The application of basic data on planing surfaces to the design of flying-boat hulls

The application of basic data on planing surfaces to the design of flying-boat hulls

Date: January 1, 1940
Creator: Diehl, Walter S
Description: Basic lift data on planing surfaces have been analyzed and the data applied to the design of flying-boat hulls. It is shown that a balance between air and water forces requires that the beam of the planing area bear a relation to the wing area that is determined by the lift coefficient of the wing and by the angle of dead rise in the planing surface. It is also shown that the fore-and-aft extent of the required planing area depends on the angle of dead rise. Failure to provide sufficient length of planing area appears to be the main reason for the poor water performance sometimes obtained when a large angle of dead rise is used.
Contributing Partner: UNT Libraries Government Documents Department
Some approximate equations for the standard atmosphere

Some approximate equations for the standard atmosphere

Date: January 1, 1932
Creator: Diehl, Walter S
Description: This report contains the derivation of a series of simple approximate equations for density ratios and for the pressure ratio in the standard atmosphere. The accuracy of the various equations is discussed and the limits of applications are given. Several of these equations are in excellent agreement with the standard values.
Contributing Partner: UNT Libraries Government Documents Department
The estimation of maximum load capacity of seaplanes and flying boats

The estimation of maximum load capacity of seaplanes and flying boats

Date: January 1, 1934
Creator: Diehl, Walter S
Description: This reports presents a method of calculating time and gross load for take-off of seaplanes and flying boats.
Contributing Partner: UNT Libraries Government Documents Department
Relative loading on biplane wings

Relative loading on biplane wings

Date: January 1, 1934
Creator: Diehl, Walter S
Description: Recent improvements in stress analysis methods have made it necessary to revise and to extend the loading curves to cover all conditions of flight. This report is concerned with a study of existing biplane data by combining the experimental and theoretical data to derive a series of curves from which the lift curves of the individual wings of a biplane may be obtained.
Contributing Partner: UNT Libraries Government Documents Department
A new chart for estimating the absolute ceiling of an airplane

A new chart for estimating the absolute ceiling of an airplane

Date: January 1, 1932
Creator: Diehl, Walter S
Description: This report is concerned with the derivation of a chart for estimating the absolute ceiling of an airplane. This chart may be used in conjunction with the usual curves of power required and power available as an accurate substitute for extended calculation, or it may be used in the estimation of absolute ceiling when power curves are not available.
Contributing Partner: UNT Libraries Government Documents Department
Static thrust of airplane propellers

Static thrust of airplane propellers

Date: January 1, 1934
Creator: Diehl, Walter S
Description: Static thrust data from more than 100 airplane propeller tests are collected from various sources and combined in working charts, from which the static thrust coefficient may be readily determined. The available data cover practically all types of propellers and are in good agreement.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of take-off run

The calculation of take-off run

Date: January 1, 1934
Creator: Diehl, Walter S
Description: A comparatively simple method of calculating length of take-off run is developed from the assumption of a linear variation in net accelerating force with air speed and it is shown that the error involved is negligible.
Contributing Partner: UNT Libraries Government Documents Department
High-Speed Load Distribution of the Wing of a 3/16-Scale Model of the Douglas XSB2D-1 Airplane with Flaps Deflected

High-Speed Load Distribution of the Wing of a 3/16-Scale Model of the Douglas XSB2D-1 Airplane with Flaps Deflected

Date: February 5, 1947
Creator: Barnes, Robert H.
Description: The tests reported herein were made for the purpose of determining the high-speed load distribution on the wing of a 3/16 scale model of the Douglas XSB2D-1 airplane. Comparisons are made between the root bending moment and section torsional moment coefficients as obtained experimentally and derived analytically. The results show good correlation for the bending moment coefficients but considerable disagreement for the torsional moment coefficients, the measured moments being greater than the analytical moments. The effects of Mach number on both the bending moment and torsional moment coefficients were small.
Contributing Partner: UNT Libraries Government Documents Department
The mean aerodynamic chord and the aerodynamic center of a tapered wing

The mean aerodynamic chord and the aerodynamic center of a tapered wing

Date: January 1, 1942
Creator: Diehl, Walter S
Description: A preliminary study of pitching-moment data on tapered wings indicated that excellent agreement with test data was obtained by locating the quarter-chord point of the average chord on the average quarter-chord point of the semispan. The study was therefore extended to include most of the available data on tapered-wing models tested by the NACA.
Contributing Partner: UNT Libraries Government Documents Department
Bending moments, envelope, and cable stresses in non-rigid airships

Bending moments, envelope, and cable stresses in non-rigid airships

Date: January 1, 1923
Creator: Burgess, C P
Description: This report describes the theory of calculating the principal stresses in the envelope of a nonrigid airship used by the Bureau of Aeronautics, United States Navy. The principal stresses are due to the gas pressure and the unequal distribution of weight and buoyancy, and the concentrated loads from the car suspension cables. The second part of the report deals with the variations of tensions in the car suspension cables of any type of airship, with special reference to the rigid type, due to the propeller thrust or the inclination of the airship longitudinally.
Contributing Partner: UNT Libraries Government Documents Department
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