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Air Force Tests of Sperry Messenger Model With Six Sets of Wings

Description: From Summary: "The purpose of this test was to compare six well-known airfoils, the R.A.F 15, U.S.A. 5, U.S.A. 27, U.S.A. 35-B, Clark Y, and Gottingen 387, fitted to the Sperry Messenger model, at full scale Reynolds number as obtained in the variable density wind tunnel of the National Advisory Committee for Aeronautics; and to determine the scale effect on the model equipped with all the details of the actual airplane. The results show a large decrease in minimum drag coefficient upon increas… more
Date: January 20, 1927
Creator: Shoemaker, James M.
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a twin-float seaplane during take-off

Description: This report presents the results of an investigation of the planing and get-away characteristics of three representative types of seaplanes, namely, single float, boat, and twin float. The experiments carried out on the single float and boat types have been reported on previously. This report covers the investigation conducted on the twin-float seaplane, the DT-2, and includes as an appendix, a brief summary of the results obtained on all three tests. At low-water speeds, 20 to 30 miles per hou… more
Date: January 1927
Creator: Crowley, John W., Jr. & Ronan, K. M.
Partner: UNT Libraries Government Documents Department
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Combat and bombing airplane, Amiot 120 B 3

Description: The Amiot 120 B 3 is designed as a French combat aircraft. It can accept a variety of engines, and is equipped with 2 machine guns as well as specialized bomb sights and other combat equipment.
Date: January 1927
Partner: UNT Libraries Government Documents Department
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Drag of Wings With End Plates

Description: "In this report a formula for calculating the induced drag of multiplanes with end plates is derived. The frictional drag of the end plates are used, is sufficiently large to increase the efficiency of the wing. Curves showing the reduction of drag for monoplanes and biplanes are constructed; the influence of gap-chord ratio, aspect ratio, and height of end plate are determined for typical cases. The method of obtaining the reduction of drag for a multiplane is described" (p. 253).
Date: January 20, 1927
Creator: Hemke, Paul E.
Partner: UNT Libraries Government Documents Department
open access

The effect of flight path inclination on airplane velocity

Description: This report was prepared at the request of the National Advisory Committee for Aeronautics in order to supply a systematic study of the relations between the flight velocity V and its horizontal component V subscript H, in power glides. Curves of V and V subscript H plotted against the inclination of the flight path 0 are given, together with curves which show the maximum values of V subscript H and the corresponding values of 0. Curves are also given showing the effect of small departures from… more
Date: January 1927
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department
open access

Factors in the design of centrifugal type injection valves for oil engines

Description: This research was undertaken in connection with a general study of the application of the fuel injection engine to aircraft. The purpose of the investigation was to determine the effect of four important factors in the design of a centrifugal type automatic injection valve on the penetration, general shape, and distribution of oil sprays. The general method employed was to record the development of single sprays by means of special high-speed photographic apparatus capable of taking 25 consecut… more
Date: January 27, 1927
Creator: Joachim, W. F. & Beardsley, E. G.
Partner: UNT Libraries Government Documents Department
open access

Method of correcting wind tunnel data for omitted parts of airplane models

Description: Wind tunnel models do not have complete similarity to the full scale airplane. Part of the dissimilarity is due to the difference between the stationary model in the artificial wind stream of the tunnel and the moving airplane in still air. There are a number of other reasons for departing from exact geometrical similitude. For reasons of accuracy and economy, all minor parts of the full scale airplane, such as struts, wires, fittings, control horns and other parts whose scale corrections are l… more
Date: January 1927
Creator: Smith, R. H.
Partner: UNT Libraries Government Documents Department
open access

Nieuport-Delage Pursuit Airplane 48 C. 1.: "Jockey" Type

Description: This is a light single-seat pursuit airplane with a tractor propeller actuated by a 12 cylinder V-type Hispano-Suiza engine giving 400 HP at 2000 R.P.M. This is a single winged aircraft capable of 273 km/h.
Date: January 1927
Partner: UNT Libraries Government Documents Department
open access

Precision of Wing Sections and Consequent Aerodynamic Effects

Description: Note presenting an investigation to determine the precision of wing sections of wood fabric construction used on a number of airplanes. All of the wing sections were found to deviate more or less from their respective prototypes. The aerodynamic effects resulting from consideration of thickness variation are then estimated from existing empirical information.
Date: January 1927
Creator: Rizzo, Frank
Partner: UNT Libraries Government Documents Department
open access

Stall-Proof Airplanes

Description: Report investigating some characteristics of aircraft stall, including the following: Is the danger of stalling necessarily inherent in the airplane in its present form and structure, or can it be diminished or eliminated by suitable means? Do we possess such means or devices and how must they operate?
Date: January 1927
Creator: Lachmann, G.
Partner: UNT Libraries Government Documents Department
open access

Testing a Windmill Airplane ("Autogiro")

Description: In order to clear up the matter ( In the Spanish report it was stated that the reference surface for the calculation of the coefficients c(sub a) and c(sub w) was the area of all four wings, instead of a single wing), the model of a windwill airplane was tested in the Gottingen wind tunnel.
Date: January 1927
Creator: Seiferth, R.
Partner: UNT Libraries Government Documents Department
open access

Tests on airplane fuselages, floats and hulls

Description: This report is a compilation of test data on airplane fuselages, nacelles, airship cars, seaplane floats, and seaplane hulls, prepared by the Bureau of Aeronautics, at the requests of the National Advisory Committee for Aeronautics. The discussion of the data includes the derivation of a scale correction curve to be used in obtaining the full scale drag. Composite curves of drag and L/D for floats and hulls are also given. (author).
Date: January 1927
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department
open access

Three methods of calculating range and endurance of airplanes

Description: This report develops new equations which give the range and endurance of airplanes with an accuracy equal to that obtained from a step-by-step integration of the flight. A method of obtaining equally satisfactory results from Brequet's equations is also given in detail. A third method of calculating range and endurance, derived by the writer for use in routine estimating in the Bureau of Aeronautics, is also given in full. The reports contains tables and curves arranged for convenient use and i… more
Date: January 1927
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department
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