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  Partner: UNT Libraries Government Documents Department
 Language: English
 Collection: National Advisory Committee for Aeronautics Collection
 Collection: Technical Report Archive and Image Library
Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers

Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers

Date: April 1947
Creator: Dryden, Hugh L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Considerations of the Total Drag of Supersonic Airfoil Sections

Considerations of the Total Drag of Supersonic Airfoil Sections

Date: July 1947
Creator: Ivey, H. Reese & Klunker, E. Bernard
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 different conditions, the circular-arc airfoil may have a higher drag.
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
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
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
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
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. & Cooper, Morton
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
Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid

Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid

Date: June 1948
Creator: Kuo, Yung-Huai
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 the effect of geometry cannot be neglected, and the conventional "pressure-correction" formulas are not valid, even in the subsonic region if the body is thick, especially if there is a supersonic region in the flow.
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. & Calvert, Clyde S.
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
Aerodynamic Investigation of a Cup Anemometer

Aerodynamic Investigation of a Cup Anemometer

Date: July 1934
Creator: Hubbard, John D. & Brescoll, George P.
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
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. & Schum, Eugene F.
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
Bending Tests of Metal Monocoque Fuselage Construction

Bending Tests of Metal Monocoque Fuselage Construction

Date: November 1930
Creator: Mossman, Ralph W. & Robinson, Russell G.
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
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.; Godwin, Glen & Creager, Marcus O.
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
Morane-Saulnier 180 light airplane (French) : a single-seat training monoplane

Morane-Saulnier 180 light airplane (French) : a single-seat training monoplane

Date: March 1, 1929
Creator: unknown
Description: Equipped with a 40 HP Salmson engine, it is a single seat parasol type construction.
Contributing Partner: UNT Libraries Government Documents Department
Nieuport-Delage 640 (French) : commercial high-wing monoplane

Nieuport-Delage 640 (French) : commercial high-wing monoplane

Date: March 1, 1929
Creator: unknown
Description: The Nieuport Delage 640 is a single engine commercial high-wing monoplane of all wood construction, including the fuselage and tail. It's landing gear is hinged in two parts.
Contributing Partner: UNT Libraries Government Documents Department
Liore-Olivier airplane : type 12 night-bomber or type 20 commercial

Liore-Olivier airplane : type 12 night-bomber or type 20 commercial

Date: March 1, 1926
Creator: Serryer, J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Francois Villiers marine pursuit airplane

The Francois Villiers marine pursuit airplane

Date: April 1, 1927
Creator: Serryer, J
Description: A traditional biplane design allows this craft to function with the speed and maneuverability necessary to perform as a pursuit aircraft while also being able to land on water. It featured retractable landing gear for water landings. It was powered with a 450 HP. Lorraine-Dietrich engine.
Contributing Partner: UNT Libraries Government Documents Department
The Westland IV commercial monoplane (British)three "Cirrus III" engine

The Westland IV commercial monoplane (British)three "Cirrus III" engine

Date: April 1, 1929
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Short "Calcutta" : first British all-metal commercial seaplane

The Short "Calcutta" : first British all-metal commercial seaplane

Date: March 1, 1928
Creator: unknown
Description: The Calcutta is a large seaplane, with seating for 16 and a payload of 3,400 pounds.
Contributing Partner: UNT Libraries Government Documents Department
Bleriot-Spad 91 Airplane (French) : pursuit single-seater, type "Jockey"

Bleriot-Spad 91 Airplane (French) : pursuit single-seater, type "Jockey"

Date: May 1, 1928
Creator: SOCIETE BLERIOT-AERONAUTIQUE
Description: This aircraft has announced a speed of 270 km per hour at 4000 m. It is of all metal construction.
Contributing Partner: UNT Libraries Government Documents Department
Lockheed "Vega" airplane : a commercial cabin monoplane

Lockheed "Vega" airplane : a commercial cabin monoplane

Date: November 1, 1927
Creator: unknown
Description: The Vega is a high wing monoplane suitable for commercial purposes. It can seat 6 passengers or 100 cubic feet of cargo.
Contributing Partner: UNT Libraries Government Documents Department
The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

Date: August 1, 1927
Creator: unknown
Description: The Widgeon III is a parasol type monoplane. One of it's strongest features was the high degree of visibility available to the pilot.
Contributing Partner: UNT Libraries Government Documents Department
The Mureaux "Brunet 3C2" pursuit airplane

The Mureaux "Brunet 3C2" pursuit airplane

Date: May 1, 1927
Creator: Serryer, J
Description: Designed by Engineer Brunet, the 3C2 is an all metal monoplane with two engines and provision for six machine guns and 12 10 Kg. bombs.
Contributing Partner: UNT Libraries Government Documents Department
The Armstrong Whitworth "Starling" (British) : (single seat fighter)

The Armstrong Whitworth "Starling" (British) : (single seat fighter)

Date: September 1, 1928
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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