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Aerodynamic Characteristics of Airfoils 6: Continuation of Reports Nos. 93, 124, 182, 244, and 286

Description: "This collection of data on airfoils has been made from the published reports of a number of the leading aerodynamic laboratories of this country and Europe. The information which was originally expressed according to the different customs of the several laboratories is here presented in a uniform series of charts and tables suitable for use of designing engineers and for purposes of general reference. The authority for the results here presented is given as the name of the laboratory at which … more
Date: 1930~
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests on a Series of Wing Models Through a Large Angle of Attack Range Part 1: Force Tests

Description: "This investigation covers force tests through a large range of angle of attack on a series of monoplane and biplane wing models. The tests were conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics. The models were arranged in such a manner as to make possible a determination of the effects of variations in tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweep back, and airfoil profile. The arrangements represented most of the types of wing … more
Date: 1930
Creator: Knight, Montgomery & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Twenty-Four Airfoils at High Speeds

Description: "If a propeller is mounted directly on the of a modern high-speed airplane engine, the outer airfoil sections of the propeller travel at speeds approaching the speed of sound. It is possible by the use of gearing and a somewhat larger propeller to reduce the speed of the propeller sections, but only at the expense of additional weight and some frictional loss of power. This report presents the results of this work" (p. 327).
Date: 1930~
Creator: Briggs, L. J. & Dryden, H. L.
Partner: UNT Libraries Government Documents Department
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Fuel Vapor Pressures and the Relation of Vapor Pressure to the Preparation of Fuel for Combustion in Fuel Injection Engines

Description: "This investigation on the vapor pressure of fuels was conducted in connection with the general research on combustion in fuel injection engines. The purpose of the investigation was to study the effects of high temperatures such as exist during the first stages of injection on the vapor pressures of several fuels and certain fuel mixtures, and the relation of these vapor pressures to the preparation of the fuel for combustion in high-speed fuel injection engines" (p. 385).
Date: 1930
Creator: Joachim, William F. & Rothrock, A. M.
Partner: UNT Libraries Government Documents Department
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Flight tests on U.S.S. Los Angeles. Part 2: stress and strength determination

Description: From Summary: "The tests described in this report furnished data on the actual aerodynamic forces, and the resulting stresses and bending moments in the hull of the U. S. S. "Los Angeles" during as severe still-air maneuvers as the airship would normally be subjected to, and in straight flight during as rough air as is likely to occur in service, short of squall or storm conditions. The maximum stresses were found to be within the limits provided for in accepted practice in airship design. Norm… more
Date: January 1930
Creator: Burgess, C. P.
Partner: UNT Libraries Government Documents Department
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Tests of Five Metal Model Propellers With Various Pitch Distributions in a Free Wind Stream and in Combination With Model VE-7 Fuselage

Description: "This report describes the tests of five adjustable blade metal model propellers both in a free wind stream and in combination with a model fuselage with stub wings. The propellers are of the same form and cross section but have variations in radial distributions of pitch. By making a survey of the radial distribution of air velocity through the propeller plane of the model fuselage it was found that this velocity varies from zero at the hub center to approximately free stream velocity at the b… more
Date: 1930
Creator: Lesley, E. P. & Reid, Elliott G.
Partner: UNT Libraries Government Documents Department
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Collection of wind-tunnel data on commonly used wing sections

Description: This report groups in a uniform manner the aerodynamic properties of commonly used wing sections as determined from tests in various wind tunnels. The data have been collected from reports of a number of laboratories. Where necessary, transformation has been made to the absolute system of coefficients and tunnel wall interference corrections have been applied. Tables and graphs present the data in the various forms useful to the engineer in the selection of a wing section.
Date: January 1930
Creator: Louden, F. A.
Partner: UNT Libraries Government Documents Department
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The Torsion of Members Having Sections Common in Aircraft Construction

Description: "Within recent years a great variety of approximate torsion formulas and drafting-room processes have been advocated. In some of these, especially where mathematical considerations are involved, the results are extremely complex and are not generally intelligible to engineers. The principal object of this investigation was to determine by experiment and theoretical investigation how accurate the more common of these formulas are and on what assumptions they are founded and, if none of the propo… more
Date: 1930
Creator: Trayer, George W. & March, H. W.
Partner: UNT Libraries Government Documents Department
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Rolling Moments Due to Rolling and Yaw for Four Wing Models in Rotation

Description: "This report presents the results of a series of autorotation and torque tests on four different rotating wing systems at various rates of roll and at several angles of yaw. The investigation covered an angle of attack range up to 90 degrees and angles of yaw of 0 degree, 5 degrees, 10 degrees, and 20 degrees. The tests were made in a 5-foot, closed-throat atmospheric wind tunnel. The object of the tests was primarily to determine the effects of various angles of yaw on the rolling moments of t… more
Date: August 19, 1930
Creator: Knight, Montgomery & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department
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Pressure distribution over the fuselage of a PW-9 pursuit airplane in flight

Description: "This report presents the results obtained from pressure distribution tests on the fuselage of a PW-9 pursuit airplane in a number of conditions of flight. The investigation was made to determine the contribution of the fuselage to the total lift in conditions considered critical for the wing structure, and also to determine whether the fuselage loads acting simultaneously with the maximum tail loads were of such a character as to be of concern with respect to the structural design of other par… more
Date: August 1, 1930
Creator: Rhode, Richard V. & Lundquist, Eugene E.
Partner: UNT Libraries Government Documents Department
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Static, Drop, and Flight Tests on Musselman Type Airwheels

Description: The purpose of this investigation was to obtain quantitative information on the shock-reducing and energy-dissipating qualities of a set of 30 by 13-6 Musselman type airwheels. The investigation consisted of static, drop, and flight tests. The static tests were made with inflation pressures of approximately 0, 5, 10, 15, 20, and 25 pounds per square inch and loadings up to 9,600 pounds.
Date: October 8, 1930
Creator: Peck, William C. & Beard, Albert P.
Partner: UNT Libraries Government Documents Department
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Elastic Instability of Members Having Sections Common in Aircraft Construction

Description: "Two fundamental problems of elastic stability are discussed in this report. In part one formulas are given for calculating the critical stress at which a thin, outstanding flange of a compression member will either wrinkle into several waves or form into a single half wave and twist the member about its longitudinal axis. In part two the lateral buckling of beams is discussed" (p. 373).
Date: October 15, 1930
Creator: Trayer, George W. & March, H. W.
Partner: UNT Libraries Government Documents Department
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Maneuverability investigation of an F6C-4 fighting airplane

Description: "In order to compare the relative maneuverability of two fighting airplanes and to accumulate additional data to assist in establishing a satisfactory criterion for the maneuverability of any airplane, the National Advisory Committee for Aeronautics has conducted maneuverability investigations on the F6C-3 (water-cooled engine) and the F6C-4 (air-cooled engine) airplanes. The investigation made on the F6C-3 airplane was reported in NACA-TR-369. This report contains the results of the investigat… more
Date: December 12, 1930
Creator: Dearborn, C. H. & Kirschbaum, H. W.
Partner: UNT Libraries Government Documents Department
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Joint report on standardization tests on N.P.L. R.A.F 15 airfoil model

Description: From Summary: "This report contains the wind-tunnel test data obtained in the United States on a 36 by 6 inch R.A.F. 15 airfoil model prepared by the British Aeronautical Research Committee for International Trials. Tests were made in cooperation with the National Advisory Committee for Aeronautics at the Bureau of Standards, Langley Memorial Aeronautical Laboratory, Massachusetts Institute of Technology, and McCook field. In addition to brief descriptions of the various wind tunnels and method… more
Date: 1930
Creator: Diehl, Walter S.
Partner: UNT Libraries Government Documents Department
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Petroleum Refinery Statistics: 1928

Description: Report discussing statistics relating to the petroleum refinery industry in 1928.
Date: 1930
Creator: Hopkins, C. R.
Partner: UNT Libraries Government Documents Department
open access

The 1929 Rhon soaring-flight contest

Description: The limitation of the 1929 contest to performance gliders necessitated the establishment of a formula which would make it possible to distinguish between performance gliders and school and training gliders. The sinking speed was therefore adopted as the basis for such a distinction, and the requirement was made that the sinking speed of a performance glider should not exceed 0.8 m/s. The rest of the report details the different entries with regard to design and performance.
Date: April 1930
Creator: Lippisch, Alexander
Partner: UNT Libraries Government Documents Department
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