National Advisory Committee for Aeronautics (NACA) - 67 Matching Results

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An Analysis of the Effects of Aeroelasticity on Static Longitudinal Stability and Control of a Swept-Wing Airplane

Description: From Introduction: "The results of the aforementioned study are presented in this report together with the method of analysis employed. The net stability change is shown together with the individual contributions due to flexibility of wing, tail, and fuselage, both including and neglecting the effect of inertial loads."
Date: March 19, 1951
Creator: Skoog, Richard B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of Theodorsen's propeller theory to the calculation of the performance of dual-rotating propellers

Description: Report presenting the use of Theodorsen's propeller theory to calculate the performance of a dual-rotating propeller with nonideal load distributions. Results regarding the propeller characteristics were made for several blade-angle settings and flight Mach numbers.
Date: March 15, 1951
Creator: Gilman, Jean, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

Description: Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
Date: March 9, 1951
Creator: Hubbartt, James E. & Schum, Eugene F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Average Skin-Friction Coefficients From Boundary-Layer Measurements in Flight on a Parabolic Body of Revolution (NACA RM-10) at Supersonic Speeds and at Large Reynolds Numbers

Description: Report presenting boundary-layer measurements on rocket-powered free-flight models to determine average skin-friction coefficients. The test body, NACA RM-10, was a fin-stabilized parabolic body of revolution of fineness ratio 12.2 with a blunt base to provide space for a rocket jet. Results regarding the skin-friction and boundary-layer profiles and experimental and theoretical curves are provided.
Date: March 7, 1951
Creator: Rumsey, Charles B. & Loposer, J. Dan
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of the Bending Stresses in Helicopter Rotor Blades

Description: A comparatively rapid method is presented for determining theoretically the bending stresses of helicopter rotor blades in forward flight. The method is based on the analysis of the properties of a vibrating beam, and its uniqueness lies in the simple solution of the differential equation which governs the motion of the bent blades.
Date: March 1951
Creator: de Guillenchmidt, P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of flow over inclined bodies of revolution

Description: From Summary: "Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly ac… more
Date: March 5, 1951
Creator: Allen, H. Julian & Perkins, Edward W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for estimation of longitudinal-stability derivatives for a helicopter rotor in forward flight

Description: Report presenting charts to provide a convenient means for obtaining the derivatives of rotor resultant force, rotor pitching amount about the helicopter center of gravity, and rotor torque with respect to rotor angle of attack, forward speed, rotor speed, and collective pitch.
Date: March 1951
Creator: Amer, Kenneth B. & Gustafson, Frederic Bowen
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combustion properties of aluminum as ram-jet fuel

Description: Report presenting an experimental investigation to determine the combustion properties of aluminum as a fuel for use in high-speed aircraft. The aluminum fuel was injected both in powder and wire form into 2-inch-diameter ramjet-type combustors. Results regarding operational problems, thrust, and combustion efficiency are provided.
Date: March 28, 1951
Creator: Branstetter, J. Robert; Lord, Albert M. & Gerstein, Melvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Coolant-Flow Calibrations of Three Simulated Porous Gas-Turbine Blades

Description: "An investigation was conducted at the NACA Lewis laboratory to determine whether simulated porous gas-turbine blades fabricated by the Eaton Manufacturing Company of Cleveland, Ohio would be satisfactory with respect to coolant flow for application in gas-turbine engines. These blades simulated porous turbine blades by forcing the cooling air onto the blade surface through a large number of chordwise openings or slits between laminations of sheet metal or wire. This type of surface has a finit… more
Date: March 20, 1951
Creator: Esger, Jack B. & Lea, Alfred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooperative Investigation of Relationship Between Static and Fatigue Properties of Heat-Resistant Alloys at Elevated Temperatures

Description: Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.
Date: March 7, 1951
Creator: NACA Subcommittee on Heat-Resisting Materials
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correction Factors for Wind Tunnels of Elliptic Section With Partly Open and Partly Closed Test Section

Description: Jet boundary corrections for partly open and partly closed elliptical wind tunnels for the cases of one and two solid wall segments are presented. Also presented are the combinations of model span and extent of the solid portion of the tunnel wall for which the average correction factor is zero.
Date: March 1951
Creator: Riegels, Fritz W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of Supersonic Convective Heat-Transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10)

Description: Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.
Date: March 7, 1951
Creator: Chauvin, Leo T. & deMoraes, Carlos A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Velocities of Ultracentrifuges

Description: The Euler equations for the rotation of a solid body are applied to the problem of the motion of ultracentrifuges. Particular attention is paid to the problem of the passage of an ultracentrifuge rotor through the critical velocity. The factors that affect the passage of rotors through the critical point are stressed.
Date: March 1951
Creator: Sokolov, V. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Damping in a roll of a missile configuration with a modified triangular wing and a cruciform tail at a Mach number of 1.52

Description: Report presenting the damping-in-roll stability derivatives of a missile configuration and its components as determined experimentally and theoretically. The experimental damping derivative of the wing-body combination was found to be 67 percent of its theoretical value. Results are given for the wing-body combination, the tail-body combination, and the wing-tail-body combination.
Date: March 6, 1951
Creator: Scherrer, Richard & Dennis, David H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Description and Investigation of a Dynamic Model of the XH-17 Two-Blade Jet Driven Helicopter

Description: Report presenting a description and results of an investigation of a model of the XH-17 two-blade, jet-powered helicopter. Tests were made with a standard configuration and with several modifications, including varying the size of blade counterweights, changing the control stiffness and chordwise bending stiffness of the blades, and varying the pylon and undercarriage damping and spring constants. Results regarding flutter testing, ground-vibration tests, and three-per-revolution rotor-blade un… more
Date: March 14, 1951
Creator: Brooks, George W. & Sylvester, Maurice A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Mass Distribution on the Low-Speed Dynamic Lateral Stability and Control Characteristics of a Model With a 60 Degree Triangular Wing

Description: Memorandum presenting an investigation to determine the effect of mass distribution on the dynamic lateral stability and control characteristics of a model with a 60 degree triangular wing in the free-flight tunnel. Flight tests and calculations were made for five different loading conditions. Results regarding the oscillatory stability, lateral control, and general flight behavior are provided.
Date: March 9, 1951
Creator: Johnson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Electromagnetic Flowmeter for Rocket Research

Description: "A method of measuring instantaneous flow rates of liquid propellants for rocket research is presented. The instrument investigated utilizes the principle of electromagnetic induction. An electromagnetic flowmeter was built, investigated, and satisfactorily placed in service to measure the rate of flow of an oxidant into a rocket" (p. 1).
Date: March 6, 1951
Creator: Jaffe, Leonard; Coss, Bert A. & Daykin, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Error in Airspeed Measurement Due to Static-Pressure Field Ahead of the Wing Tip of a Swept-Wing Airplane Model at Transonic Speeds

Description: From Summary: "As part of a study of means of airspeed measurement at transonic speeds the use of static orifices located ahead of the wing tip has been investigated for possible application to service or research airspeed installations. The local static pressure and local Mach number have been measured at a distance of 1 tip chord ahead of the wing tip of a model of a swept-wing fighter airplane at true Mach numbers between 0.7 and 1.08 by the NACA wing-flow method. All measurements were made … more
Date: March 1, 1951
Creator: Danforth, Edward C. B. & O'Bryan, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental and theoretical studies of area suction for the control of the laminar boundary layer on an NACA 64A010 airfoil

Description: From Summary: "A low-turbulence wind-tunnel investigation was made of an NACA 64A010 airfoil having a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of suction to produce continuous inflow through the surface of the airfoil (area suction). In addition to the experimental investigation, a related theoretical analysis was made to provide a basis of comparison for the test results."
Date: March 30, 1951
Creator: Braslow, Albert L.; Burrows, Dale L.; Tetervin, Neal & Visconti, Fioravante
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of effects of design changes on performance of large-capacity centrifugal compressors

Description: Report presenting an investigation to determine the effects of several design changes on the performance of large-capacity, double-entry, centrifugal compressors. Four modifications of a turbojet engine compressor were operated over a range of equivalent impeller tip speeds an the compressor overall and component performances were determined. Results regarding the impeller performance, diffuser performance, and compressor performance are provided.
Date: March 2, 1951
Creator: Withee, Joseph R., Jr.; Kovach, Karl & Ginsburg, Ambrose
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of tail-pipe-burner design variables

Description: Report summarizing several experimental tail-pipe-burner investigations to indicate the effects of tail-pipe-burner design variables on the performance and operating characteristics. Most of the configurations were investigated over a wide range of altitudes and flight Mach numbers. The results indicate the desirable design features of a tail-pipe burner that will operate with high combustion efficiency and exhaust-gas temperature up to an altitude of approximately 50,000 feet.
Date: March 5, 1951
Creator: Fleming, W. A.; Conrad, E. William & Young, W. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fatigue strengths of aircraft materials: axial load fatigue tests on unnotched sheet specimens of 24S-T3 and 75S-T6 aluminum alloys and of SAE 4130 steel

Description: Report presenting information on the axial-load fatigue behavior of unnotched specimens of 24S-T3 and 75S-T6 aluminum alloys and normalized SAE 4130 steel. The primary objectives of the investigation were to determine fatigue strengths and measurements of damage due to stress level are provided. Results regarding static strength tests, fatigue strength tests, fatigue damage tests, and results at high and low speeds are provided.
Date: March 1951
Creator: Grover, H. J.; Bishop, S. M. & Jackson, L. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flame velocities of four alkylsilanes

Description: Report presenting the rates of flame propagation of four alkylsilanes as determined by the tube method. Results regarding alkylsilane flame velocities, blends of diethylsilane and n-pentane, and flame propagation theories are provided.
Date: March 9, 1951
Creator: Gerstein, Melvin; Wong, Edgar L. & Levine, Oscar
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Instrument for Measurement of Liquid-Water Content in Clouds at Temperatures Above and Below Freezing

Description: "A principle formerly used in an instrument for cloud detection was further investigated to provide a simple and rapid means for measuring the liquid-water content of clouds at temperatures above and below freezing. The instrument consists of a small cylindrical element so operated at high surface temperatures that the impingement of cloud droplets creates a significant drop in the surface temperature. The instrument is sensitive to a wide range of liquid-water content and was calibrated at one… more
Date: March 6, 1951
Creator: Perkins, Porter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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