Technical Report Archive & Image Library (TRAIL) - 339 Matching Results

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Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag

Description: "By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third fa… more
Date: August 21, 1951
Creator: Adams, Mac C.
Partner: UNT Libraries Government Documents Department
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Tanks test of a model of the hull of the Navy PB-1 flying boat - N.A.C.A. Model 52

Description: A model of the hull of the Navy PB-1 flying boat was tested in the N.A.C.A. tank as part of a program intended to provide information regarding the water performance of hulls of flying boats of earlier design for which hydrodynamic data have heretofore been unavailable. Tests were made according to the general method over the range of practical loadings with the model both fixed in trim and free to trim. A free-to-trim test according to the specific method was also made for the design load and … more
Date: August 1936
Creator: Allison, John M.
Partner: UNT Libraries Government Documents Department
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Comparison of the Experimental Pressure Distribution on an NACA 0012 Profile at High Speeds With That Calculated by the Relaxation Method

Description: Note presenting pressure-distribution measurements made on a 5-inch-chord NACA 0012 airfoil at zero angle of attack in the Langley rectangular high-speed tunnel, a 4- by 18-inch closed-throat tunnel, and compared with results calculated by Emmons for an equivalent airfoil-channel configuration by using the relaxation method.
Date: August 1950
Creator: Amick, James L.
Partner: UNT Libraries Government Documents Department
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Charts Relating the Compressive Buckling Stress of Longitudinally Supported Plates to the Effective Deflectional and Rotational Stiffness of the Supports

Description: Report presenting a stability analysis of a long flat rectangular plate subjected to uniform longitudinal compressive stress and support along its longitudinal edges and one or more other longitudinal lines by elastic line supports. This was performed in order to provide more information about stabilization methods for thin-wing construction. The effective stiffness of different supports and the buckling observed in different structures is provided.
Date: August 1953
Creator: Anderson, Roger A. & Semonian, Joseph W.
Partner: UNT Libraries Government Documents Department
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Effect of Stress-Solvent Crazing on Tensile Strength of Polymethyl Methacrylate

Description: Note presenting an investigation of the loss of strength of tensile specimens of polymethyl methacrylate as a result of stress-solvent crazing at 23 degrees Celsius and 50-percent relative humidity. the materials tested were commercial cast polymethyl-methacrylate sheets of both heat-resistant and ordinary grades from each of two manufacturers.
Date: August 1951
Creator: Axilrod, B. M. & Sherman, Martha A.
Partner: UNT Libraries Government Documents Department
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Properties of aircraft fuels

Description: Report presenting a combination of two previously published reports with an extension of the data to cover properties of fuels up to temperatures as high as 400 degrees Fahrenheit.
Date: August 1956
Creator: Barnett, Henry C. & Hibbard, Robert R.
Partner: UNT Libraries Government Documents Department
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Tank Tests to Determine the Effects of the Chine Flare of a Flying-Boat Hull N.A.C.A. Model Series 62 and 69

Description: Note presenting testing of twenty-two models of flying-boat hulls for the purpose of determining the effects on water resistance and spray of 13 variations in the transverse section of the bottom of the forebody and of three variations in the form of the afterbody. Generally, the effect of chine flare on the resistance was small, although the resistance of force with chine flare was generally less than the resistance of the form without chine flare.
Date: August 1939
Creator: Bell, Joe W. & Olson, Roland E.
Partner: UNT Libraries Government Documents Department
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On Two-Dimensional Flows of Compressible Fluids

Description: "This report is devoted to the study of two-dimensional steady motion of a compressible fluid. It is shown that the complete flow pattern around a closed obstacle cannot be obtained by the method of Chaplygin. In order to overcome this difficulty, a formula for the stream-function of a two-dimensional subsonic flow is derived" (p. 1).
Date: August 1945
Creator: Bergman, Stefan
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.
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.
Partner: UNT Libraries Government Documents Department
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A flight investigation of the effect of steady rolling on the natural frequencies of a body-tail combination

Description: Report presenting flight experiments with a freely falling model to observe the effects of steady rolling on the pitching and yawing motions of a body-tail combination. Steady rolling introduces yawing moments into the pitch oscillations and pitching motions into the yaw oscillations. Results regarding the experimental effects of steady-roll on no-roll natural frequencies, comparison of measured and experimental effects of steady rolling on the no-roll natural frequencies, and effects of roll a… more
Date: August 1953
Creator: Bergrun, Norman R. & Nickel, Paul A.
Partner: UNT Libraries Government Documents Department
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Internal-Friction Study of Aluminum Alloy Containing 4 Weight Percent Copper

Description: Note presenting a study of aluminum alloy containing 4 weight percent copper during aging using low-frequency internal-friction measurements in torsional and flexural vibration. Both polycrystalline and single-crystal specimens exhibit an initial internal-friction peak at 173 degrees Celsius after solution treatment and quenching.
Date: August 1958
Creator: Berry, B. S. & Nowick, A. S.
Partner: UNT Libraries Government Documents Department
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Column Strength of H-Sections and Square Tubes in Postbuckling Range of Component Plates

Description: Note presenting a calculation of the column buckling stress in the range where the component plates have buckled using the method of split rigidities. Tests were carried out for a considerable range of slenderness ratios on three H-sections and two square tube sections.
Date: August 1953
Creator: Bijlaard, P. P. & Fisher, G. P.
Partner: UNT Libraries Government Documents Department
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Effect of chemical reactivity of lubricant additives on friction and surface welding at high sliding velocities

Description: Report presenting an investigation of the effect of chemical reactivity of lubricant additives on friction at high sliding velocities. The investigation was conducted with a kinetic-friction apparatus consisting of an elastically restrained spherical rider specimen sliding on a rotating steel disk lubricated with cetane containing lubricant additives of different chemical reactivities. Results regarding chlorine compounds and sulfur compounds are provided.
Date: August 1950
Creator: Bisson, Edmond E.; Swikert, Max A. & Johnson, Robert L.
Partner: UNT Libraries Government Documents Department
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Driving Standing Waves by Heat Addition

Description: Note presenting types of burner instability and the role of standing waves in burners. The status of the problem of flame-driven standing waves is reviewed and a one-dimensional flow theory giving the mechanism whereby a flame drives or damps a standing wave is presented.
Date: August 1952
Creator: Blackshear, Perry L., Jr.
Partner: UNT Libraries Government Documents Department
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Fatigue Testing of Wing Beam by the Resonance Method

Description: "Preliminary fatigue tests on two aluminum-alloy wing-beam specimens subjected to reversed axial loading are described. The motion used consists in incorporating one or two reciprocating motors in a resonance system of which the specimen is the spring element. A description is given of the reciprocating motors, and of the method of assembling and adjusting the vibrating system" (p. 1).
Date: August 1938
Creator: Bleakney, William M.
Partner: UNT Libraries Government Documents Department
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An investigation of aircraft heaters 36: preliminary investigation of a combustion-type aircraft heater

Description: Report presenting experimental results on the thermal performance of an aircraft combustion-type heater. The performance of the heater with a counterflow and a parallel-flow return passage on the gas side does not appear predictable by use of existing equations. The thermal conductance for the gases within the combustion chamber is predicted to be many times lower than the experimental data indicate.
Date: August 1951
Creator: Boelter, L. M. K.; Elswick, W. R.; Sanders, V. D. & Rubesin, M. W.
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters XXVIII : Equations for Steady-State Temperature Distribution Caused by Thermal Sources in Flat Plates Applied to Calculation of Thermocouple Errors, Heat-meter Corrections, and Heat Transfer by Pin-fin Plates

Description: Report presenting an equation for steady-sate temperature distribution caused by a thermal source (or sink) in a flat plate surrounded on either side by fluids of different temperature and applications for three sections in the report.
Date: August 1948
Creator: Boelter, L. M. K.; Romie, F. E.; Guibert, A. G. & Miller, M. A.
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 34: Experimental Determination of Thermal and Hydrodynamical Behavior of Air Flowing Between a Flat and a Wave-Shaped Plate

Description: Report presenting an investigation of the thermal and hydrodynamical behavior of air flowing along a passage with one flat side, which was steam-heated, and one wave-shaped side, which was unheated. Two series of tests were conducted, one with the plates in direct opposition and one with the plates slightly separated, which induced turbulence upstream of the thermal boundary layer. Results regarding heat transfer and static-pressure drop are provided.
Date: August 1951
Creator: Boelter, L. M. K.; Sanders, V. D.; Young, G.; Morgan, M. & Morrin, E. H.
Partner: UNT Libraries Government Documents Department
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Flight Investigation on a Fighter-Type Airplane of Factors Which Affect the Loads and Load Distributions on the Vertical Tail Surfaces During Rudder Kicks and Fishtails

Description: Note presenting results of a flight investigation conducted on a fighter-type airplane to determine the factors which affect the loads and load distributions on the vertical tail surfaces in maneuvers. An analysis is made of the data obtained in steady flight, rudder kicks, and fishtail maneuvers.
Date: August 1947
Creator: Boshar, John
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Investigation of Gyroscopic Effects of Jet-Engine Rotating Parts (or of Rotating Propellers) on Spin and Spin Recovery

Description: Note presenting an investigation initiated in the 20-foot free-spinning tunnel to study the gyroscopic effects of jet-engine rotating parts on the erect spin and spin-recovery characteristics. A model of a military attack airplane was arbitrarily used and tests were made at basic and alternative loadings.
Date: August 1955
Creator: Bowman, James S., Jr.
Partner: UNT Libraries Government Documents Department
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Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Note presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: August 1956
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Partner: UNT Libraries Government Documents Department
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Two-dimensional wind-tunnel investigation of an approximately 14-percent-thick NACA 66-series-type airfoil section with a double slotted flap

Description: Report presenting a two-dimensional wind tunnel investigation for the purpose of developing a suitable double slotted flap on a 14-percent-thick modified NACA 66-series-type airfoil section. Section aerodynamic characteristics of the airfoil with various double-slotted-flap arrangements are presented. Results regarding the airfoil with the flap retracted and flap deflected are provided.
Date: August 1946
Creator: Braslow, Albert L. & Loftin, Laurence K., Jr.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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