST