National Advisory Committee for Aeronautics (NACA) - 19 Matching Results

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An analysis of the factors affecting the loss in lift and shift in aerodynamic center produced by the distortion of a swept wing under aerodynamic load

Description: From Introduction: "The importance of this aeroelastic phenomenon has been recognized for some time, and several investigators have developed more or less refined methods for analysis of wing elastic distortions and their effects. (For examples, see refs. 1 to 4.) More specific evidence as to the influence of wing external geometry (in conjunction with flight condition) on this flexibility-longitudinial-stability problem would appear to be of interest to the aerodynamicist, however, so that he … more
Date: March 1953
Creator: Mathews, Charles W. & Kurbjun, Max C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An application of the method of characteristics to two-dimensional transonic flows with detached shock waves

Description: From Summary: "An application of the method of characteristics is presented which affords a means for determining the surface pressures for a class of two-dimensional airfoils of given nose shape and arbitrary rear part in a sonic or supersonic stream if surface pressure data are given for one member of the class. For engineering purposes, the method of characteristics may be replaced by a simple application of Prandtl-Meyer flow concepts. An explanation of the nonlinear force characteristics o… more
Date: March 1953
Creator: Harder, Keith C. & Klunker, E. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The calculation of pressure on slender airplanes in subsonic and supersonic flow

Description: "Under the assumption that a wing, body, or wing-body combination is slender or flying at near sonic velocity, expressions are given which permit the calculation of pressure in the immediate vicinity of the configuration. The disturbance field, in both subsonic and supersonic flight, is shown to consist of two-dimensional disturbance fields extending laterally and a longitudinal field that depends on the streamwise growth of cross-sectional area. A discussion is also given of couplings, between… more
Date: March 1953
Creator: Heaslet, Max A. & Lomax, Harvard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Design of Variable Mach Number Asymmetric Supersonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

Description: Report presenting two theoretical procedures for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One is for Mach numbers less than approximately 3 and one is for Mach numbers greater than 3.
Date: March 1953
Creator: Syvertson, Clarence A. & Savin, Raymond C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Direct-reading design charts for 24S-T3 aluminum-alloy flat compression panels having longitudinal formed hat-section stiffeners and comparisons with panels having Z-section stiffeners

Description: Report presenting direct-reading design charts for 24S-T3 aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. The charts make it possible to directly determine the stress and all panel proportions required to carry a given intensity of loading with a given skin thickness and effective length of panel. Results regarding simple compression, combined compression and bending, and combined compression, bending, and shear are provided.
Date: March 1953
Creator: Hickman, William A. & Dow, Norris F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of processing variables on the transition temperature, strength, and ductility of high-purity, sintered, wrought molybdenum metal

Description: Report presenting an investigation of the effect of processing variables on the properties of sintered, wrought molybdenum. The amount of swaging, recrystallization, and stress-relieving were considered.
Date: March 1953
Creator: Dike, Kenneth C. & Long, Roger A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of thermal properties on laminar-boundary-layer characteristics

Description: Report presenting an iteration method for solving the laminar-boundary-layer equations for compressible flow in the absence of a pressure gradient when the temperature variation of all the fluid thermal properties is considered. Results in regard to skin friction and heat-transfer characteristics are provided.
Date: March 1953
Creator: Klunker, E. B. & McLean, F. Edward
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Parallel-Jet Mixing on Downstream Mach Number and Stagnation Pressure With Application to Engine Testing in Supersonic Tunnels

Description: "A one-dimensional analysis of the results of the parallel-jet mixing encountered in the testing of engines in supersonic wind tunnels is reported. Equations were derived for determining the totla pressure and Mach number behind the tunnel terminal shock. The method represents a simple procedure for determining these quantities while a tunnel is still in the design stage" (p. 1).
Date: March 1953
Creator: Bernstein, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat and Momentum Transfer Between a Spherical Particle and Air Streams

Description: Note presenting experimentally determined heat-transfer coefficients for a spherical particle heated by an induction coil in a moving air stream for a range of Reynolds numbers using spheres of various sizes and various air velocities. The skin-friction factor representing the momentum transfer calculated from the boundary-layer theory showed good agreement with the experimental heat-transfer factor except in the lower range of Reynolds numbers studied.
Date: March 1953
Creator: Tang, Y. S.; Duncan, J. M. & Schweyer, H. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Impingement of Cloud Droplets on Aerodynamic Bodies as Affected by Compressibility of Air Flow Around the Body

Description: Note presenting the computation of the trajectories of water droplets in a compressible-air flow field around a cylinder using a mechanical analog. The results of the calculations at approximately the flight critical Mach number were compared with calculations of trajectories in an incompressible flow field. Results regarding the extension of cylinder results to airfoils are provided.
Date: March 1953
Creator: Brun, Rinaldo J.; Serafini, John S. & Gallagher, Helen M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Impingement of water droplets on a cylinder in an incompressible flow field and evaluation of rotating multicylinder method for measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds

Description: Report presenting an evaluation of the rotating multicylinder method for the measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds, which showed that small uncertainties in the basic data eliminate the distinction between cloud droplet-size distributions and are a source of large errors in the determination of droplet size. Matching curves for obtaining droplet-size distribution, volume-median droplet size, and liquid-water content from flight … more
Date: March 1953
Creator: Brun, Rinaldo J. & Mergler, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Impingement of Water Droplets on a Cylinder in an Incompressible Flow Field and Evaluation of Rotating Multicylinder Method for Measurement of Droplet-Size Distribution, Volume-Median Droplet-Size, and Liquid-Water Content in Clouds

Description: Note presenting an evaluation of the rotating method for the measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds, which showed that small uncertainties in basic data eliminate the distinction between cloud droplet-size distributions and are a source of large errors in the determination of the droplet size. Matching curves for obtaining droplet-size distribution, volume-median droplet size, and liquid-water content from flight data were comput… more
Date: March 1953
Creator: Brun, Rinaldo J. & Mergler, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A linear time-temperature relation for extrapolation of creep and stress-rupture data

Description: Report presenting a time-temperature parameter based on examination of the published stress-rupture data for a variety of materials, rather than on physical theory, is presented in equation form. An examination of published data on 40 materials representing ferritic and sustenitic steels, high-temperature alloys, and aluminum alloys is used to create conclusions.
Date: March 1953
Creator: Manson, S. S. & Haferd, A. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Low-Speed Experimental Study of the Directional Characteristics of a Sharp-Nosed Fuselage Through a Large Angle-of-Attack Range at Zero Angle of Sideslip

Description: Static yawing moments and some instantaneous yawing moments are presented through a range of angle of attack at zero sideslip angle for a plain fuselage model having a sharp conical nose and for the fuselage with several nose modifications, one of which consisted of a ring located at different stations along the nose. Some circumferential pressure measurements at one station on the body at several angles of attack are also presented.
Date: March 1953
Creator: Letko, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Matrix methods for determining the longitudinal-stability derivatives of an airplane from transient flight data

Description: Report presenting three matrix methods for determining the longitudinal-stability derivatives from transient flight data. The results obtained for the methods presented depend in a large measure on accurate instrument measurements and require considerable computation to yield adequate engineering answers.
Date: March 1953
Creator: Donegan, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method for Rapid Determination of the Icing Limit of a Body in Terms of the Stream Conditions

Description: "The effects of existing frictional heating were analyzed to determine the conditions under which ice formations on aircraft surfaces can be prevented. A method is presented for rapidly determining by means of charts the combination of-Mach number, altitude, and stream temperature which will maintain an ice-free surface in an icing cloud. The method can be applied to both subsonic and supersonic flow. The charts presented are for Mach numbers up to 1.8 and pressure altitudes from sea level to 4… more
Date: March 1953
Creator: Callaghan, Edmund E. & Serafini, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Modified Reynolds Analogy for the Compressible Turbulent Boundary Layer on a Flat Plate

Description: Note presenting a modified Reynolds analogy developed for the compressible turbulent boundary layer on a flat plate. When mixing-length theories are used to evaluate terms of the final expressions, it is found for air that the ratio of Stanton number to half the local skin-friction coefficient is greater than unity.
Date: March 1953
Creator: Rubesin, Morris W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Development of Turbulent Wakes from Vortex Streets

Description: "Wake development behind circular cylinders at Reynolds numbers from 40 to 10,000 was investigated in a low-speed wind tunnel. Standard hotwire techniques were used to study the velocity fluctuations. The Reynolds number range of periodic vortex shedding is divided into two distinct subranges. At R = 40 to 150, called the stable range, regular vortex streets are formed and no turbulent motion is developed" (p. 1).
Date: March 1953
Creator: Roshko, Anatol
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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