Latest content added for UNT Digital Library Collection: National Advisory Committee for Aeronautics (NACA)http://digital.library.unt.edu/explore/collections/NACA/browse/?fq=untl_institution:UNTGD2014-09-25T20:32:43-05:00UNT LibrariesThis is a custom feed for browsing UNT Digital Library Collection: National Advisory Committee for Aeronautics (NACA)Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc100822/<p><a href="/ark:/67531/metadc100822/"><img alt="Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section" title="Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section" src="/ark:/67531/metadc100822/thumbnail/"/></a></p><p>Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges.</p>Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc100823/<p><a href="/ark:/67531/metadc100823/"><img alt="Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique" title="Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique" src="/ark:/67531/metadc100823/thumbnail/"/></a></p><p>Carpet plots included permit the selection of the blade camber and the design angle of attack required to fulfill a design vector diagram. Other carpet plots provide means for the prediction of off-design turning angles.</p>Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc100824/<p><a href="/ark:/67531/metadc100824/"><img alt="Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades" title="Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades" src="/ark:/67531/metadc100824/thumbnail/"/></a></p><p>Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.</p>Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc100821/<p><a href="/ark:/67531/metadc100821/"><img alt="Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K" title="Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K" src="/ark:/67531/metadc100821/thumbnail/"/></a></p><p>Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition.</p>Tables and Charts of Flow Parameters Across Oblique Shocks2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc172508/<p><a href="/ark:/67531/metadc172508/"><img alt="Tables and Charts of Flow Parameters Across Oblique Shocks" title="Tables and Charts of Flow Parameters Across Oblique Shocks" src="/ark:/67531/metadc172508/thumbnail/"/></a></p><p>Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy.</p>A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc172515/<p><a href="/ark:/67531/metadc172515/"><img alt="A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow" title="A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow" src="/ark:/67531/metadc172515/thumbnail/"/></a></p><p>Comparison of free-molecule-flow theory with the results of wind-tunnel tests performed to determine the drag and temperature-rise characteristics of a transverse circular cylinder.</p>Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc172521/<p><a href="/ark:/67531/metadc172521/"><img alt="Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method" title="Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method" src="/ark:/67531/metadc172521/thumbnail/"/></a></p><p>Instead of solving the nonlinear differential equation which governs the compressible flow, an approximate method of solution by means of the variational method is used. The general problem of steady irrotational flow past an arbitrary body is formulated. Two examples were carried out, namely, the flow past a circular cylinder and the flow past a thin curved surface. The variational method yields results of velocity and pressure distributions which compare excellently with those found by existing methods. These results indicate that the variational method will yield good approximate solution for flow past both thick and thin bodies at both high and low Mach numbers.</p>Bending Tests of Metal Monocoque Fuselage Construction2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc172433/<p><a href="/ark:/67531/metadc172433/"><img alt="Bending Tests of Metal Monocoque Fuselage Construction" title="Bending Tests of Metal Monocoque Fuselage Construction" src="/ark:/67531/metadc172433/thumbnail/"/></a></p><p>Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.</p>Performance of B. M. W. 185-Horsepower Airplane Engine2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc172405/<p><a href="/ark:/67531/metadc172405/"><img alt="Performance of B. M. W. 185-Horsepower Airplane Engine" title="Performance of B. M. W. 185-Horsepower Airplane Engine" src="/ark:/67531/metadc172405/thumbnail/"/></a></p><p>None</p>Aerodynamic Investigation of a Cup Anemometer2014-09-25T20:32:43-05:00http://digital.library.unt.edu/ark:/67531/metadc172432/<p><a href="/ark:/67531/metadc172432/"><img alt="Aerodynamic Investigation of a Cup Anemometer" title="Aerodynamic Investigation of a Cup Anemometer" src="/ark:/67531/metadc172432/thumbnail/"/></a></p><p>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.</p>