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The "Comte A.C. 3" Military Airplane (Swiss) : A High-Wing Semicantilever Monoplane

Description: Circular presenting a description of the Comte A.C. 3, which is a high-wing monoplane with tow tandem 600 hp Hispano-Suiza engines mounted above the fuselage. Details of the design, fuel tanks, fuselage, pilot seating, engine, wings, safety factors, and flight qualities are provided.
Date: July 1930
Partner: UNT Libraries Government Documents Department
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The Vortex Theory and Its Significance in Aviation

Description: This report will present ideas closely related to the vortex conception and illustrate them in the simplest possible terms. In addition to these general considerations, this report will attempt to show the application of the vortex theory in connection with the wing theory.
Date: July 1930
Creator: Betz, A.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Variations in the Velocity of the Air Flow About a Wing Profile

Description: Memorandum presenting an investigation to determine the variations in the velocity of the air when it was obliged to flow about a wing profile. Special interest was paid to the determination of velocity as compared with that of the undisturbed flow and of the velocity drop in successive planes perpendicular to the flow direction at increasing distances from the wing profile.
Date: July 1930
Creator: Repenthin, Walter
Partner: UNT Libraries Government Documents Department
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The Caproni "90 P.B." Military Airplane (Italian): A Giant Biplane of 6000 Horsepower

Description: Circular presenting a description of the Caproni 90 P.B., which is the largest airplane in existence at the time of the report. Details of the weight, construction, wings, controls, fuselage, tail, landing gear, flying qualities, and photographs are provided.
Date: July 1930
Partner: UNT Libraries Government Documents Department
open access

Impact Tests on Rubber Compression Springs for Airplane Landing Gears

Description: The present report gives the results of tests which were made for the purpose of solving the problem of whether diagrams obtained from pressure tests could be conclusive for the determination of the safe impact coefficients. It is first established that the rubber rings adhere firmly to the compression surfaces during deformation. Suggestions are thus obtained for a constructive simplification of the rubber rings. The hysteresis phenomenon is ascribed to external and internal friction forces. A… more
Date: July 1930
Creator: Hohenemser, K.
Partner: UNT Libraries Government Documents Department
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Span load distribution on two monoplanes wing models as affected by twist and sweepback

Description: The results presented in this note show the effect of twist and sweepback on the span load distribution over two monoplane wing models. The tests were made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The data are taken from the results of an investigation dealing primarily with lateral stability. As presented, they are suitable as an aid in the structural design of certain monoplane wings.
Date: July 1930
Creator: Knight, Montgomery & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department
open access

The Prevention of the Ice Hazard on Airplanes

Description: A review of various methods to prevent ice formation and adhesion to aircraft surfaces is given. It was concluded that the adhesion of ice to a surface may be reduced somewhat by the application of certain waxes and varnishes. In the experiments described, the varnishes containing calcium stearate and calcium oleate gave the best results. In wind tunnel tests, the adhesion was further reduced by the application of these waxes and varnishes to a thin, heat insulating layer of rubber.
Date: July 1930
Creator: Geer, William C. & Scott, Merit
Partner: UNT Libraries Government Documents Department
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Calculation of Pressure Distribution on Airship Hulls

Description: These calculations were based on the shape of the ZR III, with the following simplifications: cars, fins, and rudders removed; all cross sections replaced by equivalent circular cross sections. Under these assumptions the pressure distribution was calculated for the following cases: symmetrical case, or flow parallel to the axis; unsymmetrical case, or flow at an angle to the axis. In both cases the simple potential flow first forms the basis for the determination of the pressure distribution.
Date: July 1930
Creator: Von Karman, Theodor
Partner: UNT Libraries Government Documents Department
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Air forces and air-force moments at large angles of attack and how they are affected by the shape of the wing

Description: From Summary: "The present report is, in the first place, a compilation of the test results now available from wing tests up to angles of attack 90^o. Reports are also given of tests with monoplane and auxiliary wings in the Gottingen wind tunnel for the purpose of plotting a steadily rising curve of the normal force as a foundation of the angle of attack."
Date: July 1930
Creator: Fuchs, Richard & Schmidt, Wilhelm
Partner: UNT Libraries Government Documents Department
open access

A new chart for estimating the absolute ceiling of an airplane

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.
Date: July 1930
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department
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