National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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Investigations toward simplification of missile control systems

Description: Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.
Date: November 12, 1953
Creator: Curfman, Howard J., Jr.; Strass, H. Kurt & Crane, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Description: Report presenting a theory regarding engine-cooling variables from a previous report, which was used as a basis for the development of a semi-empirical equation to correlate exhaust-valve temperature with engine conditions. Results regarding the determination of constants, influences of operating variables on mean effective gas temperatures, thermal-resistance factor, and accuracy of correlating equation are provided.
Date: October 1945
Creator: Zipkin, M. A. & Sanders, J. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experiments on Drag of Revolving Disks, Cylinders and Streamline Rods at High Speeds

Description: Report presenting an experimental investigation concerned primarily with the extension of test data on the drag of revolving disks, cylinders, and streamline rods to high Mach numbers and Reynolds numbers. The tests generally confirm earlier theories and add in some new results. One of the primary findings of interest is that skin friction does not depend on Mach number.
Date: June 1944
Creator: Theodorsen, Theodore & Regier, Arthur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

Description: Summary: The effective change in the velocity of flow past a wing section, caused by the presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. It is shown that for a symmetrical section at zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M^2 to take account of compressibility effects. The Mach numb… more
Date: May 1943
Creator: Nitzberg, Gerald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lioré-Olivier LeO 194 Seaplane

Description: Report presenting a description of the Lioré-Olivier LeO 194 seaplane and a particular series of flights made over several months. Its fuselage is made entirely of wood. It has 6 gasoline tanks each with a capacity of 255 liters. It is a single engine biplane with wings mounted above the body of the seaplane.
Date: April 1927
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Hanriot-Biche 110 C1 Airplane (French): An All-Metal Low-Wing Pursuit Monoplane

Description: Circular presenting a description of the Hanriot-Biche 110 C1 airplane, which is a French all-metal low-wing pursuit monoplane. Details regarding the wing, girders and tail surfaces, pilot's cockpit, power plant, landing gear, flying qualities, and photographs are provided.
Date: July 1933
Creator: Rabion, René
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for determining the rate of heat transfer from a wing or streamline body

Description: From Summary: "A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude, for example."
Date: December 1942
Creator: Frick, Charles W., Jr. & McCullough, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Emergency Measures for Increasing the Range of Fighter Airplanes

Description: "An analysis was made to show the relative effectiveness of streamline external fuel tanks, a fuel tank in the form of a wing mounted in a biplane position, and auxiliary wing panels attached at the wing tips to increase the span as temporary means for increasing the range of a fighter-type airplane. Figures and charts for the various devices considered show the results of calculations of range, duration of flight, and take-off distance for both land-base and carrier operation. The results indi… more
Date: May 1943
Creator: Jones, Robert T. & Wetmore, Joseph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Vickers "Viastra I" Commercial Airplane (British): A High-Wing All-Metal Semicantilever Monoplane

Description: Circular describing the Vickers Viastra I, which is a commercial high-wing all-metal semicantilever monoplane. Details of the structure, fuselage, wings, fuel tanks, landing gear, tail, cabin, cockpit, characteristics, drawings, and photographs are provided.
Date: November 1930
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Review of Flight Tests of NACA C and D Cowlings on the XP-42 Airplane

Description: Report presenting the results of flight tests of the performance and cooling characteristics of three NACA D cowlings and of a conventional NACA C cowling on the XP-42 airplane. The D cowling is, generally, characterized by the use of an annular inlet and diffuser section for the engine-cooling air. An increase in maximum speed was noted in the XP-42 airplane due to the change from a C cowling to a D cowling.
Date: April 1943
Creator: Johnston, J. Ford
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fuel-Evaporation Loss as Determined by the Change in the Specific Gravity of the Fuel in an Aircraft Fuel Tank

Description: Report discusses the results of an investigation to determine the feasibility of using the change in the specific gravity of fuels in aircraft fuel tanks to measure fuel-vaporization loss. Six fuels were tested via fuel-distillation tests and simulated-flight tests. An equation based on the specific gravity of the fuel is also described.
Date: May 1945
Creator: Stone, Charles S. & Kramer, Walter E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Transformation of Heat in an Engine

Description: This report presents a thermodynamic basis for rating heat engines. The production of work by a heat engine rests on the operation of supplying heat, under favorable conditions, to a working fluid and then taking it away.
Date: April 1929
Creator: Neumann, Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fluid de-icing tests on a Chandler-Evans 1900 CPB-3 carburetor mounted on a Pratt & Whitney R-1830-C4 intermediate rear engine section

Description: Report presenting an investigation of the icing and de-icing characteristics of a Pratt & Whitney R-1830 engine induction system. The current report covers a program to determine the most effective rate and method of injection of de-icing fluid to remove a heavy ice formation from the induction system. Results regarding the flow rates, recovery times, de-icing portions of the runs, and ice formation characteristics are provided.
Date: October 1944
Creator: Galvin, Herman B. & Essex, Henry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Richard-Penhoet Commercial Seaplane

Description: This is a multi-engine monoplane with a central hull and without external bracing. The trim of the seaplane on the water is assured by two wing floats, one on each side of the hull 9 m. from its axis. It has a total power of 2100 HP. from 5 air cooled Jupiter radial engines.
Date: March 1927
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Breguet Military Airplane, Type 33: A Two-Place Long-Distance Sesquiplane for Observation and Bombing

Description: Circular presenting a description of the Breguet military airplane, Type 33, which is a two-place long-distance sesquiplane made for observation and bombing. Details of the components, bomb dropping, flying qualities, design, flying qualities and performances, drawings, and photographs are provided.
Date: September 1931
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Fokker "Trimotor F VII" Commercial Transport Monoplane

Description: Directly developed from the single engined type F VII ten passenger monoplanes, the Fokker Trimotor closely follows the commercial aircraft that preceded it. It has three Wright Whirlwind air-cooled engines, rated at 200 HP each. Details of the wings, cockpit and cabin, baggage and freight compartments, controls, landing gear, characteristics, drawings, and photographs are provided.
Date: June 1928
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Airspeed "Oxford" Training Airplane (British): A Two-Engine Cantilever Monoplane

Description: Circular describing the Airspeed A.S. 10 "Oxford", which is a twin-engine trainer with a variety of equipment, including propellers, landing gear, and other components.Details of the wings, fuselage, the inside, characteristics, performance, drawings, and photographs are provided.
Date: September 1937
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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