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The 5- by 7-meter wind tunnel of the DVL

Description: The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
Date: March 1936
Creator: Kramer, M.
Item Type: Refine your search to only Report
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Accurate Calculation of Multispar Cantilever and Semicantilever Wings With Parallel Webs Under Direct and Indirect Loading

Description: In the present report the computation is actually carried through for the case of parallel spars of equal resistance in bending without direct loading, including plotting of the influence lines; for other cases the method of calculation is explained. The development of large size airplanes can be speeded up by accurate methods of calculation such as this.
Date: March 1932
Creator: Sänger, Eugen
Item Type: Refine your search to only Report
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The Aerodynamic Analysis of the Gyroplane Rotating-Wing System

Description: "An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters" (p. 1).
Date: March 1934
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
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The Aerodynamic Effect of a Retractable Landing Gear

Description: "Tests were conducted in the N.A.C.A. full scale wind tunnel at the request of the Army Air Corps to determine the effect of retractable landing gear openings in the bottom surface of a wing upon the characteristics of a Lockheed Altair airplane. The tests were extended to include the determination of the lift and drag characteristics throughout the angle-of-attack range with the landing gear both retracted and extended. Covering the wheel openings in the wing with sheet metal when the wheels w… more
Date: March 1933
Creator: DeFrance, Smith J.
Item Type: Refine your search to only Report
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Aerodynamic Rolling and Yawing Moments Produced by Floating Wing-Tip Ailerons, as Measured by Spinning Balance

Description: From Summary: "The investigation described in this report was made to determine the effectiveness of floating wing-tip ailerons as an airplane control in the spin. In these tests the ailerons, not being balanced, were set parallel to the axis of rotation, which is probably very nearly the attitude that balanced floating ailerons would assume in a spin. Rolling - and yawing moment coefficients are given as measured for the model with and without the ailerons, and computed values are given for th… more
Date: March 1934
Creator: Bamber, Millard J.
Item Type: Refine your search to only Report
open access

Air flow in the boundary layer near a plate

Description: From Summary: "The published data on the distribution of speed near a thin flat plate with sharp leading edge placed parallel to the flow (skin friction plate) are reviewed and the results of some additional measurements are described. The purpose of the experiments was to study the basic phenomena of boundary-layer flow under simple conditions."
Date: March 1936
Creator: Dryden, Hugh L.
Item Type: Refine your search to only Report
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Alternating-current equipment for the measurement of fluctuations of air speed in turbulent flow

Description: From Summary: "Recent electrical and mechanical improvements have been made in the equipment developed at the National Bureau of Standards for measurement of fluctuations of air speed in turbulent flow. Data useful in the design of similar equipment are presented. The design of rectified alternating-current power supplies for such apparatus is treated briefly, and the effect of the power supplies on the performance of the equipment is discussed."
Date: March 1937
Creator: Mock, W. C., Jr.
Item Type: Refine your search to only Report
open access

Applied Potential Corrosion of Aluminum and 18-8 Stainless Steel Alloys

Description: Introduction: In anticipation of the design of equipment for heat transfer tests, a series of short exposure corrosion tests was initiated in an effort to determine the order of magnitude of the corrosion involved. Information was required on the effect on corrosion rates of applying a potential between two concentric tubes, the annulus between them containing condensate water.
Date: March 13, 1930
Creator: Sanborn, Kenneth L.
Item Type: Refine your search to only Report
open access

Bending Tests of Circular Cylinders of Corrugated Aluminum-Alloy Sheet

Description: "Bending tests were made of two circular cylinders of corrugated aluminum-alloy sheet. In each test failure occurred by bending of the corrugations in a plane normal to the skin. It was found, after analysis of the effect of short end bays, that the computed stress on the extreme fiber of a corrugated cylinder is in excess of that for a flat panel of the same basic pattern and panel length tested as a pin-ended column. It is concluded that this increased strength was due to the effects of curva… more
Date: March 1937
Creator: Niles, Alfred S.; Buckwalter, John C. & Reed, Warren D.
Item Type: Refine your search to only Report
open access

The Boundary Layer as a Means of Controlling the Flow of Liquids and Gases

Description: According to one of the main propositions of the boundary layer theory the scarcely noticeable boundary layer may, under certain conditions, have a decisive influence on the form of the external flow by causing it to separate from the wing surface. These phenomena are known to be caused by a kind of stagnation of the boundary layer at the point of separation. The present report deals with similar phenomena. It is important to note that usually the cause (external interference) directly affects … more
Date: March 1930
Creator: Schrenk, Oskar
Item Type: Refine your search to only Report
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The C.A.M.S. 80 Amphibian (French): An Observation Monoplane

Description: Circular presenting a description of the C.A.M.S. 80, which is a shipboard or observation patrol, light-bombing, long-range amphibian. Details of the hull, landing gear, wing, tail surfaces, power plant, front cockpit, pilot's compartment, photographer's compartment, radio cabinet, rear gunner's cockpit, stern compartment, and flying qualities are provided.
Date: March 1932
Item Type: Refine your search to only Report
open access

Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil

Description: Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are pres… more
Date: March 25, 1936
Creator: Pinkerton, Robert M.
Item Type: Refine your search to only Report
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Calculations of the Effect of Wing Twist on the Air Forces Acting on a Monoplane Wing

Description: "A method is presented for calculating the aerodynamic forces on a moncylane wing, taking into account the elastic twisting of the wing due to these forces. The lift distribution along the span is calculated by the formulas of Amstutz as a function of the geometrical characteristics of the wing and of the twist at stations 60 and 90 percent of the semispan. The twist for a given lift distribution is calculated by means of influence lines" (p. 1).
Date: March 1935
Creator: Dätwyler, G.
Item Type: Refine your search to only Report
open access

Characteristics of the NACA 23012 airfoil from tests in the full-scale and variable-density tunnels

Description: "This report gives the results of tests in the NACA full-scale and variable-density tunnels of a new wing section, the NACA 23012, which is one of the more promising of an extended series of related airfoils recently developed. The tests were made at several values of the Reynolds number between 1,000,000 and 8,000,000. The new airfoil develops a reasonably high maximum lift and a low profile drag, which results in an unusually high value of the speed-range index. In addition, the pitching-mome… more
Date: March 1, 1935
Creator: Jacobs, Eastman N. & Clay, William C.
Item Type: Refine your search to only Report
open access

Combustion-engine temperatures by the sodium line-reversal method

Description: The sodium line-reversal method has been used in some preliminary measurements of flame temperature. Improvements in the method involving a photographic recorder and a means of correcting for the dirtiness of the windows are described. The temperatures so obtained are compared with those calculated from pressure diagrams.
Date: March 1936
Creator: Brevoort, Maurice J.
Item Type: Refine your search to only Report
open access

A Comparison of Corrosion-Resistant Steel (18 Percent Chromium - 8 Percent Nickel) and Aluminum Alloy (24st)

Description: "In the selection of materials for aircraft application, it is not enough to make the selection on a strength-weight basis alone. A strength-weight comparison is significant but other factors must be considered, for while a material with a high ratio of strength to weight may be perfectly satisfactory for one use, it may be totally unfitted for another. It is essential, among other things, that the probable nature, magnitude, and direction of the principal stresses be given special consideratio… more
Date: March 1936
Creator: Sullivan, J. E.
Item Type: Refine your search to only Report
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