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  Partner: UNT Libraries Government Documents Department
 Decade: 1970-1979
 Year: 1979
 Collection: Technical Report Archive and Image Library
The Aerodynamic Forces on Airship Hulls

The Aerodynamic Forces on Airship Hulls

Date: December 1, 1979
Creator: Munk, M. M.
Description: The new method for making computations in connection with the study of rigid airships, which was used in the investigation of Navy's ZR-1 by the special subcommittee of the National Advisory Committee for Aeronautics appointed for this purpose is presented. The general theory of the air forces on airship hulls of the type mentioned is described and an attempt was made to develop the results from the very fundamentals of mechanics.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of Tentative Seismic Design Provisions for Buildings

Analysis of Tentative Seismic Design Provisions for Buildings

Date: July 1979
Creator: Harris, James Robert; Fenves, Steven J. & Wright, Richard N.
Description: Report issued by the U.S. National Bureau of Standards discussing an analysis of seismic design provisions for buildings with three main objectives. As stated in the introduction, "The first objective was to assist the ATC in the preparation of its report. The second objective of the study was to augment the text of the published Provisions by providing a formal, consistent documentation of the text. The third objective was to provide alternate arrangements of the Provisions that would make them more readily usable by several categories of users" (p. 1). This report includes illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Applications of Modern Hydrodynamics to Aeronautics. Part 1: Fundamental Concepts and the Most Important Theorems. Part 2: Applications

Applications of Modern Hydrodynamics to Aeronautics. Part 1: Fundamental Concepts and the Most Important Theorems. Part 2: Applications

Date: December 1, 1979
Creator: Prandtl, L.
Description: A discussion of the principles of hydrodynamics of nonviscous fluids in the case of motion of solid bodies in a fluid is presented. Formulae are derived to demonstrate the transition from the fluid surface to a corresponding 'control surface'. The external forces are compounded of the fluid pressures on the control surface and the forces which are exercised on the fluid by any solid bodies which may be inside of the control surfaces. Illustrations of these formulae as applied to the acquisition of transformations from a known simple flow to new types of flow for other boundaries are given. Theoretical and experimental investigations of models of airship bodies are presented.
Contributing Partner: UNT Libraries Government Documents Department
Construction of a Large Transverse Electromagnetic Cell

Construction of a Large Transverse Electromagnetic Cell

Date: February 1979
Creator: Decker, W. F. & Wilson, W. A.
Description: Report issued by the U.S. National Bureau of Standards discussing the construction of large electromagnetic cells. As stated in the introduction, "this instruction provides information and procedures necessary to fabricate a large transverse electromagnetic (TEM) cell to be used for experimental "electromagnetic interference" (EMI) evaluation studies" (p. 1). This report includes illustrations, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
Electromagnetic Boundary-Value Problems Based Upon a Modification of Residue Calculus and Function Theoretic Techniques

Electromagnetic Boundary-Value Problems Based Upon a Modification of Residue Calculus and Function Theoretic Techniques

Date: June 1979
Creator: Montgomerey, James Patrick & Chang, David C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Elements of the Wing Section Theory and of the Wing Theory

Elements of the Wing Section Theory and of the Wing Theory

Date: December 1, 1979
Creator: Munk, Max M.
Description: Results are presented of the theory of wings and of wing sections which are of immediate practical value. They are proven and demonstrated by the use of the simple conceptions of kinetic energy and momentum only.
Contributing Partner: UNT Libraries Government Documents Department
Flow and Drag Formulas for Simple Quadrics

Flow and Drag Formulas for Simple Quadrics

Date: December 1, 1979
Creator: Zahm, A. F.
Description: The pressure distribution and resistance found by theory and experiment for simple quadrics fixed in an infinite uniform stream of practically incompressible fluid are calculated. The experimental values pertain to air and some liquids, especially water; the theoretical refer sometimes to perfect, again to viscid fluids. Formulas for the velocity at all points of the flow field are given. Pressure and pressure drag are discussed for a sphere, a round cylinder, the elliptic cylinder, the prolate and oblate spheroid, and the circular disk. The velocity and pressure in an oblique flow are examined.
Contributing Partner: UNT Libraries Government Documents Department
Flow and Force Equations for a Body Revolving in a Fluid

Flow and Force Equations for a Body Revolving in a Fluid

Date: December 1, 1979
Creator: Zahm, A. F.
Description: A general method for finding the steady flow velocity relative to a body in plane curvilinear motion, whence the pressure is found by Bernoulli's energy principle is described. Integration of the pressure supplies basic formulas for the zonal forces and moments on the revolving body. The application of the steady flow method for calculating the velocity and pressure at all points of the flow inside and outside an ellipsoid and some of its limiting forms is presented and graphs those quantities for the latter forms. In some useful cases experimental pressures are plotted for comparison with theoretical. The pressure, and thence the zonal force and moment, on hulls in plane curvilinear flight are calculated. General equations for the resultant fluid forces and moments on trisymmetrical bodies moving through a perfect fluid are derived. Formulas for potential coefficients and inertia coefficients for an ellipsoid and its limiting forms are presented.
Contributing Partner: UNT Libraries Government Documents Department
General Potential Theory of Arbitrary Wing Sections

General Potential Theory of Arbitrary Wing Sections

Date: December 1, 1979
Creator: Theodorsen, T. & Garrick, I. E.
Description: The problem of determining the two dimensional potential flow around wing sections of any shape is examined. The problem is condensed into the compact form of an integral equation capable of yielding numerical solutions by a direct process. An attempt is made to analyze and coordinate the results of earlier studies relating to properties of wing sections. The existing approximate theory of thin wing sections and the Joukowski theory with its numerous generalizations are reduced to special cases of the general theory of arbitrary sections, permitting a clearer perspective of the entire field. The method which permits the determination of the velocity at any point of an arbitrary section and the associated lift and moments is described. The method is also discussed in terms for developing new shapes of preassigned aerodynamical properties.
Contributing Partner: UNT Libraries Government Documents Department
General Theory of Aerodynamic Instability and the Mechanism of Flutter

General Theory of Aerodynamic Instability and the Mechanism of Flutter

Date: December 1, 1979
Creator: Theodorsen, Theodore
Description: The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom were determined. The problem resolves itself into the solution of certain definite integrals, which were identified as Bessel functions of the first and second kind, and of zero and first order. The theory, based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability was analyzed. An exact solution, involving potential flow and the adoption of the Kutta condition, was derived. The solution is of a simple form and is expressed by means of an auxiliary parameter k. The flutter velocity, treated as the unknown quantity, was determined as a function of a certain ratio of the frequencies in the separate degrees of freedom for any magnitudes and combinations of the airfoil-aileron parameters.
Contributing Partner: UNT Libraries Government Documents Department
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