National Advisory Committee for Aeronautics (NACA) - 388 Matching Results

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Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition

Description: Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date: August 12, 1948
Creator: Acker, Loren W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Results of Natural Icing of an Axial-Flow Turbojet Engine

Description: Memorandum presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Tail-pipe temperature increased from 761 to 1065 degrees Fahrenheit and the jet thrust decreased from 1234 to 910 pounds during a period of 45 minutes in icing. No general conclusions can be reached from the data because the icing condition was relatively light.
Date: August 6, 1948
Creator: Acker, Loren W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Wind-Tunnel Investigation of the Effect of Area Suction on the Laminar Boundary Layer Over an NACA 64A010 Airfoil

Description: Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hydrodynamic Characteristics of a Low-Drag, Planing-Tail Flying-Boat Hull

Description: Report discussing the hydrodynamic characteristics of a flying boat with a low-drag, planing-tail hull compared with a conventional-type hull. The planing-tail model had more take-off stability than the conventional model and had lower hydrodynamic resistance. Information about the landing stability, variation of trim with speed, and spray characteristics is also provided.
Date: October 21, 1948
Creator: Suydam, Henry B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Additional Abstracts Pertaining to Seaplanes

Description: "About 500 additional references pertaining to hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings:GENERAL INFORMATION, HYDROSTATICS, HYDRODYNAMICS, AERODYNAMICS, OPERATION, and RESEARCH. The compilation is an extension of NACA RM No. L6I13, entitled "Abstracts Pertaining to Seaplanes," by Jerold M. Bidwell and Douglas A. King. An author index and a subject index are included" (p. 1).
Date: March 9, 1948
Creator: Bidwell, Jerold M. & King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of a Ceramic Lining for a Combustion Chamber for Gas-Turbine Use

Description: Combustion chamber liners for gas turbines and experimental set-ups were tested for failure. A ceramic-lined test chamber was operated at fuel/air ratios up to 0.050. Thermal-shock evaluation indicated that a ceramic lining, which expands after firing, would crack but would not fall apart during operation. Refractoriness of the lining and the resistance to mechanical shock were adequate. In general, shell temperature reductions of approximately 400 deg F were effected by the use of this lining … more
Date: April 12, 1948
Creator: Woodward, William H. & Bobrowsky, A. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of hydrazine as a rocket fuel

Description: Report presenting an investigation of the properties of hydrazine, stability and corrosiveness with a number of construction materials, sensitivity to detonation and temperature, and spontaneous reaction with the oxidants, concentrated hydrogen peroxide, sodium permanganate solution, fuming nitric acid, and tetranitromethane. Results regarding corrosion and stability, sensitivity to temperature and detonation, and theoretical calculations are provided.
Date: May 24, 1948
Creator: Ordin, Paul M.; Miller, Riley O. & Diehl, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static tests of a shrouded and an unshrouded propeller

Description: Report presenting outdoor static testing made on two high-solidity propellers of different design, one shrouded and the other unshrouded. Three shrouds were tested to determine the effects of shroud length and exit area. Results regarding the action of shroud, results and comparison of propellers, and comparison with theory are provided.
Date: February 9, 1948
Creator: Platt, Robert J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Indirect Methods for Obtaining Ram-Jet Exhaust-Gas Temperature Applied to Fuel-Metering Control

Description: Memorandum presenting an analytical method developed that gives two independent means of obtaining the total-temperature ratio across a ram jet or across a turbojet tail-pipe burner without direct measurement of the final gas temperature. Experimental verification of the analysis has been obtained with a 20-inch ram jet over a wide range of operating conditions.
Date: January 14, 1948
Creator: Perchonok, Eugene; Sterbentz, William H. & Moore, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Aerodynamic Characteristics of a Model Tail Plane with Modified NACA 65-010 Sections and 0 Degree and 45 Degrees Sweepback

Description: Memorandum presenting wind-tunnel tests that have been made to determine the aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and a tapered plan form. Results were obtained with the model tail plane unswept and swept back. The data show the lift, drag, pitching-moment, and hinge-moment coefficient variation with angle of attack and flap deflection at various Mach numbers.
Date: January 12, 1948
Creator: Anderson, Joseph L. & Martin, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cyclic Engine Test of Cast Vitallium Turbine Buckets - 1

Description: Report presenting an investigation to correlate the engine service performance of cast Vitallium turbine buckets with standard laboratory metallurgical data. Data was obtained on four turbine wheels of Timken alloy with cast Vitallium buckets. Results regarding the engine test and metallurgical examination are provided.
Date: February 19, 1948
Creator: Farmer, J. Elmo; Darmara, F. N. & Poulson, Francis D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cyclic Engine Test of Cast Vitallium Turbine Buckets 2

Description: Memorandum presenting an investigation conducted to provide data that may be used to correlate the engine service performance of cast Vitallium turbine buckets with metallurgical properties. Data were obtained from four turbine wheels of Timken alloy with cast Vitallium buckets. Examination of 12 broken buckets indicated that 8 of the failures were probably caused by fatigue and 4 by impact with pieces of other broken buckets.
Date: January 12, 1948
Creator: Farmer, J. Elmo; Deutsch, George C. & Sikora, Paul F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area I : an inlet enclosing 61.5 percent of the maximum circumference of the forebody

Description: Report presenting tests at Mach numbers between 1.36 and 2.01 of a twin-scoop air intake enclosing 61.5 percent of the maximum circumference of a body of revolution and located five forebody diameters behind the apex, which showed that the total pressure recovered after diffusion was about 10 percent greater than that attained in previous tests with an annular entrance of the same area.
Date: January 21, 1948
Creator: Davis, Wallace F. & Goldstein, David L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of a Model Pursuit Airplane and Correlation With Flight-Test Results

Description: Report presenting the results of tests on a model of a jet-propelled airplane and a comparison of drag, maximum lift coefficient, and elevator angle required for level flight in the wind tunnel and in flight. Results regarding the aerodynamic characteristics, longitudinal control, wing pressure distribution, and dive-recovery flaps are provided.
Date: January 21, 1948
Creator: Cleary, Joseph W. & Gray, Lyle J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 1 The Effect of Combination With a Body Revolution and Height Above a Ground Plane

Description: Memorandum presenting low-speed wind-tunnel test conducted of a triangular wing of aspect ratio 2.0 with a symmetrical double-wedge section with a maximum thickness of 5 percent of the chord at 20 percent of the chord. The wing was also tested in the presence of a ground plane. Results regarding isolated wing and wing-body combinations, split-flap effectiveness, and ground effect are provided.
Date: August 27, 1948
Creator: Rose, Leonard M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Helicopter Stability

Description: Report presenting information about some of the fundamental concepts and lines of development that may be undertaken regarding helicopter stability. Some of the principles discussed include method of control, control lag, stability characteristics, control forces, and center of gravity. Some of the means for improvement discussed include use of a horizontal stabilizer, use of trim devices, use of power-operated controls, automatic controls, and choice and grouping of indicating instruments.
Date: April 12, 1948
Creator: Gustafson, F. B. & Reeder, J. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. 1: the effect of Reynolds number and Mach number on the aerodynamic characteristics of the wing with flap undeflected

Description: Report presenting testing of a semispan model of a wing of triangular plan form and aspect ratio 2 in the 12-foot pressure tunnel to determine the aerodynamic characteristics of the wing as influenced by the independent effects of Reynolds number and Mach number up to Mach numbers approaching unity. Results regarding the effect of body and effect of wing-profile modification are also provided.
Date: January 22, 1948
Creator: Edwards, George G. & Stephenson, Jack D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Two-Dimensional Wind-Tunnel Investigation at High Reynolds Numbers of an NACA 65A006 Airfoil With High-Lift Devices

Description: Report presenting an investigation of an NACA 65A006 airfoil equipped with high-lift devices, including a 0.15-chord drooped-nose flap and a 0.20-chord plain trailing-edge flap. Airfoil section lift, pitching-moment, and drag characteristics obtained at high Reynolds numbers and low Mach numbers with the flaps deflected individually and simultaneously are presented. At Reynolds numbers up to 9.0 x 10(exp 6), the optimum combination of drooped-nose and plain trailing-edge flaps increased the max… more
Date: February 4, 1948
Creator: Nuber, Robert J. & Gottlieb, Stanley M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-speed aerodynamic characteristics of horn and overhang balances on a full-scale elevator

Description: Report presenting high-speed wind tunnel testing of horn- and overhang-balance elevators on a full-scale, semispan, horizontal tail. The effects of unshielding the horn and unsealing the overhang were investigated. Results regarding aerodynamic characteristics, distortions of the tail, and critical Mach numbers are provided.
Date: February 27, 1948
Creator: Cleary, Joseph W. & Krumm, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet

Description: Memorandum presenting a flight investigation conducted on a 20-inch-diameter steady-flow ramjet at a range of altitudes and free-stream Mach numbers. Results regarding the variation of combustion efficiency with fuel-air ratio and pressure altitude, effects of combustion-chamber-inlet velocity, and altitude on the operating range of fuel-air ratio are provided. The ramjet unit operated smoothly over the entire range of velocities and altitudes with the exception of occasional rough operation at… more
Date: January 14, 1948
Creator: Disher, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical analysis of the performance of a supersonic ducted rocket

Description: Report presenting calculated performance characteristics of a ducted rocket with gasoline and liquid oxygen as the fuel mixture and with a mass flow of 1 slug per second. Evaluations of net thrust, frontal area, thrust per unit frontal area, and specific fuel consumption are given for all of the flight conditions under which it might operate.
Date: February 13, 1948
Creator: Hensley, Reece V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation at Low Speeds of Swept Wings in Yawing Flow

Description: Memorandum presenting a wind-tunnel investigation conducted to determine the rotary stability characteristics in yawing flow of a series of untapered wings with angles of sweep of -45, 0, 45, and 60 degrees. The results of the yawing-flow tests indicated that the values of the rotary derivatives agreed fairly well with simple sweep theory for a moderate range of lift coefficients.
Date: February 4, 1948
Creator: Goodman, Alex & Feigenbaum, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of a piston-type gas-generator engine

Description: From Introduction: "An analysis of an engine having a division of work such that the power of the reciprocating engine is just sufficient to drive the compressor is reported herein. This combination of a reciprocating-type internal-combustion engine that drives its own supercharging compressor and generates gas for further expansion through a turbine will be called a piston-type gas generator in this report."
Date: February 18, 1948
Creator: Tauschek, Max J. & Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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