National Advisory Committee for Aeronautics (NACA) - 55 Matching Results

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Fuel investigation in a tubular-type combustor of a turbojet engine

Description: A series of 11 fuels ranging in volatility and including various types of hydrocarbons were tested in a single tubular combustion chamber of a turbojet engine under inlet-air conditions simulating engine operation at two speeds at an altitude of 40,000 feet. Temperature-rise data at various fuel-air ratios were obtained for each set of air-flow conditions. Results regarding the effect of combustor inlet-air conditions on temperature rise, four different series of tests, and a review of some gen… more
Date: August 1, 1947
Creator: Tischler, Adelbert O. & Dittrich, Ralph T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Further experiments on the flow and heat transfer in a heated turbulent air jet

Description: "Measurements have been made of the mean-total-head and mean-temperature fields in a round turbulent jet with various initial temperatures. The results show that the jet spreads more rapidly as its density becomes lower than that of the receiving medium, even when the difference is not sufficiently great to cause dynamic-pressure function. Rough analytical considerations have given the same relative spread. The effective "turbulent Prandtl number" for a section of the fully developed jet was fo… more
Date: August 18, 1947
Creator: Corrsin, Stanley & Uberoi, Mahinder S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Load Distribution on the Wing of a 3/16-Scale Model of a Scout-Bomber Airplane with Flaps Deflected

Description: "The tests reported herein were made for the purpose of determining the high-speed load distribution on the wing of a 3/16 scale model of a scout-bomber airplane. Comparisons are made between the root bending-moment and section torsional-moment coefficients as obtained experimentally and derived analytically. The results show good correlation for the bending-moment coefficients but considerable disagreement for the torsional-moment coefficients" (p. 1).
Date: August 21, 1947
Creator: Barnes, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-speed wind-tunnel investigation of the effects of compressibility on a pitot-static tube

Description: Report presenting a high-speed wind-tunnel investigation of a pitot-static tube to provide information on the effects of compressibility upon the pressure indications of a representative airspeed head at high subsonic speeds. The calibration factor for the instrument has been evaluated for several small angles of pitch and yaw throughout a Mach number range from 0.30 to approximately 0.925. The results indicate that the calibration factor for each combination of pitch and yaw angles tested is a… more
Date: August 4, 1947
Creator: Stivers, Louis S., Jr. & Adams, Charles N., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of an NACA 16-009 Airfoil Having a 32.9-Percent-Chord Flap With an Overhang 20.7 Percent of the Flap Chord

Description: Report presenting an investigation to determine the effects of compressibility on the aerodynamic characteristics of a 5-inch-chord NACA 16-009 airfoil with a 32.9-percent-chord flap with a nose overhang and an unsealed gap. Airfoil lift and pitching moment and flap hinge moments were obtained for a range of angles of attack, flap angle ranges, and Mach numbers.
Date: August 1947
Creator: Stevenson, David B. & Byrne, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hinge-moment characteristics of balanced elevator and rudder for a specific tail configuration on a fuselage in spinning attitudes

Description: Report presenting the results of an investigation of a specific tail configuration in the 15-foot free-spinning tunnel in order to supplement the existing published data on hinge moments of elevators and rudders in spins. Hinge-moment measurements are presented for a balanced elevator equipped with trim tabs and for a balanced rudder. Results regarding elevator hinge moments, rudder hinge moments, and application of hinge-moment data are provided.
Date: August 1947
Creator: Stone, Ralph W., Jr. & Burk, Sanger M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Instantaneous ultraviolet knock spectra correlated with high-speed photographs

Description: Report presenting an investigation to obtain a record of any chemical changes directly associated with knock in a spark-ignition engine on a greatly magnified time scale by means of coordinated high-speed motion pictures and spectrograms.
Date: August 1947
Creator: Hirshfeld, M. A. & Miller, Cearcy D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation in the Langley 19-foot pressure tunnel of two wings of NACA 65-210 and 64-210 airfoil sections with various type flaps

Description: Report presents the results of an investigation conducted in the Langley 19-foot pressure tunnel to determine the maximum lift and stalling characteristics of two thin wings equipped with several types of flaps. Split, single slotted, and double slotted flaps were tested on one wing which had NACA 65-210 airfoil sections and split and double slotted flaps were tested on the other, which had NACA 64-210 airfoil sections. Both wings were zero sweep, an aspect ratio of 9, and a taper ratio of 0.4.
Date: August 19, 1947
Creator: Sivells, James C. & Spooner, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a Spoiler-Type Lateral Control System on a Wing with Full-Span Flaps in the Langley 19-Foot Pressure Tunnel

Description: "Tests of a partial-span model of a large bomber-type airplane were conducted to determine the aerodynamic characteristics of the wing equipped with full-span flaps and a retractable spoiler end aileron lateral control system. The arrangement consisted of (1) a double slotted flap extending over aproximate1y 86 percent of the wing semispan, (2) a 20-percent constant-percentage-chord aileron extending from the outboard end of the flap to the wing tip, and (3) a retractable spoiler, located at th… more
Date: August 1947
Creator: Deters, Owen J. & Russell, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of an Experimental Supersonic Axial-Flow Compressor

Description: An investigation is in progress at the Langley Laboratory of the NACA to explore the possibilities of axial-flow compressors operating with supersonic velocities relative to the blade rows. The first phase of this investigation, a study of supersonic diffusers, has been reported. The second phase, an analysis of supersonic compressors, has also been reported. Preliminary calculations have shown that very high pressure ratios across a stage, together with somewhat increased mass flows, are poss… more
Date: August 7, 1947
Creator: Erwin, John R.; Wright, Linwood C. & Kantrowitz, Arthur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Sea-Level Performance of I-16 Turbojet Engine at Zero Ram with XFR-1 Intake Duct Shroud, and Tail Pipe

Description: The sea-level performance of I-16 turbojet engine at zero ram was investigated to determine the effects of an intake duct, shroud, and tail pipe intended for installation in an XFR-1 airplane. Engine speeds ranged from 8000 to 16,500 rpm for several variations of the intake duct and tail pipes.
Date: August 5, 1947
Creator: Dowman, Harry W. & Anderson, William G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of shock diffusers at Mach number 1.85 3: multiple-shock and curved-contour projecting cones

Description: Report presenting total-pressure recoveries obtained with four-cone inlet combinations at Mach number 1.85. The configurations tested included a cone designed to produce three oblique shocks ahead of the diffuser inlet combined with two other inlets, a cone generated by a parabolic arc in combination with two other inlets, a cone-inlet combination designed to produce an isentropic entrance flow at 0 degrees angle of attack, and a 30 degree single-shock cone combined with a perforated inlet sect… more
Date: August 13, 1947
Creator: Moeckel, W. E. & Connors, J. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part 4 - Aileron Characteristics TED No. NACA DE308, Part 4, Aileron Characteristics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The aileron characteristics of the complete model are presented in the present report with a very limited analysis of the results.
Date: August 22, 1947
Creator: Goodson, Kenneth W. & Myers, Boyd C., II
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Thrust Augmentation of a 1600-Pound Thrust Centrifugal-Flow-Type Turbojet Engine by Injection of Refrigerants at Compressor Inlets

Description: Investigations were conducted to determine effectiveness of refrigerants in increasing thrust of turbojet engines. Mixtures of water an alcohol were injected for a range of total flows up to 2.2 lb/sec. Kerosene was injected into inlets covering a range of injected flows up to approximately 30% of normal engine fuel flow. Injection of 2.0 lb/sec of water alone produced an increase in thrust of 35.8% of rate engine conditions and kerosene produced a negligible increase in thrust. Carbon dioxide … more
Date: August 25, 1947
Creator: Jones, William L. & Dowman, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Thrust Losses Due to Shanks of a Flared-Shank Two-Blade Propeller on a Slender-Nose Airplane

Description: Note presenting flight measurements of thrust losses due to shanks on a flared-shank two-blade propeller mounted on an airplane with a streamline slender nose. Thrust losses due to the shanks were found to be high; they were of the order of 9 percent at an airplane Mach number of 0.7 when the propeller was operating at the highest test power coefficient of 0.17 per blade.
Date: August 1947
Creator: Hammack, Jerome B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of X24C-2 10-Stage Axial-Flow Compressor 2: Effect of Inlet-Air Pressure and Temperature of Performance

Description: Effect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Compressor from the X24C-2 turbojet engine was evaluated. Speeds of 80, 89, and 100 percent of equivalent design speed with inlet-air pressures of 6 and 12 inches of mercury absolute and inlet-air temperaures of approximately 538 degrees, 459 degrees,and 419 degrees R ( 79 degrees, 0 degrees, and minus 40 degrees F). Results were compared with prior investigations.
Date: August 21, 1947
Creator: Finger, Harold B.; Schum, Harold J. & Buckner, Howard A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations of Free Turbulent Mixing

Description: Note presenting a discussion of the integral relations for flow of the boundary-layer type. It is shown that the characteristic laws of spread of jets, wakes, and so forth, can be obtained directly for the laminar case and, with the help of dimensional reasoning, for the turbulent case as well. Measurements of the mean velocity, the intensity and scale of the turbulent fluctuations, and of the turbulent shear in a two-dimensional mixing zone are presented.
Date: August 1947
Creator: Liepmann, Hans Wolfgang & Laufer, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations on Reductions of Friction on Wings, in Particular by Means of Boundary Layer Suction

Description: Memorandum presenting investigation on reductions of friction on wings, especially by means of boundary-layer suction. The report is broken up into several sections, including: causes of transition, laminar profiles with the transition taking place, laminar boundary-layer suction, investigation of the laminar pressure increase, investigation of the slot flow for laminar boundary-layer suction with single slots, tests about keeping a boundary layer for high Reynolds laminar with the aid of bound… more
Date: August 1947
Creator: Pfenninger, Werner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Langley Full-Scale-Tunnel Investigation of Maximum Lift and Stability Characteristics of an Airplane Having Approximately Triangular Plan Form (DM-1 Glider)

Description: "An investigation of the DM-1 Glider, which had approximately triangular plan form, an aspect ratio of 1.8 and a 60 degree sweptback leading edge, has been conducted in the Langley full-scale tunnel. The investigation consisted of the determination of the separate effects of the following modifications made to the glider on its maximum lift and stability characteristics: (a) installation of sharp leading edges over the inboard semispan of the wing, (b) removal of the vertical fin, (c) sealing o… more
Date: August 5, 1947
Creator: Lovell, J. Calvin & Wilson, Herbert A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift and Drag of Wings with Small Span

Description: The lift coefficient of a wing of small span at first shows a linear increase for the increasing angle of attack, but to a lesser degree then was to be expected according to the theory of the lifting line; thereafter the lift coefficient increases more rapidly than linearity, as contrasted with the the theory of the lifting line. The induced drag coefficient for a given lift coefficient, on the other hand, is obviously much smaller than it would be according to the theory. A mall change in the … more
Date: August 1947
Creator: Weinig, F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Plain Flap by the NACA Wing-Flow Method

Description: Report presenting measurements using the NACA wing-flow method of the lift, pitching-moment, and hinge-moment characteristics of a 35 degree sweptback NACA 65-009 airfoil of aspect ratio 3.04 with a full-span 1/4-chord unsealed plain flap. The tests were carried out at a range of Mach numbers, Reynolds numbers, angles of attack, and flap deflections. Variations of lift and pitching moment with angle of attack or flap deflection were approximately rectilinear at all Mach numbers for moderate ang… more
Date: August 5, 1947
Creator: Johnson, Harold I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for numerically calculating the area and distribution of water impingement on the leading edge of an airfoil in a cloud

Description: Report presenting a method for determining, by step-by-step integration, the trajectories of water drops around any body in two-dimensional flow for which the streamline velocity components are known or can be computed. The equations are presented in general form and then water-drop trajectories are calculated about a 12-percent-thick symmetric Joukowski profile.
Date: August 1947
Creator: Bergrun, Norman R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method for Numerically Calculating the Area and Distribution of Water Impingement on the Leading Edge of an Airfoil in a Cloud

Description: Note presenting a method for determining, by step-by-step integration, the trajectories of water drops around any body in two-dimensional flow for which the streamline velocity components are known or can be computed. The equations are presented in general form and then, to illustrate the procedure, water-drop trajectories are calculated about a 12-percent-thick symmetrical Joukowski profile chosen to simulate an NACA 0012 section. The method provides a means for the relatively rapid calculatio… more
Date: August 1947
Creator: Bergrun, Norman R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Numerical evaluation of mass-flow coefficient and associated parameters from wake-survey equations

Description: Report presenting a method for the determination by use of charts of mass-flow coefficient and associated flow parameters from pressure surveys in internal-flow systems. The charts presented cover a wide range of specific parameters through the complete range of subsonic Mach numbers. The equations have also been evaluated for flows that involve the adding of mechanical or thermal energy, such as flows behind radiators or propellers.
Date: August 1947
Creator: Smith, Norman F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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