Technical Report Archive & Image Library (TRAIL) - 222 Matching Results

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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.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Damping Screens

Description: From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date: January 1950
Creator: Schubauer, G. B.; Spangenberg, W. G. & Klebanoff, P. S.
Partner: UNT Libraries Government Documents Department
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Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Description: From Introduction: "The fundamental integral equation for the pressure distribution on an oscillating thin airfoil moving at subsonic speed has been derived by Possio in reference 1. Collocation procedures have been used by Possio, Frazer, and Skan, and others to obtain lift and moment on an oscillating first plate. An important contribution has been made by Dietze (see reference 2 and 3), who has developed an iterative procedure for numerical solution of Possio's integral equation."
Date: October 1950
Creator: Turner, M. J. & Rabinowitz, S.
Partner: UNT Libraries Government Documents Department
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The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Description: From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."
Date: September 1950
Creator: Stone, Ralph W., Jr.; Burk, Sanger M., Jr. & Bihrle, William, Jr.
Partner: UNT Libraries Government Documents Department
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Analysis for Control Application of Dynamic Characteristics of Turbojet Engine With Tail-Pipe Burning

Description: "The first basic problem that must be solved before control synthesis can proceed is that of determining the dynamic characteristics of the engine. Accordingly, an analysis of the dynamic behavior of the turbojet engine with tail-pipe burning was made at the NACA Lewis laboratory and is presented herein" (p. 1).
Date: September 1950
Creator: Feder, Melvin S. & Hood, Richard
Partner: UNT Libraries Government Documents Department
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Analysis of an induction blowdown supersonic tunnel

Description: From Introduction: "In the present paper, general ejector equations (see reference 4 or 5) and certain assumptions with regard to flow conditions and pressure losses have been utilized to calculate the running times of induction blowdown supersonic tunnels operating in the mentioned Mach number range."
Date: April 1950
Creator: Bidwell, Jerold M.
Partner: UNT Libraries Government Documents Department
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An analysis of base pressure at supersonic velocities and comparison with experiment

Description: From Introduction: "The primary purpose of the investigation described in the present report is to formulate a method which is of value for quantitative calculations of base pressure on airfoils and bodies without boat-tailing. Part I consists of a detailed study of the base pressure in two-dimensional and axially-symmetric inviscid flow. In part II a semi-empirical theory is formulated since the results of part I indicate that an inviscid-flow theory cannot possibly be satisfactory for quantit… more
Date: July 1950
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department
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Analysis of effect of variations in primary variables on time constant and turbine-inlet-temperature overshoot of turbojet engine

Description: From Introduction: "The design of turbojet-engine control systems is intimately related to the dynamic characteristics of the engine and has advanced to the stage where theoretically correct control constants can be determined for fixed dynamic properties (references 1 and 2). The use of the thermodynamic equations presupposes that the engine processes are quansi-static. Such an assumption is shown to be valid for a turbojet engine in references 3 and 4.
Date: September 1950
Creator: Heidmann, Marcus F.
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.
Partner: UNT Libraries Government Documents Department
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Analysis of shear strength of honeycomb cores for sandwich constructions

Description: From Introduction: "In the present report an analysis was undertaken to arrive at a mathematical formula by which the shear strengths of honeycomb core materials could be calculated. Experimental verification of the formula of the present paper was obtained by tests of honeycomb-type sheets of resin-impregated paper; two groups of specimens were tested, each of which represented a different resin-impregation treatment of the basic paper."
Date: October 1950
Creator: Werren, Fred & Norris, Charles Brazer
Partner: UNT Libraries Government Documents Department
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An analysis of the normal accelerations and airspeeds of a four-engine airplane type in postwar commercial transport operations on trans-Pacific and Caribbean-South American routes

Description: Report presenting an analysis of normal-acceleration and airspeed data on several transport airplanes of a four-engine type during postwar commerical operations on trans-Pacific and Caribbean-South American routes of the same airlines. The results indicate that the acceleration increment corresponding to the limit-gust-load-factor increment may be exceed about twice in all of the flight miles for each route. Results regarding accelerations, flight loads, gust encounters, and speeds are provided. more
Date: August 1950
Creator: Coleman, Thomas L. & Schumacher, Paul W. J.
Partner: UNT Libraries Government Documents Department
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Analytical and Experimental Investigation of Adiabatic Turbulent Flow in Smooth Tubes

Description: Note presenting equations derived for the prediction of velocity distributions for fully developed adiabtic turbulent flow in smooth tubes; both the incompressible and compressible flow cases were treated. The analysis produced a single equation that represents flow in both the conventional buffer layer and the laminar layer. The results for fully developed flow were correlated by using conventional dimensionless velocity and distance parameters, and agreed closely with those of Nikuradse and o… more
Date: July 1950
Creator: Deissler, Robert G.
Partner: UNT Libraries Government Documents Department
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Analytical Method for Determining Transmission and Absorption of Time-Dependent Radiation Through Thick Absorbers 3: Absorber With Radioactive Daughter Products

Description: Report presenting a theoretical treatment of absorption problems that considers the following cases: radiation is normal to an absorber with plane parallel surfaces, radiations are of several polyenergetic types, induced radioactive isotopes decay to stable atoms in multistep decay processes, and radiations from the absorber affect the time-dependency of the source activity. Radiation from intermediate isotopes can become more dangerous than the original activity, so the entire range of radiati… more
Date: June 1950
Creator: Allen, G.
Partner: UNT Libraries Government Documents Department
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Application of the Laplace Transformation to the Solution of the Lateral and Longitudinal Stability Equations

Description: Note presenting the application of the Laplace transformation to the solution of the lateral and longitudinal stability equations. The expressions for the time history of the motion in response to a sinusoidal control motion are derived for the general case in which all initial measurements are assumed different from zero.
Date: January 1950
Creator: Mokrzycki, G. A.
Partner: UNT Libraries Government Documents Department
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Application of the wire-mesh plotting device to incompressible cascade flows

Description: From Summary: "The methods used in the application of the wire-mesh plotting device to find the flow pattern about a cascade of airfoils in compressible inviscid flow and some mathematical checks that increase the accuracy of this application are described. Results for two typical turbine-blade cascades are shown to compare well with experimental data. A method of utilizing the wire mesh to design turbine blades with a prescribed pressure distribution in incompressible flow is presented."
Date: May 1950
Creator: Westphal, Willard R. & Dunavant, James C.
Partner: UNT Libraries Government Documents Department
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Approximate aerodynamic influence coefficients for wings of arbitrary plan form in subsonic flow

Description: From Summary: "Aerodynamic influence coefficients for symmetrically loaded wings of arbitrary plan form in subsonic flow are derived from a simple empirical method of estimating spanwise lift distributions. The application of the coefficients to an aeroelastic analysis is discussed."
Date: July 1950
Creator: Diederich, Franklin W.
Partner: UNT Libraries Government Documents Department
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An approximate method of calculating pressures in the tip region of a rectangular wing of circular-arc section at supersonic speeds

Description: From Introduction: "The present paper introduces the approximate method by means of which it is possible to calculate the pressures in the tip region of a rectangular with a symmetrical circular-arc section to a higher degree of accuracy than is possible with the usual linear methods."
Date: October 1950
Creator: Czarnecki, K. R. & Mueller, James N.
Partner: UNT Libraries Government Documents Department
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A Balsa-Dust Technique for Air-Flow Visualization and Its Application to Flow Through Model Helicopter Rotors in Static Thrust

Description: Note presenting a method of visualizing air-flow patterns by observing the motion of finely divided particles of balsa wood introduced into the air. Photographic results obtained by this method for small-scale models of several helicopter rotor configurations in the static-thrust condition are presented. The results indicate the feasibility of using the balsa-dust technique for obtaining useful qualitative information on the air-flow patterns for transient conditions as well as for steady-state… more
Date: November 1950
Creator: Taylor, Marion K.
Partner: UNT Libraries Government Documents Department
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Bending and buckling of rectangular sandwich plates

Description: "Differential equations and boundary conditions are derived for the bending and buckling of sandwich plates. The buckling load is calculated for a simply supported plate subjected to edgewise compression. The formulas are evaluated numerically and the results are plotted in a diagram" (p. 1).
Date: November 1950
Creator: Hoff, N. J.
Partner: UNT Libraries Government Documents Department
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Bonding Investigation of Titanium Carbide With Various Elements

Description: Report presenting a metallographic study of the interface between various elements and titanium carbide. Hardness measurements of the different elemental combinations are also provided.
Date: September 1950
Creator: Engel, Walter J.
Partner: UNT Libraries Government Documents Department
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The Boundary-Layer and Stalling Characteristics of the NACA 64A010 Airfoil Section

Description: Note presenting a wind-tunnel investigation of the NACA 64A010 airfoil section to determine the boundary-layer and stalling characteristics at low speed. The tests were made at a Reynolds number of 4.1 million and included force measurements, pressure-distribution measurements, flow studies by the liquid-film technique, and boundary-layer measurements.
Date: November 1950
Creator: Peterson, Robert F.
Partner: UNT Libraries Government Documents Department
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Boundary-layer measurements in 3.84- by 10-inch supersonic channel

Description: Report presenting boundary-layer measurements in the transonic and supersonic regions of a channel with maximum cross-sectional dimensions 3.84 by 10 inches and designed by potential-flow methods for a uniform Mach number of 2.08. Results regarding the Mach number distribution along the channel, temperature recovery and Prandtl number, boundary layer development, skin-friction coefficient, and secondary flows are provided.
Date: October 1950
Creator: Brinich, Paul F.
Partner: UNT Libraries Government Documents Department
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Boundary-Layer Transition on a Cooled 20 Degree Cone at Mach Numbers of 1.5 and 2.0

Description: Note presenting an investigation of the laminar boundary layer on a cooled 20 degree cone at Mach numbers of 1.5 and 2.0 to determine the variation of the position of transition with surface temperature for both constant surface temperatures and surface temperatures that increased toward the rear of the cone. The increase in the extent of the laminar boundary layer for uniform surface temperatures was found to be directly proportional to the difference between the surface and recovery temperatu… more
Date: July 1950
Creator: Scherrer, Richard
Partner: UNT Libraries Government Documents Department
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Calculated Engine Performance and Airplane Range for Variety of Turbine-Propeller Engines

Description: Note presenting an analysis of the performance of basic, reheat, regenerative, and regenerative-plus-reheat turbine-propeller engines. The analysis covered an overall range of flight speeds, altitudes, and turbine-inlet temperatures for a range of compressor pressure ratios.
Date: August 1950
Creator: Nagey, Tibor F. & Martin, Cecil G.
Partner: UNT Libraries Government Documents Department
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