UNT Libraries Government Documents Department - 14 Matching Results

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Analysis of temperature distribution in liquid-cooled turbine blades

Description: From Summary: "This report presents analytical methods for computing temperature distributions in liquid-cooled turbine blades, or in simplified shapes used to approximate sections of the blade. The individual analyses are first presented in terms of their mathematical development. Nondimensional charts to simplify some temperature-distribution calculations are also given."
Date: October 27, 1950
Creator: Livingood, John N. B. & Brown, W. Byron

The Effect of Sweepback on the Longitudinal Characteristics at a Mach Number of 1.24 of a 1/30 Scale Semispan Model of the Bell X-5 Airplane From Tests by the NACA Wing Flow Method

Description: Report discussing testing to determine the effect of sweepback on the longitudinal characteristics of a model of the Bell X-5 airplane at Mach number 1.24. Lift, drag, and pitching moments were obtained for several angles of attack. Effects on the drag coefficient and lift-curve slope are described.
Date: November 27, 1950
Creator: Morris, Garland J.; Kennedy, Robert M. & Silsby, Norman S.

Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine 2 - Performance of Revised Compressor at Design Equivalent Speed

Description: From Summary: "The compressor from the XT-46 turbine-propeller engine was revised by removing the last two rows of stator blades and by eliminating the interstage leakage paths described in a previous report. With the revised compressor, the flow choking point shifted upstream into the last rotor-blade row but the maximum weight flow was not increased over that of the original compressor. The flow range of the revised compressor was reduced to about two-thirds that obtained with the original compressor. The later stages of the compressor did not produce the design static-pressure increase probably because of excessive boundary-layer build-up in this region. Measurements obtained in the ninth-stage stator showed that the performance up to this station was promising but that the last three stages of the compressor were limiting the useful operating range of the preceding stages. Some modifications in flow-passage geometry and blade settings are believed to be necessary, however, before any major improvements in over-all compressor performance can be obtained."
Date: October 27, 1950
Creator: Creagh, John W. R.

Preliminary investigation of heat transfer to water flowing in an electrically heated Inconel tube

Description: A heat-transfer investigation was conducted with water flowing in an electrically heated Inconel tube with an inside diameter of 0.204 inch and a length-diameter ratio of 50 for ranges of Reynolds number up to 100,000 and of entrance pressure up to 200 inches of mercury gage. Correlation of average heat-transfer coefficients was obtained by use of the familiar Nusselt relation, wherein the physical properties of water were evaluated at an average bulk temperature. For conditions in which no boiling occurred, the data gave a good correlation. Runs made in the nucleate-boiling region, however, gave higher values of heat-transfer coefficient than would be predicted by the Nusselt relation.
Date: September 27, 1950
Creator: Kaufman, Samuel J. & Isely, Francis D.

Preliminary Performance Data on Westinghouse Electronic Power Regulator Operating on J34-WE-32 Turbojet Engine in Altitude Wind Tunnel

Description: "The behavior of the Westinghouse electronic power regulator operating on a J34-WE-32 turbojet engine was investigated in the NACA Lewis altitude wind tunnel at the request of the Bureau of Aeronautics, Department of the Navy. The object of the program was to determine the, steady-state stability and transient characteristics of the engine under control at various altitudes and ram pressure ratios, without afterburning. Recordings of the response of the following parameters to step changes in power lever position throughout the available operating range of the engine were obtained; ram pressure ratio, compressor-discharge pressure, exhaust-nozzle area, engine speed, turbine-outlet temperature, fuel-valve position, jet thrust, air flow, turbine-discharge pressure, fuel flow, throttle position, and boost-pump pressure" (p. 1).
Date: October 27, 1950
Creator: Ketchum, James R.; Blivas, Darnold & Pack, George J.

Rough-Water Tests of Models of the Vosper and Plum Planing Boats

Description: Models of two types of high-speed surface craft were tested in Langley tank no. 1 to obtain rough-water data for an evaluation by the David Taylor .Model Basin of the relative merits of the designs. Time-history records were obtained of trim, rise, and normal acceleration at two points in the hulls for various speeds and two sizes of waves.
Date: April 27, 1950
Creator: Chambliss, Derrill B. & Blanchard, Ulysse J.

The Separation of Trace Amounts of Radioactive Cs From Macro Quanitites of Sodium and Potassium Salts

Description: Summary: A method for the separation of cesium from macro quantities of sodium and potassium using an ion exchange resin, Dowex 50, has been developed. A 95% recovery of cesium with a reduction of the solid content of 95% was found possible. Curves illustrating the effect of acidity, column length, and flow rate are presented in the report. The sodium form, hydrogen form and ammonium form of Dowex 50 were investigated; the hydrogen form was found to give the best separation.
Date: January 27, 1950
Creator: Thorburn, R. C.

Stall Characteristics Obtained from Flight 10 of Northrop X-4 No. 2 Airplane (USAF No. 46-677)

Description: NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the acceptance tests conducted by the Northrop Aircraft Corporation. This report presents data obtained on the stalling characteristics of the airplane in the clean and gear- down configurations. The center of gravity was located at approximately 18 percent of the mean aerodynamic chord during the tests. The results indicated that the airplane was not completely stalled when stall was gradually approached during nominally U accelerated flight but that it was completely stalled during a more abruptly approached stall in accelerated flight. The stall in accelerated flight was relatively mild, and this was attributed to the nature of the variation of lift with angle of attack for the 001-614 airfoil section, the plan form of the wing, and to the fact that the initial sideslip at the stall produced (as shown by wind-tunnel tests of a model of the airplane) a more symmetrical stall pattern.
Date: February 27, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.

Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the Douglas X-3 Research Airplane, Study 41-B

Description: Report presenting calculations of the dynamic lateral stability characteristics of a mock-up configuration of the Douglas X-3. The oscillations were found to be stable for all calculations investigated but would not meet the Air Force damping requirements for the majority of the conditions. The use of an autopilot was found to greatly improve oscillation damping.
Date: April 27, 1950
Creator: Bennett, Charles V.

Turbojet combustion efficiency at high altitudes

Description: Report presenting research on the single problem of combustion efficiency of turbojet engines at high altitudes. Representative results of investigations with turbojet combustors are presented to analyze trends regarding combustor operating variables, combustor-design variables, and fuel variables.
Date: October 27, 1950
Creator: Olson, Walter T.; Childs, J. Howard & Jonash, Edmund R.

Turbojet-engine evaluation of AISI 321 and AISI 347 stainless steels as nozzle-blade materials

Description: Report presenting an investigation to evaluate the engine service performance of nozzle-diaphragm blades of AISI 321 and AISI 347 stainless steels. Data were obtained from three nozzle diaphragms alternately bladed with each of the two materials. Results regarding a visual inspection, a metallurgical examination, the mechanism of cracking, and the classification of failures are provided.
Date: February 27, 1950
Creator: Garrett, Floyd B. & Yaker, Charles