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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1924
 Collection: National Advisory Committee for Aeronautics Collection
Remarks on the Pressure Distribution over the Surface of an Ellipsoid, Moving Translationally Through a Perfect Fluid

Remarks on the Pressure Distribution over the Surface of an Ellipsoid, Moving Translationally Through a Perfect Fluid

Date: June 1, 1924
Creator: Munk, Max M
Description: This note, prepared for the National Advisory Committee for Aeronautics, contains a discussion of the pressure distribution over ellipsoids when in translatory motion through a perfect fluid. An easy and convenient way to determine the magnitude of the velocity and of the pressure at each point of the surface of an ellipsoid of rotation is described. The knowledge of such pressure distribution is of great practical value for the airship designer. The pressure distribution over the nose of an airship hull is known to be in such good agreement with the theoretical distribution as to permit basing the computation of the nose stiffening structure on the theoretical distribution of pressure.
Contributing Partner: UNT Libraries Government Documents Department
On the distribution of lift along the span of an airfoil with displaced ailerons

On the distribution of lift along the span of an airfoil with displaced ailerons

Date: June 1, 1924
Creator: Munk, Max M
Description: The effect of an aileron displacement on the distribution of the lift along the span is computed for an elliptic wing of aspect ratio 6 for three conditions. The lift distribution caused by the aileron displacement is uniform and extends normally beyond the inner end of the ailerons. Hence, the displacement of an aileron with constant chord length may bring about passing the stalling point of the adjacent wing sections, if these were near this point before. Hence, such ailerons can become ineffective at low speeds. Tapering the aileron towards the inside suggests itself as a remedy.
Contributing Partner: UNT Libraries Government Documents Department
Micarta propellers I : materials

Micarta propellers I : materials

Date: August 1, 1924
Creator: Caldwell, F W
Description: Here, values for tension, compression edgewise of laminations, and transverse flatwise of laminations are given for Micarta made with various kinds of sheet material. The corresponding values for white oak are given for comparison. It was found by destructive and service tests that Micarta made with a good grade of cotton duck will give satisfactory service with most designs. In propellers having detachable blades, it is desirable that the root of the blade be of a small cross section to decrease the weight of the metal hub. Here the use of the special fabric or wood veneer offers advantages due to greater tensile strength. These materials, especially the wood veneer, produce stiffer blades than duck. This is also a value in controllable and reversible pitch designs where it is desirable that the plan form of the blades be symmetrical.
Contributing Partner: UNT Libraries Government Documents Department
Structural weight of aircraft as affected by the system of design

Structural weight of aircraft as affected by the system of design

Date: November 1, 1924
Creator: Hall, Charles Ward
Description: Various details of design or arrangement of the parts of airplane structures are shown and discussed, the use of these devices having resulted in the production of structures of adequate strength, yet of a weight less than one-half of the usual construction.
Contributing Partner: UNT Libraries Government Documents Department
Micarta Propellers II : method of construction

Micarta Propellers II : method of construction

Date: August 1, 1924
Creator: Caldwell, F W
Description: The methods used in manufacturing Micarta propellers differ considerably from those employed with wood propellers on account of the hardness of the materials. The propellers must be formed accurately to size in a mold and afterwards balanced without the customary trimming of the material from the tips. Described here are the pressing and molding processes, filing, boring, balancing, and curing.
Contributing Partner: UNT Libraries Government Documents Department
The simplifying assumptions, reducing the strict application of classical hydrodynamics to practical aeronautical computations

The simplifying assumptions, reducing the strict application of classical hydrodynamics to practical aeronautical computations

Date: November 1, 1924
Creator: Munk, Max M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some tables of the factor of apparent additional mass

Some tables of the factor of apparent additional mass

Date: July 1, 1924
Creator: Munk, Max M
Description: This note, prepared for publication by the National Advisory Committee for Aeronautics, is a collection of the tables of the factor of apparent mass that have been published up to now. The theory of the motion of solids in a perfect fluid is of the greatest value for the study of most aerodynamic problems, and the additional apparent mass of an immersed solid is the most important characteristic for such theoretical numerical computations. It will therefore be helpful to have the most important values of the apparent mass - for some elementary cases - collected in a convenient form.
Contributing Partner: UNT Libraries Government Documents Department
Significance of the expression C(sub L)(exp 3)/C(sub D)(exp 2)

Significance of the expression C(sub L)(exp 3)/C(sub D)(exp 2)

Date: January 1, 1924
Creator: Von Sanden, H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airplanes in horizontal curvilinear flight

Airplanes in horizontal curvilinear flight

Date: January 1, 1924
Creator: Kann, Heinrich
Description: War airplanes require not only high speed and the ability to climb rapidly, but also the ability to transverse sharp curves quickly. Here, an attempt is made to give a simple method of calculating horizontal curvilinear flight. A method for determining the area of the aileron and rubber surfaces are also indicated. The discussion given here applies primarily to single and two-seater airplanes, although it can be extended to larger airplanes.
Contributing Partner: UNT Libraries Government Documents Department
The induction factor used for computing the rolling moment due to the ailerons

The induction factor used for computing the rolling moment due to the ailerons

Date: April 1, 1924
Creator: Munk, Max M
Description: In the following note, prepared for the National Advisory Committee for Aeronautics, this induction factor is determined from the result of a model test, and compared with a formula recently developed by the author. The two results are found to be in substantial agreement.
Contributing Partner: UNT Libraries Government Documents Department
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