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 Collection: National Advisory Committee for Aeronautics Collection
Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section

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

Date: June 1954
Creator: Grant, Fredrick C.
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.
Contributing Partner: UNT Libraries Government Documents Department
Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique

Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique

Date: February 1957
Creator: Felix, A. Richard
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades

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

Date: March 9, 1951
Creator: Hubbartt, James E.
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.
Contributing Partner: UNT Libraries Government Documents Department
Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K

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

Date: July 1948
Creator: Huff, Vearl N.
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.
Contributing Partner: UNT Libraries Government Documents Department
Tables and Charts of Flow Parameters Across Oblique Shocks

Tables and Charts of Flow Parameters Across Oblique Shocks

Date: August 1948
Creator: Neice, Mary M.
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.
Contributing Partner: UNT Libraries Government Documents Department
A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow

A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow

Date: 1951
Creator: Stalder, Jackson R.
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method

Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method

Date: March 1951
Creator: Wang, Chi-Teh
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 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.
Contributing Partner: UNT Libraries Government Documents Department
Bending Tests of Metal Monocoque Fuselage Construction

Bending Tests of Metal Monocoque Fuselage Construction

Date: November 1930
Creator: Mossman, Ralph W.
Description: Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Contributing Partner: UNT Libraries Government Documents Department
Performance of B. M. W. 185-Horsepower Airplane Engine

Performance of B. M. W. 185-Horsepower Airplane Engine

Date: April 13, 1922
Creator: Sparrow, Stanwood Willston
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Investigation of a Cup Anemometer

Aerodynamic Investigation of a Cup Anemometer

Date: July 1934
Creator: Hubbard, John D.
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
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