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Additional Static and Fatigue Tests of High-Strength Aluminum-Alloy Bolted Joints
From Introduction: "Early in 1951 the National Advisory Committee for Aeronautics published, as Technical Note 2276 (ref. 1), a report by the Aluminum Research Laboratories of the Aluminum Company of America on the results of static and fatigue tests of high-strength aluminum alloy monobloc specimens and bolted joints. In view of special interest shown by several aircraft companies, certain expansions of the test program were undertaken by the Aluminum Research Laboratories and are reported herein."
Date:
July 1954
Creator:
Hartmann, E. C.; Holt, Marshall & Eaton, I. D.
System:
The UNT Digital Library
Aerodynamic Investigation of a Cup Anemometer
Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Date:
July 1934
Creator:
Hubbard, John D. & Brescoll, George P.
System:
The UNT Digital Library
Aerodynamic Properties of Slender Wing-Body Combinations at Subsonic, Transonic, and Supersonic Speeds
From Introduction: "In an incomprehensible medium, the mutual interference of a fuselage and wing of high-aspect ratio (to which lifting-line theory is applicable) has been treated by Lennertz, Wiselsberger, Pepper, and Multhopp in reference 1, 2, 3, and 4. It is the purpose of this note to treat the effect of on the aerodynamic loading of the mutual interference between a low-aspect-ratio pointed wing and a fuselage consisting of a slender body of revolution."
Date:
July 1948
Creator:
Spreiter, John R.
System:
The UNT Digital Library
Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds
From Introduction: "The present paper contains a first-order evaluation of a number of aerodynamic derivatives for a rectangular wing of infinite aspect ratio at finite angles of attack, based upon the linear perturbation theory for rotational flow."
Date:
July 1955
Creator:
Martin, John C. & Malvestuto, Frank S., Jr.
System:
The UNT Digital Library
An analysis of base pressure at supersonic velocities and comparison with experiment
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 quantitative calculations of a viscous flow."
Date:
July 1950
Creator:
Chapman, Dean R.
System:
The UNT Digital Library
An analysis of buzzing in supersonic ram jets by a modified one-dimensional nonstationary wave theory
From Introduction: "The buzz or pulsation of axially symmetric supersonic inlets having central bodies has been the subject of investigations since Oswatitsch first observed the phenomenon in 1944 (ref.1). This buzzing is essentially an oscillation of the normal shock along the spike of certain diffusers operating at mass flows below design, and this buzz decreases the performance of the propulsion units appreciably (ref.2). This paper continues the analysis of the buzzing cycle by means of a modified one-dimensional approach."
Date:
July 1956
Creator:
Trimpi, Robert L.
System:
The UNT Digital Library
Analysis of propeller efficiency losses associated with heated-air thermal de-icing
From Introduction: "The results of the tests made with unheated internal flow are reported in reference 1. It is the purpose of this paper to attempt to express simply the efficiency loss as a function of the parameters which govern propeller operation and the internal air flow. The derived equations are correlated with the data presented in reference 1."
Date:
July 1946
Creator:
Corson, Blake W. & Maynard, Julian D.
System:
The UNT Digital Library
Analysis of Square Shear Web Above Buckling Load
"A solution of Von Karman's fundamental equations for plates with large deflections is presented for the case of a shear web divided into square panels by reinforcing struts. Numerical solutions are given for struts of infinite rigidity and for struts the weight of which is one-fourth the weight of the sheet. The results are compared with Wagner's diagonal tension theory as extended by Kuhn and by Langhaar. It is found that the diagonal tension theory as developed by Kuhn agrees best with the present paper in the practical range when r=1/4. Kuhn's theory is in especially good agreement for the force in the strut when r=1/4" (p. 1).
Date:
July 1944
Creator:
Levy, Samuel; Fienup, Kenneth L. & Woolley, Ruth M.
System:
The UNT Digital Library
An analysis of the main spray characteristics of some full-size multi-engined flying boats
From Introduction: "Because of the importance of spray height, it is the purpose of the work considered in this report to attempt to determine a correlation for the main spray height in relatively smooth water."
Date:
July 1946
Creator:
Locke, F. W. S., Jr.
System:
The UNT Digital Library
An analysis of the normal accelerations and airspeeds of a two-engine type of transport airplane in commercial operations on routes in the central United States from 1948 to 1950
Report presenting normal-acceleration and airspeed data obtained from V-G recorders installed in a two-engine type of transport airplane, employed in routine commercial operation in the United States for two years, which was analyzed to determine the gust and gust-load experiences of the airplane. Results regarding the acceleration experience, gust experience, average operating airspeed, maximum airspeed, comparison of predicted gust envelopes, and predicted gust-load envelopes are provided.
Date:
July 1952
Creator:
Walker, Walter G. & Schumacher, Paul W. J.
System:
The UNT Digital Library
Analysis of two-dimensional compressible-flow loss characteristics downstream of turbomachine blade rows in terms of basic boundary-layer characteristics
Report presenting the effect of compressibility on the loss characteristics downstream of two-dimensional turbomachine blade rows. In this particular example, increasing the trailing-edge thickness increased the overall loss coefficients significantly, with an effect of compressibility only at exit flow angles close to axial.
Date:
July 1955
Creator:
Stewart, Warner L.
System:
The UNT Digital Library
Analytical and Experimental Investigation of Adiabatic Turbulent Flow in Smooth Tubes
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 other investigators.
Date:
July 1950
Creator:
Deissler, Robert G.
System:
The UNT Digital Library
Analytical Investigation of Fully Developed Laminar Flow in Tubes With Heat Transfer With Fluid Properties Variable Along the Radius
"In the analytical investigation reported herein, which was conducted in the NACA Lewis laboratory, both velocity and temperature distribution are obtained for fully developed laminar flow in tubes of gases and of liquid metals with variable fluid properties" (p. 1).
Date:
July 1951
Creator:
Deissler, Robert G.
System:
The UNT Digital Library
Applicability of Similarity Principles to Structural Models
"A systematic account is given in part I of the use of dimensional analysis in constructing similarity conditions for models and structures. The analysis covers large deflections, buckling, plastic behavior, and materials with nonlinear stress-strain characteristics, as well as the simpler structural problems" (p. 1).
Date:
July 1944
Creator:
Goodier, J. N. & Thomson, W. T.
System:
The UNT Digital Library
Application of X-Ray Absorption to Measurement of Small Air-Density Gradients
Report presenting an analysis of two x-ray absorption methods for determining small air-density gradients. One method uses a Geiger-Mueller counter for detection and the other uses photographic film for detection. Both of the methods are found to have some advantages and disadvantages.
Date:
July 1951
Creator:
Weltmann, Ruth N.; Fairweather, Steven & Papke, Daryl
System:
The UNT Digital Library
Approximate aerodynamic influence coefficients for wings of arbitrary plan form in subsonic flow
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.
System:
The UNT Digital Library
Approximate design method for high-solidity blade elements in compressors and turbines
Note presenting an approximate blade-element design method for compressible or incompressible nonviscous flow in high-solidity stators or rotors of axial-, radial-, or mixed-flow compressors, turbines, or two-dimensional cascades. The method is based upon channel-type flow between blade elements on a specified surface of revolution that lies between the hub and shroud and is concentric with the axis of the compressor turbine.
Date:
July 1951
Creator:
Stanitz, John D.
System:
The UNT Digital Library
Approximate method for determining equilibrium operation of compressor component of turbojet engine
Report presenting a method for estimating the equilibrium operating line for a compressor as a component part of a turbojet engine. Charts are presented for locating the equilibrium operating line on the performance map of the compressor component of a turbojet engine operating at sea-level static conditions. Results regarding design-point operation, off-design operation, effect of compressor-discharge bleed, effect of jet-nozzle adjustment, and an example are provided.
Date:
July 1955
Creator:
Huppert, Merle C.
System:
The UNT Digital Library
Approximate Method for Predicting Form and Location of Detached Shock Waves Ahead of Plane or Axially Symmetric Bodies
Note presenting an approximate method developed to predict the location of detached shock waves ahead of two-dimensional and axially symmetric bodies. The method is based on the continuity relation, which is applied to the air that passes the sonic line.
Date:
July 1949
Creator:
Moeckel, W. E.
System:
The UNT Digital Library
Axial Fatigue Test at Two Stress Amplitudes of 0.032-Inch 24S-T Sheet Specimens With a Circular Hole
Report presenting testing of the effect of applying a number of cycles of a high fatigue stress followed by a number of cycles of relatively low stress to failure has been investigated on 93 drilled specimens of a 24S-T sheet. The results indicated that any general formula for endurance must take sequence into consideration, which makes overly simple formulas inadequate to describe endurance over varying stress amplitudes.
Date:
July 1945
Creator:
Brueggeman, W. C.; Mayer, M., Jr. & Smith, W. H.
System:
The UNT Digital Library
Axial-Momentum Theory for Propellers in Compressible Flow
Note presenting the development of the axial-momentum theory for compressible flow as a step in the formulation of a rational propeller theory for compressible flow. The simple theory neglects some properties but predicts flow conditions through a propeller that are significantly different from the conditions predicted by the incompressible-flow theory.
Date:
July 1951
Creator:
Vogeley, Arthur William
System:
The UNT Digital Library
Behavior of materials under conditions of thermal stress
Report presenting a review of available information on the behavior of brittle and ductile materials under conditions of thermal stress and thermal shock. A number of practical methods that have been used to minimize the negative effects of thermal stress and shock are provided.
Date:
July 1953
Creator:
Manson, S. S.
System:
The UNT Digital Library
Bench-Test Investigation of the Transient-Response Characteristics of Several Simulated Airplanes Incorporating an Autopilot Sensitive to Yawing Accelerations
Note presenting testing of an autopilot sensitive to yawing acceleration, which was used to control four simulated airplane (mass-spring) configurations, and a series of bench tests to determine the response characteristics of the combinations.
Date:
July 1951
Creator:
Howard, Donald A.
System:
The UNT Digital Library
Bending Tests of Ring-Stiffened Circular Cylinders
Twenty-five ring-stiffened circular cylinders were loaded to failure in bending. The results are presented in the form of design curves which are applicable to cylinders with heavy rings that fail as a result of local buckling.
Date:
July 1956
Creator:
Peterson, James P.
System:
The UNT Digital Library