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Wind tunnel force tests in wing systems through large angles of attack

Description: Force tests on a systematic series of wing systems over a range of angle of attack from minus forty-five degrees to plus ninety degrees are covered in this report. The investigation was made on monoplane and biplane wing models to determine the effects of variations of tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweepback, and airfoil profile.
Date: August 1928
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel of Zeppelin Airship Company

Description: This report discusses the general considerations for the design of aerodynamic laboratories. The dimensions, construction, and components of the wind tunnel are given special attention.
Date: April 1923
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Pressure Distribution Tests on a Series of Biplane Wing Models Part I: Effects of Changes in Stagger and Gap

Description: This report is on the changes in forces on each wing of a biplane cellule when either the stagger or the gap is varied. Since each test was carried up to a 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning as well as in the structural design of biplane wings.
Date: July 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel pressure distribution tests on a series of biplane wing models Part II: effects of changes in decalage, dihedral, sweepback and overhang

Description: This preliminary report furnishes information on the changes in the forces on each wing of a biplane cellule when the decalage, dihedral, sweepback and overhang are separately varied. The data were obtained from pressure distribution tests made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. Since each test was carried up to 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning and in the structural design of biplane wi… more
Date: October 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind tunnel pressure distribution tests on a series of biplane wing models Part III: effects of charges in various combinations of stagger, gap, sweepback, and decalage

Description: A concept for the calculation of the vortex lift of sharp-edge delta wings is presented and compared with experimental data. The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading edge. This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent predi… more
Date: December 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Pressure Distribution Tests on an Airfoil With Trailing Edge Flap

Description: "This report deals with pressure distribution tests on an airfoil with a conventional trailing edge flap. These tests were conducted in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Maximum chord loadings were obtained with the flap displaced downward and with the airfoil at large angles of attack. Greater changes were produced in the normal force and in the center of pressure travel by up-flap than by an equal down-flap displacement" (p. 1).
Date: October 1929
Creator: Wenzinger, Carl J. & Loeser, Oscar, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Standardization Disk Drag

Description: Note presenting the resistances of a series of three similar disks placed normal to the wind as determined in the atmospheric wind tunnel. The curves of drag coefficient plotted against Reynolds number for this tunnel show discrepancies between overlapping values which are to be attributed to the presence of the tunnel walls.
Date: December 1926
Creator: Knight, Montgomery
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Studies in Aerodynamic Phenomena at High Speed

Description: A great amount of research and experimental work has been done and fair success obtained in an effort to place airplane and propeller design upon an empirical basis. However, one can not fail to be impressed by the apparent lack of data available toward establishing flow phenomena upon a rational basis, such that they may be interpreted in terms of the laws of physics. With this end in view it was the object of the authors to design a wind tunnel differing from the usual type especially in rega… more
Date: 1921
Creator: Caldwell, F. W. & Fales, E. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests of Correction Formula for Wings of Large Span

Description: The theory (wing experiments in an artificial air stream are subject to error, due to the fact that the wing is not situated in an unlimited body of air) by means of which the given drag correction was obtained, was based on various assumptions (e.g., elliptical distribution of lift) which do not always hold true. For this reason it was desirable to test the equation for the additional drag in regard to its reliability and range of application.
Date: May 1924
Creator: Wieselsberger, C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests of Five Strut Sections in Yaw

Description: In the first series of wind tunnel tests, the drag and cross wing force of all the struts were measured at a wind speed of 30 mph and at angles of yaw from 0 degrees to 20 degrees. To determine the magnitude of the VL effect, each strut was tested at zero yaw and at a series of speeds ranging from 15 to 38 mph. Although designed as fairings for cables, part of these sections gave such high crosswind forces that they seemed to have possibilities as airfoils.
Date: November 1923
Creator: Warner, Edward P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests of Fuselages and Windshields

Description: "The tests described herein were made in 1918, in the old four-foot wind tunnel at the Massachusetts Institute of Technology and at the request of the Engineering Division of the U.S. Army Air Service. The results were given circulation only in official circles at that time. The interest of the work appears sufficient to justify its wider distribution even at this very late date" (p. 1).
Date: September 1925
Creator: Warner, Edward P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests on Airfoil Boundary Control Using a Backward Opening Slot (1929)

Description: "This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil equipped with a backward opening slot. Various slot locations, widths of opening, and pressures, were used. The tests were conducted in the Five-Foot Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory" (p. 1).
Date: October 1929
Creator: Knight, Montgomery & Bamber, Millard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests on an Airfoil Equipped With a Split Flap and a Slot

Description: "The investigation described in this report is concerned with the changes in the aerodynamic characteristics of an airfoil which are produced by a gauze-covered suction slot, located near the leading edge, and connected by an air passage to a split flap at the trailing edge. The tests were conducted at the Langley Memorial Aeronautical Laboratory. At the larger values of lift coefficient where the action of the slot might be expected to be most effective, the pressure differences were such that… more
Date: October 1929
Creator: Bamber, Millard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests on Autorotation and The "Flat Spin"

Description: "This report deals with the autorotational characteristics of certain differing wing systems as determined from wind tunnel tests made at the Langley Memorial Aeronautical Laboratory. The investigation was confined to autorotation about a fixed axis in the plane of symmetry and parallel to the wind direction. Analysis of the tests leads to the following conclusions: autorotation below 30 degree angle of attack is governed chiefly by wing profile, and above that angle by wing arrangement" (p. 34… more
Date: 1928
Creator: Knight, Montgomery
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Vane With Various Applications

Description: A design for a wind vane is presented and various applications are discussed. The equations that can be used to calculate effects on the aircraft using the vane and control assistance that can be provided using the wind vane are provided.
Date: September 1922
Creator: Constantin, M. Louis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Windmills in the Light of Modern Research

Description: The chief contribution of modern research in the field of windmills is a better understanding of the phenomena and of the available means for the accomplishment of certain results, but also of the natural limits to their productive capacity.
Date: August 1928
Creator: Betz, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing Resistance Near the Ground

Description: In the present treatise, a convenient method will be indicated, which makes it possible to determine the polar curve of an airplane at short distances from the ground by a simple short calculation, when the polar curve is known for flight in unlimited space.
Date: April 1922
Creator: Wieselsberger, C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing Spar Stress Charts and Wing Truss Proportions

Description: "In order to simplify the calculation of beams continuous over three supports, a series of charts have been calculated giving the bending moments at all the critical points and the reactions at all supports for such members. Using these charts as a basis, calculations of equivalent bending moments, representing the total stresses acting in two bay-wing trusses of proportions varying over a wide range, have been determined, both with and without allowance for column effect. This leads finally to… more
Date: 1926
Creator: Warner, Edward P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Wing With a Pointed Tip

Description: In airplane construction generally one finds an almost exclusive use of wing tips that are practically square end but occasionally those with large rounded tips. For use as a cantilever wing, however, a wing with pointed tips may contain valuable aerodynamic advantages.
Date: October 1922
Creator: v. Prondzynski, Stephan
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wings With Nozzle-Shaped Slots

Description: Even before the publication of the results of the Gottingen experiments on the removal of the boundary layer by suction, experiments with nozzle-slotted wings were begun. A report of those experiments will be given here. Taken collectively, the experiments show that, as regards increasing the lift values, the effect of the air flowing from the nozzle-shaped slots is similar to the effect produced in the case of ordinary slotted wings. The high lift values are attained, however, at the smaller a… more
Date: July 1929
Creator: Katzmayr, Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wire Suspensions in Wind Tunnel Experiments

Description: The elimination of the rigid supports for models and their replacement by wires constitute a great improvement by rendering negligible the interactions of support. There are disadvantages to wire, namely, the aerodynamic resistance is very large and their use is rather difficult because the whole suspension lacks rigidity and easily becomes distorted. We will here investigate the nature of these distortions, evaluate the errors they entail and describe the methods for taking account of or avoid… more
Date: December 1925
Creator: Kerneis, Jean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wood Versus Metal in Airplane Construction

Description: The aim of this article is to present, in broad outline, a scientific method for solving the problem, "Wood or Metal." It will be shown that structural methods have by no means reached their final perfection. The strength of the different materials is discussed as well as different construction methods.
Date: June 1923
Creator: Seehase, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wood Versus Metal in Airplane Construction

Description: The aim of this article is to present, in broad outline, a scientific method for solving the problem, "Wood or Metal." It will be shown that structural methods have by no means reached their final perfection. The strength of the different materials is discussed as well as different construction methods.
Date: June 1923
Creator: Seehase, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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