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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Determination of rate, area, and distribution of impingement of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Determination of rate, area, and distribution of impingement of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Date: February 16, 1949
Creator: Guibert, A. G.; Janssen, E. & Robbins, W. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

Date: January 1, 1947
Creator: Novik, David & Otto, Edward W.
Description: Requirements of an automatic engine control, as affected by engine characteristics, have been analyzed for a direct-coupled turbojet engine. Control parameters for various conditions of engine operation are discussed. A hypothetical engine control is presented to illustrate the use of these parameters. An adjustable speed governor was found to offer a desirable method of over-all engine control. The selection of a minimum value of fuel flow was found to offer a means of preventing unstable burner operation during steady-state operation. Until satisfactory high-temperature-measuring devices are developed, air-fuel ratio is considered to be a satisfactory acceleration-control parameter for the attainment of the maximum acceleration rates consistent with safe turbine temperatures. No danger of unstable burner operation exists during acceleration if a temperature-limiting acceleration control is assumed to be effective. Deceleration was found to be accompanied by the possibility of burner blow-out even if a minimum fuel-flow control that prevents burner blow-out during steady-state operation is assumed to be effective. Burner blow-out during deceleration may be eliminated by varying the value of minimum fuel flow as a function of compressor-discharge pressure, but in no case should the fuel flow be allowed to fall below the value required for steady-state burner operation.
Contributing Partner: UNT Libraries Government Documents Department
An Analysis of the Full-Floating Journal Bearing

An Analysis of the Full-Floating Journal Bearing

Date: January 28, 1947
Creator: Shaw, M.C. & Nussdorfer, T.J.
Description: An analysis of the operating characteristics of a full-floating bearing - a bearing in which a floating sleeve is located between the journal and bearing surfaces - is presented together with charts - from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing to verify some results of the analysis are reported. The floating sleeve can operate over a wide range of speeds for a given shaft speed, the exact value depending principally upon the ratio of clearances and upon the ratio of radii of the bearing. Lower operating temperatures at high rotative speeds are to be expected by using a full-floating bearing. This lower operating temperature would be obtained at the expense of the load-carrying capacity of the bearing if, for comparison, the clearances remain the same in both bearings. A full-floating bearing having the same load capacity as a conventional journal bearing may be designed if decreased clearances are allowable.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Compressor of XJ-41-V Turbojet Engine II - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 rpm

Performance of Compressor of XJ-41-V Turbojet Engine II - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 rpm

Date: January 1, 1948
Creator: Dildine, Dean M. & Arthur, W. Lewis
Description: At the request of the Air Material Command, Army Air Forces, an investigation was conducted by the NACA Cleveland laboratory to determine the performance characteristics of the compressor of the XJ-41-V turbojet engine. This report is the second in a series presenting the compressor performance and analysis of flow conditions in the compressor. The static-pressure variation in the direction of flow through the compressor and the location and the cause of the maximum flow restriction at an equivalent speed of 8000 rpm are presented. After the initial runs were reported, the leading edges of the impeller blades and the diffuser surfaces were found to have been roughened by steel particles from a minor failure of auxiliary equipment. The leading edges of the impeller blades were refinished and all high spots resulting from scratches in the diffuser and the accessible parts of the vaned collector passages were removed. The initial overall performance and that obtained with the refinished blades are presented.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Compressor XJ-41-V Turbojet Engine I - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM

Performance of Compressor XJ-41-V Turbojet Engine I - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM

Date: January 1, 1948
Creator: Ginsburg, Ambrose & Creagh, John W.R.
Description: At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compressor, the characteristic performance of each of the compressor components, the state of the air stream in the simulated burner annulus, and the operation of the compressor bearings. An initial investigation at an equivalent compressor speed of 8000 rpm was made to determine the performance of the compressor and the collecting chamber and to determine the similarity of the air stream at the entrance to the simulated burner annulus. The mechanical performance of the compressor over a range of actual compressors speeds from 3300 to 8000 rpm is reported.
Contributing Partner: UNT Libraries Government Documents Department
Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles

Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles

Date: December 2, 1948
Creator: Shames, Harold & Seashore, Ferris L.
Description: Design data are presented for the graphical construction of two-dimensional sharp-edge-throat supersonic nozzles of minimum length for test-section Mach numbers from 1.20 to 10.00. The method of characteristics used in the design is briefly reviewed.
Contributing Partner: UNT Libraries Government Documents Department
Design factors for 4- by 8-inch ram-jet combustor

Design factors for 4- by 8-inch ram-jet combustor

Date: August 11, 1949
Creator: Male, Donald W & Cervenka, Adolph J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Carbon deposition of 19 fuels in an annular turbojet combustor

Carbon deposition of 19 fuels in an annular turbojet combustor

Date: February 3, 1949
Creator: Jonash, Edmund R & Wear, Jerrold D
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
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
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