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Aero dopes and varnishes

Description: Before proceeding to discuss the preparation of dope solutions, it will be necessary to consider some of the essential properties which should be possessed of a dope film, deposited in and on the surface of an aero fabric. The first is that it should tighten the material and second it should withstand weathering.
Date: July 1927
Creator: Britton, H T S
Item Type: Report
Partner: UNT Libraries Government Documents Department

The aerodynamic characteristics of seven frequently used wing sections at full Reynolds number

Description: This report contains the aerodynamic properties of the wing sections U.S.A. 5, U.S.A. 27, U.S.A. 35 A, U.S.A. 35 B, Clark Y, R.A.F. 15, and Gottingen 387, as determined at various Reynolds numbers up to an approximately full scale value in the variable density wind tunnel of the National Advisory Committee for Aeronautics. It is shown that the characteristics of the wings investigated are affected greatly and in a somewhat erratic manner by variation of the Reynolds number. In general there is a small increase in maximum lift and an appreciable decrease in drag at all lifts.
Date: 1927~
Creator: Munk, Max M. & Miller, Elton W.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Aerodynamic laboratory at Cuatro Vientos

Description: This report presents a description of the design of the Cuatro Vientes wind tunnel.
Date: June 1927
Creator: Caracciolo, Moreno
Item Type: Report
Partner: UNT Libraries Government Documents Department

The air forces on a systematic series of biplane and triplane cellule models

Description: The air forces on a systematic series of biplane and triplane cellule models are the subject of this report. The test consist in the determination of the lift, drag, and moment of each individual airfoil in each cellule, mostly with the same wing section. The magnitude of the gap and of the stagger is systematically varied; not, however, the decalage, which is zero throughout the tests. Certain check tests with a second wing section make the tests more complete and conclusions more convincing. The results give evidence that the present army and navy specifications for the relative lifts of biplanes are good. They furnish material for improving such specifications for the relative lifts of triplanes. A larger number of factors can now be prescribed to take care of different cases.
Date: 1927
Creator: Munk, Max M.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Airfoil lift with changing angle of attack

Description: Tests have been made in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics to determine the effects of pitching oscillations upon the lift of an airfoil. It has been found that the lift of an airfoil, while pitching, is usually less than that which would exist at the same angle of attack in the stationary condition, although exceptions may occur when the lift is small or if the angle of attack is being rapidly reduced. It is also shown that the behavior of a pitching airfoil may be qualitatively explained on the basis of accepted aerodynamic theory.
Date: September 1, 1927
Creator: Reid, Elliott G
Item Type: Report
Partner: UNT Libraries Government Documents Department

Approximation method for determining the static stability of a monoplane glider

Description: The calculations in this paper afford an approximate solution of the static stability. A derivation of the formulas for moment coefficient of a wing, moment coefficient of elevator, and the total moment of the combined wing and elevator and the moment coefficient with reference to the center of gravity are provided.
Date: November 1, 1927
Creator: Lippisch, A
Item Type: Report
Partner: UNT Libraries Government Documents Department

Approximations for column effect in airplane wing spars

Description: The significance attaching to "column effect" in airplane wing spars has been increasingly realized with the passage of time, but exact computations of the corrections to bending moment curves resulting from the existence of end loads are frequently omitted because of the additional labor involved in an analysis by rigorously correct methods. The present report represents an attempt to provide for approximate column effect corrections that can be graphically or otherwise expressed so as to be applied with a minimum of labor. Curves are plotted giving approximate values of the correction factors for single and two bay trusses of varying proportions and with various relationships between axial and lateral loads. It is further shown from an analysis of those curves that rough but useful approximations can be obtained from Perry's formula for corrected bending moment, with the assumed distance between points of inflection arbitrarily modified in accordance with rules given in the report. The discussion of general rules of variation of bending stress with axial load is accompanied by a study of the best distribution of the points of support along a spar for various conditions of loading.
Date: January 1, 1927
Creator: Warner, Edward P. & Short, Mac
Item Type: Report
Partner: UNT Libraries Government Documents Department

The Boeing mail airplane

Description: The Boeing Mail Airplane is a biplane with cloth covered wings of wood and wire construction, a top speed of 130 MPH, and a fuel capacity of 100 gallons in two tanks.
Date: August 1, 1927
Item Type: Report
Partner: UNT Libraries Government Documents Department

Building a full-size glider

Description: The building and flying of a glider is possible for anyone who can use a few basic tools. This report presents some plans and techniques for building your own glider.
Date: September 1, 1927
Creator: Camm, F J
Item Type: Report
Partner: UNT Libraries Government Documents Department

Calculating thrust distribution and efficiency of air propellers

Description: I am now proposing a method for the preliminary approximate calculation of the thrust distribution and efficiency of air propellers under any operating conditions. Our task becomes the following, namely, to determine the speed relations and the forces developed on a section with a given direction and velocity of the air current, a problem which can be solved with the aid of the momentum theory.
Date: December 1, 1927
Creator: Bienen, Theodor
Item Type: Report
Partner: UNT Libraries Government Documents Department

Caproni airplane Ca 73 (commercial) and Ca 73 ter (military)

Description: The Caproni 73 is a biplane with medium thick wings, a rigid central section, and with each lateral extension forming a single cell and is powered by two 500 Isotta Fraschini "Asso" Engines.
Date: August 1, 1927
Item Type: Report
Partner: UNT Libraries Government Documents Department

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 hour, the seaplane trims by the stern and has a high resistance. Above these speeds the longitudinal control becomes increasingly effective until, with corresponding speeds of 56 to 46 miles per hour. It was further determined that an increase in the load caused little if any change in the water speed at which the maximum angle and resistance occurred, but that it did produce an increase in the maximum angle.
Date: January 1, 1927
Creator: Crowley, John W , Jr & Ronan, K M
Item Type: Report
Partner: UNT Libraries Government Documents Department

Climbing efficiency of aircraft

Description: The object of this report was to indicate that we frequently only make use of 50 percent of the maximum brake horsepower of the engine in taking off the ground, that this loss is not inevitable, and that the effort to get engines of low weight per horsepower by boosting revolutions is of very little use to bombers and commercial airplanes.
Date: June 1, 1927
Creator: Walker, C C
Item Type: Report
Partner: UNT Libraries Government Documents Department

Coal-Mine Fatalities in the United States, 1926

Description: Report compiled by the U.S. Bureau of Mines including statistics on fatalities in coal mines located in the United States as well as data regarding the various operations (e.g., number of miners employed and average production). The information is organized into tables for comparison and the text draws some overall conclusions in the summary.
Date: 1927
Creator: Adams, William W.
Item Type: Report
Partner: UNT Libraries Government Documents Department

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 1, 1927
Item Type: Report
Partner: UNT Libraries Government Documents Department

Comparison of American, British, and German Standards for Metal Fits

Description: Report issued by the Bureau of Standards discussing the comparison of American, British, and German metal fit standards. The comparisons between national standards of the three countries are presented and described. This report includes tables, and illustrations.
Date: 1927
Creator: Fullmer, Irvin H.
Item Type: Report
Partner: UNT Libraries Government Documents Department