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

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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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The optical system of the NACA 400,000-frame-per-second motion-picture camera

Description: Report presenting the optical principle of the NACA ultrahigh-speed camera. Simplified sketches are included illustrating the optical principle and main design features of the camera, but without minor design details. A detailed description of the camera is provided as well as some sample photographs taken with the camera.
Date: August 1947
Creator: Miller, Cearcy D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance and Ranges of Application of Various Types of Aircraft-Propulsion System

Description: Note presenting a discussion of the performance characteristics of the compound engine, the turbine-propeller engine, the turbojet engine, the turbo ramjet engine, the ramjet engine, and the rocket engine. Insight is provided into the proper position of each of these engine types in the speed-range spectrum of aircraft operation. It is shown that the compound engine, which has the greatest weight per unit thrust and also the lowest specific fuel consumption, gives the longest range.
Date: August 1947
Creator: Cleveland Laboratory Staff
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a double-row radial aircraft engine with three methods of safety-fuel injection

Description: Report presenting an investigation to determine whether a safety fuel with a flash point of 122 degrees Fahrenheit could be successfully used in a high-power radial aircraft engine without individual cylinder fuel-injection equipment. The safety fuel was injected into the combustion-air stream in three different ways. Results regarding the standard powers, effect of average fuel-air ratio on mixture distribution, effect of combustion-air temperature on mixture distribution, general engine perfo… more
Date: August 1947
Creator: Michel, Donald J.; Hickel, Robert O. & Voit, Charles H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A preliminary correlation of the behavior of water rudders on seaplanes and flying boats

Description: From Summary: "This report presents a rough correlation of the dimensions of water rudders of various actual seaplanes and flying boats as related to their behavior. The correlation should be useful for determining the size of a water rudder which will give adequate control for maneuvering at low speeds."
Date: August 1947
Creator: Locke, F. W. S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of spoiler lateral control on a 42 degree sweptback wing at transonic speeds

Description: Investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the rolling-effectiveness characteristics of a spoiler on a double-wedge-type semispan wing with a sweepback angle of 42 degrees. Results regarding the variation of rolling-moment coefficient, spoiler effectiveness, and rolling effectiveness are provided.
Date: August 12, 1947
Creator: Schneiter, Leslie E. & Ziff, Howard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine II - Windmilling Characteristics

Description: An investigation was conducted to determine the operational and performance characteristics of the TG-100A gas turbine-propeller engine II. Windmilling characteristics were deterined for a range of altitudes from 5000 to 35,000 feet, true airspeeds from 100 to 273 miles per hour, and propeller blade angles from 4 degrees to 46 degrees.
Date: August 4, 1947
Creator: Conrad, E. W. & Durham, J. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Torsional Stiffness Criterion for Preventing Flutter of Wings of Supersonic Missiles

Description: "A formula, based on a semirational analysis, is presented for estimating the torsional stiffness necessary to prevent flutter of a sweptback or unswept uniform wing that attains supersonic speeds. Results of missile flights at speeds up to Mach number 1.4 demonstrate the usefulness of the formula" (p. 1).
Date: August 28, 1947
Creator: Budiansky, Bernard; Kotanchik, Joseph N. & Chiarito, Patrick T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of drooped ailerons on a 16-percent-thick low-drag airfoil

Description: Report presenting a wind-tunnel investigation to determine the practicability of the dropped-aileron-type lateral-control device on NACA low-drag airfoils. Section aerodynamic characteristics of an NACA 66(215)-216 airfoil with an aileron of normal profile and an aileron of straight-sided profile with a modified nose shape are presented for various aileron locations, hinge centers, and aerodynamic balances.
Date: August 1947
Creator: Holtzclaw, Ralph W. & Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the effect of tab balance on tab and control-surface characteristics

Description: An investigation was conducted to furnish data on the effect of tab balance on tab and control-surface characteristics. The airfoil tested had a modified NACA 65(1)-012 contour with a plain flap having a chord equal to 25 percent of the wing chord and with a tab having a chord equal to 25 percent of the flap chord and having several nose shapes and overhang lengths. The results of the investigation indicated that, in general, tab balance affected tab hinge-moment characteristics in much the sam… more
Date: August 1947
Creator: Brewer, Jack D. & Queijo, M. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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