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in publisher: "United States. National Advisory Committee for Aeronautics."  
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Performance of B. M. W. 185-horsepower airplane engine

Description: Report discusses the results of testing on a B.M.W. engine in an altitude chamber where temperature and pressure can be controlled to simulate flight at various altitudes. Results for various engine speeds, altitudes, and propeller speeds are provided.
Date: April 13, 1922
Creator: Sparrow, Stanwood Willston
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Considerations of the Total Drag of Supersonic Airfoil Sections

Description: The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under … more
Date: July 1947
Creator: Ivey, H. Reese & Klunker, E. Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid

Description: The methods of NACA TN No. 995 have been slightly modified and extended in include flows with circulation by considering the alteration of the singularities of the incompressible solution due to the presence of the hypergeometric functions in the analytic continuation of the solution. It was found that for finite Mach numbers the only case in which the nature of the singularity can remain unchanged is for a ratio of specific heats equal to -1. From a study of two particular flows it seems that … more
Date: June 1948
Creator: Kuo, Yung-Huai
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tables and charts of flow parameters across oblique shocks

Description: 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.
Date: August 1948
Creator: Neice, Mary M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Two-dimensional subsonic compressible flows past arbitrary bodies by the variational method

Description: 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 existi… more
Date: March 1951
Creator: Wang, Chi-Teh
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Three-Dimensional Instability of Laminar Boundary Layers on Concave Walls

Description: Memorandum presenting a study of the stability of laminar boundary layer profiles on slightly curved walls relative to small disturbances, in the shape of vortices, whose axes are parallel to the principal direction of flow. The result in an eigenvalue problem by which, for a given undisturbed flow at a prescribed wall, the amplification or decay is computed for each Reynolds number and each vortex thickness.
Date: June 1954
Creator: Görtler, H.
Item Type: Refine your search to only Thesis or Dissertation
Partner: UNT Libraries Government Documents Department
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An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.
Date: April 21, 1954
Creator: Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section

Description: 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.
Date: June 1954
Creator: Grant, Frederick C. & Cooper, Morton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

Description: 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.
Date: March 9, 1951
Creator: Hubbartt, James E. & Schum, Eugene F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Oxygen-Nitrogen System at Temperatures From 2000° to 5000° Degrees K

Description: 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.
Date: July 1948
Creator: Huff, Vearl N. & Calvert, Clyde S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Design of Airplane-Engine Superchargers

Description: Report studying the "underlying principles for the computation and design of airplane engine superchargers" (p. 1). With the forms of superchargers and underlying principles of computation, delivery heads per stage of 7,000 to 8,500 meters (air column) at an effective efficiency, based on the adiabatic process, of 0.7 may be attained, the space and weight requirements being kept within reasonable limits.
Date: October 1937
Creator: von der Nüll, Werner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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