Latest content added for Digital Library Collection: National Advisory Committee for Aeronautics (NACA)https://digital.library.unt.edu/explore/collections/NACA/browse/?sort=date_d&display=list2011-11-11T19:22:00-06:00UNT LibrariesThis is a custom feed for browsing Digital Library Collection: National Advisory Committee for Aeronautics (NACA)The Theory of the Pitot and Venturi Tubes, Part 22011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53589/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53589/"><img alt="The Theory of the Pitot and Venturi Tubes, Part 2" title="The Theory of the Pitot and Venturi Tubes, Part 2" src="https://digital.library.unt.edu/ark:/67531/metadc53589/small/"/></a></p><p>None</p>Elements of the Wing Section Theory and of the Wing Theory2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53404/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53404/"><img alt="Elements of the Wing Section Theory and of the Wing Theory" title="Elements of the Wing Section Theory and of the Wing Theory" src="https://digital.library.unt.edu/ark:/67531/metadc53404/small/"/></a></p><p>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.</p>Flow and Drag Formulas for Simple Quadrics2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53407/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53407/"><img alt="Flow and Drag Formulas for Simple Quadrics" title="Flow and Drag Formulas for Simple Quadrics" src="https://digital.library.unt.edu/ark:/67531/metadc53407/small/"/></a></p><p>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.</p>Flow and Force Equations for a Body Revolving in a Fluid2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53409/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53409/"><img alt="Flow and Force Equations for a Body Revolving in a Fluid" title="Flow and Force Equations for a Body Revolving in a Fluid" src="https://digital.library.unt.edu/ark:/67531/metadc53409/small/"/></a></p><p>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.</p>General Potential Theory of Arbitrary Wing Sections2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53411/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53411/"><img alt="General Potential Theory of Arbitrary Wing Sections" title="General Potential Theory of Arbitrary Wing Sections" src="https://digital.library.unt.edu/ark:/67531/metadc53411/small/"/></a></p><p>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.</p>General Theory of Aerodynamic Instability and the Mechanism of Flutter2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53413/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53413/"><img alt="General Theory of Aerodynamic Instability and the Mechanism of Flutter" title="General Theory of Aerodynamic Instability and the Mechanism of Flutter" src="https://digital.library.unt.edu/ark:/67531/metadc53413/small/"/></a></p><p>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.</p>Graphic Construction of Joukowski Wings2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53401/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53401/"><img alt="Graphic Construction of Joukowski Wings" title="Graphic Construction of Joukowski Wings" src="https://digital.library.unt.edu/ark:/67531/metadc53401/small/"/></a></p><p>A plot of the cross sectional outline of a Joukowski wing is presented.</p>The Inertia Coefficients of an Airship in a Frictionless Fluid2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53406/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53406/"><img alt="The Inertia Coefficients of an Airship in a Frictionless Fluid" title="The Inertia Coefficients of an Airship in a Frictionless Fluid" src="https://digital.library.unt.edu/ark:/67531/metadc53406/small/"/></a></p><p>The apparent inertia of an airship hull is examined. The exact solution of the aerodynamical problem is studied for hulls of various shapes with special attention given to the case of an ellipsoidal hull. So that the results for the ellipsoidal hull may be readily adapted to other cases, they are expressed in terms of the area and perimeter of the largest cross section perpendicular to the direction of motion by means of a formula involving a coefficient kappa which varies only slowly when the shape of the hull is changed, being 0.637 for a circular or elliptic disk, 0.5 for a sphere, and about 0.25 for a spheroid of fineness ratio. The case of rotation of an airship hull is investigated and a coefficient is defined with the same advantages as the corresponding coefficient for rectilinear motion.</p>The Minimum Induced Drag of Aerofoils2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53402/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53402/"><img alt="The Minimum Induced Drag of Aerofoils" title="The Minimum Induced Drag of Aerofoils" src="https://digital.library.unt.edu/ark:/67531/metadc53402/small/"/></a></p><p>Equations are derived to demonstrate which distribution of lifting elements result in a minimum amount of aerodynamic drag. The lifting elements were arranged (1) in one line, (2) parallel lying in a transverse plane, and (3) in any direction in a transverse plane. It was shown that the distribution of lift which causes the least drag is reduced to the solution of the problem for systems of airfoils which are situated in a plane perpendicular to the direction of flight.</p>Pressure Distribution on Joukowski Wings2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53400/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53400/"><img alt="Pressure Distribution on Joukowski Wings" title="Pressure Distribution on Joukowski Wings" src="https://digital.library.unt.edu/ark:/67531/metadc53400/small/"/></a></p><p>The hydrodynamics and mathematical models as applied to the potential flow about a Joukowski wing are presented.</p>