National Advisory Committee for Aeronautics (NACA) - 2,223 Matching Results

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Results of Shear Fatigue Tests of Joints With 3/16-Inch-Diameter 24S-T31 Rivets in 0.064-Inch-Thick Alclad Sheet

Description: Note presenting shear fatigue tests of joints with rivets in Alclad sheet of several high-strength aluminum alloys. The results showed that the design of the joint gives a wider range of fatigue strengths than does the choice of material from the group studied. No one sheet alloy showed superiority over the others.
Date: February 1950
Creator: Holt, Marshall
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rise of Air Bubbles in Aircraft Lubricating Oils

Description: Note presenting measurements of the rates of rise of small air bubbles, up to 2 millimeters in diameter, at room temperature in an undoped oil, in the same oil containing foam inhibitors, and in an oil containing lubricating additives. The apparent diameter of the air bubbles was measured visually through an ocular micrometer on a traveling telescope. A method is derived to calculate the thickness of the liquid shell which would have to move with the bubbles in the doped oils to account for the… more
Date: February 1950
Creator: Robinson, J. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A small-deflection theory for curved sandwich plates

Description: From Summary: "A small-deflection theory that takes into account deformations due to transverse shear is presented for the elastic-behavior analysis of orthotropic plates of constant cylindrical curvature, with considerations of buckling included. The theory is applicable primarily to sandwich construction."
Date: February 1950
Creator: Stein, Manuel & Mayers, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static longitudinal stability and control of a convertible-type airplane as affected by articulated-and rigid-propeller operation

Description: Report presenting the results of an investigation in the full-scale tunnel of the static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation. The investigation included force measurements for a large angle-of-attack range of the model with the all-movable horizontal tail installed and removed. Results regarding the static longitudinal stability and control at normal-flight altitudes and transition range are provided.
Date: February 1950
Creator: Lange, Roy H. & McLemore, Huel C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tables for Determining Reduction of Energy and Intensity of X-Rays and Gamma-Rays at Various Scattering Angles in Small Thickness of Matter

Description: Report presenting tables for determining the total-absorption coefficients as well was the intensities and spectral distribution of gamma rays at any scattering angle. Both experimental and computed data on gamma rays of quantum energies up to 20 million electron volts for all elements which have significant data available are provided. The accuracy of results is obtained by the use of tables.
Date: February 1950
Creator: Allen, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Time-dependent downwash at the tail and the pitching moment due to normal acceleration at supersonic speeds

Description: Report presenting an analysis of the time-dependent downwash behind a wing in a supersonic stream when the angle of attack varies linearly with time. The result is applied to the calculation of the contribution of the horizontal tail to the pitching moment and lift due to normal acceleration of the airplane. Results regarding downwash charts and some limitations on the results are provided.
Date: February 1950
Creator: Ribner, Herbert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Variation With Temperature of Surface Tension of Lubricating Oils

Description: Note presenting surface-tension measurements from room temperature to 180 degrees Celsius of a series of aeronautical lubricating oils and a few liquids of associated interest. The critical temperatures of the liquids are calculated and a general classification of existing oils into three groups is provided.
Date: February 1950
Creator: Ross, Sydney
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Water Landing Investigation of a Model Having a Heavy Beam Loading and a 30 Degree Angle of Dead Rise

Description: Results presenting testing of a model with heavy beam loading and an angle of dead rise of 30 degrees subjected to smooth-water impacts in the Langley impact basin. Testing was made at fixed trims of 6 degrees, 15 degrees, 30 degrees, and 45 degrees for a range of flight-path angles and consistent beam-loading coefficient. Time histories of horizontal and vertical displacements, vertical velocity, vertical acceleration, and pitching moment are provided.
Date: February 1950
Creator: Batterson, Sidney A. & McArver, A. Ethelda
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of factors influencing the stability characteristics of symmetrical twin-intake Air-induction systems

Description: From Introduction: "Experimental investigations of air-induction systems in which the air flows of two intakes join in a common duct have inducted that many of these systems are subject to air-flow instability at low inlet-velocity ratios. Therefore, an analysis has been made to determine a proper basis for an explanation and to provide a more quantitative explanation of the flow instability and the flow reversal. This report presents the results of this analysis."
Date: March 1950
Creator: Martin, Norman J. & Holzhauser, Curt A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Chart for simplifying calculations of pressure drop of a high-speed compressible fluid under simultaneous action of friction and heat transfer - application to combustion-chamber cooling passages

Description: Report presenting a method for calculating the pressure drop of a high-speed compressible fluid in a constant-area duct under the simultaneous action of friction and heat transfer. The temperature distribution assumed in the development of the working chart can be made to closely approximate, in on one or two steps, the temperature distributions found in the cooling passages of ramjet and tail-pipe-burner combustion chambers.
Date: March 1950
Creator: Sibulkin, Merwin & Koffel, William K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic Similitude Between a Model and a Full-Scale Body for Model Investigation at Full-Scale Mach Number

Description: Note presenting an analysis for interpreting results of dynamic tests of a model investigated at full-scale Mach number in terms of the corresponding full-scale body. The analysis indicates that dynamic similarity for such a condition can be closely approximated although the effect of gravity is not to scale.
Date: March 1950
Creator: Neihouse, Anshal I. & Pepoon, Philip W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of heat and power extraction on turbojet-engine performance 1: analytical method of performance evaluation with compressor-outlet air bleed

Description: Report presenting an analytical investigation of the performance of a turbojet engine with air bled off at the compressor outlet. A wide range of engine and flight conditions are covered and air bleeds of 0 to 15 percent of the air mass flow are considered. Results are provided in the form of generalized performance charts that are applicable to a wide range of operating conditions.
Date: March 1950
Creator: Hensley, Reece V.; Rom, Frank E. & Koutz, Stanley L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of rate of change of angle of attack on the maximum lift of a small model

Description: Report presenting a wind-tunnel investigation of a partial model of a conventional fighter airplane to determine the effects of rate of change of angle of attack on its maximum lift. The results indicated that the maximum lift coefficient increased linearly with pitching velocity up to a limit value of the lift coefficient which depended on the Mach number.
Date: March 1950
Creator: Harper, Paul W. & Flanigan, Roy E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of an Aging Treatment on Life of Small Cast Vitallium Gas-Turbine Blades

Description: Note presenting an investigation conducted to determine the effects of an aging treatment on the life of a small cast Vitallium gas-turbine blades operated at a blade temperature of approximately 1500 degrees Fahrenheit and a stress of 20,000 pounds per square inch at the blade-failure plane. Twenty blades that were aged for 48 hours at 1500 degrees Fahrenheit were compared with 33 unaged blades. Results regarding turbine evaluation and metallurgical examination are provided.
Date: March 1950
Creator: Hoffman, Charles A. & Yaker, Charles
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of aircraft heaters 33: experimental determination of thermal and hydrodynamical behavior of air flowing along finned plates

Description: Report presenting an experimental investigation on the thermal and hydrodynamical behavior of air flowing along a steam-heated plate to which were attached cylindrical fins. The data indicate that the principal criterion for the application of the equations for heat transfer along unfinned flat plates is the initiation of a thermal boundary layer.
Date: March 1950
Creator: Boelter, L. M. K.; Leasure, R.; Romie, F. E.; Sanders, V. D.; Elswick, W. R. & Young, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method of Calibrating Airspeed Installations on Airplanes at Transonic and Supersonic Speeds by Use of Temperature Measurements

Description: Note presenting a method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by use of instrumentation in the airplane only. A description of the method and some suggestions for increasing the accuracy of the method are provided.
Date: March 1950
Creator: Zolovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method of computing subsonic flows around given airfoils

Description: From Summary: "An extremely simple computational method is established for obtaining circulatory flows around given bodies to a high degree of accuracy for flows satisfying the linear pressure and specific-volume equation of state. The method depends not on an integral equation but on the transformation from the holograph to the physical plane involving the determination of an arbitrary analytic function. The determination of the arbitrary analytic function by elementary means results in a clos… more
Date: March 1950
Creator: Gelbart, Abe & Resch, Daniel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Distribution and Damping in Steady Roll at Supersonic Mach Numbers of Flat Swept-Back Wing with Subsonic Edges

Description: Note presenting a method for calculating the pressure distribution and damping in steady roll at supersonic Mach numbers of thin, flat, sweptback wings with all edges straight and subsonic. It can be adapted to wings with negative rake at the tips, but the method is developed only for wings with streamwise tips.
Date: March 1950
Creator: Walker, Harold J. & Ballantyne, Mary B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Properties of a boron carbide-iron ceramal

Description: Report presenting an investigation to determine the properties of a boron carbide-iron ceramal. The properties were compared to the properties of hot-pressed boron carbide. The properties evaluated were room- and elevated-temperature modulus of rupture, resistance to fracture by thermal shock, density, and oxidation characteristics.
Date: March 1950
Creator: Lidman, William G. & Hamjian, H. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Spin-tunnel investigation to determine the effect on spin recoveries of reducing the opening shock load of spin-recovery parachutes

Description: Report presenting an investigation in the 20-foot free-spinning tunnel to determine whether the effectiveness of a spin-recovery parachute would be influenced by a reduction, through the use of a shock absorber, or the opening shock load. The results indicated that a given spin-recovery parachute was effective with or without a rubber shock absorber installed in the parachute towline. Results regarding the effect of the shock absorber on spin-recovery characteristics and effect of porosity and … more
Date: March 1950
Creator: Jones, Ira P., Jr. & Klinar, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tables of wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow

Description: Report presenting the wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow for a variety of Mach numbers. Various ratios of control-surface chord to airfoil chord are employed in the calculation and for each combination of chord ratio and Mach number, approximate 35 values of reduced frequency are utilized.
Date: March 1950
Creator: Huckel, Vera & Durling, Barbara J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Lift and Damping in Roll of Thin Sweptback Tapered Wings With Raked-in and Cross-Stream Wing Tips at Supersonic Speeds: Subsonic Leading Edges

Description: Note presenting the lift and damping in roll for families of thin sweptback tapered wings with raked-in and cross-stream wing tips. Equations were derived for wings that are contained within a boundary formed by the Mach lines, which means that the wing has subsonic leading edges, supersonic trailing edges, and supersonic wing tips.
Date: March 1950
Creator: Margolis, Kenneth
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Velocity Distribution on Wing Sections of Arbitrary Shape in Compressible Potential Flow 3: Circulatory Flows Obeying the Simplified Density-Speed Relation

Description: "The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determining the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerically by an iteration meth… more
Date: March 1950
Creator: Bers, Lipman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing various portions of the original chord from the trailing edge of the NACA 0012 airfoil section. Results regarding lift, drag, and pitching moment and aerodynamic center are provided.
Date: April 1950
Creator: Smith, Hamilton A. & Schaefer, Raymond F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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