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Tests on Duralumin Columns for Aircraft Construction

Description: The following paper is based on the results of tests, upon duralumin columns, contained in two theses presented to the Department of Civil and Sanitary Engineering of the Massachusetts Institute of Technology.
Date: November 1924
Creator: Lee, John G.
Partner: UNT Libraries Government Documents Department
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The Effect of Wind Tunnel Turbulence Upon the Forces Measured on Models

Description: These tests were undertaken to find the effect of turbulence in the air stream upon the lift and drag forces measured on models in the four-foot wind tunnel at the Massachusetts Institute of Technology. Maximum lifts and minimum drags were measured on Gottingen-387 and R.A.F.-15 airfoils, minimum drag on a streamlined strut, and the static pressure gradients for different conditions of turbulence were investigated. The results show that the scale of the turbulence (as defined in this report) ha… more
Date: May 1924
Creator: LePage, W. L. & Nichols, J. T.
Partner: UNT Libraries Government Documents Department
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Interference of Multiplane Wings Having Elliptical Lift Distribution

Description: In calculating the self-induction of a wing surface, elliptical lift distribution is assumed, while in calculating the mutual induction or interference of two wing surfaces, a uniform distribution of the lift along the wing has hitherto been assumed. Whether the results of these calculations are substantially altered by assuming an elliptical lift distribution (which is just as probable as uniform distribution) is examined here.
Date: February 1924
Creator: von Sanden, H.
Partner: UNT Libraries Government Documents Department
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Induced Drag of Multiplanes

Description: "The most important part of the resistance or drag of a wing system, the induced drag, can be calculated theoretically, when the distribution of lift on the individual wings is known. The calculation is based upon the assumption that the lift on the wings is distributed along the wing in proportion to the ordinates of a semi-ellipse. Formulas and numerical tables are given for calculating the drag. In this connection, the most favorable arrangements of biplanes and triplanes are discussed and t… more
Date: February 1924
Creator: Prandtl, L.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Effect of an Oscillating Airstream (Katzmayr Effect) on the Characteristics of Airfoils

Description: A series of experiments were conducted related to the action of an airstream oscillating vertically on supporting surfaces. The object of the experiments was to verify the very interesting results of Mr. Katzmayr, Director of the Vienna Aerodynamics Laboratory, and, if possible, to obtain more complete data on the effect of the amplitude and velocity of the oscillations of the airstream. The results obtained by Mr. Katzmayr are briefly summarized. The conduct of the numerous experiments to veri… more
Date: September 1924
Creator: Toussaint; Kerneis & Girault
Partner: UNT Libraries Government Documents Department
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Static stability of seaplane floats and hulls

Description: Values of lateral and longitudinal metacentric heights for various seaplanes were calculated by means of approximate formulae derived here. The data are given in tabular form. Upon plotting these metacentric heights against the corresponding gross weights, it appears that the metacentric height is approximately a straight line function of the gross weight.
Date: March 1924
Creator: Diehl, W. S.
Partner: UNT Libraries Government Documents Department
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Note on Vortices on Their Relation to the Lift of Airfoils

Description: "This note, prepared for the NACA, contains a discussion of the meaning of vortices, so often mentioned in connection with the creation of lift by wings. The action of wings can be more easily understood without the use of vortices" (p. 1).
Date: March 1924
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department
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A Short Method of Calculating Torsional Stresses in an Airplane Fuselage

Description: "This report deals with an investigation carried out in the Civil Engineering Laboratory of the University of California, to determine the accuracy of existing methods of computing the stresses in an airplane fuselage when subjected to torsion, and to derive a simple approximate formula for the rapid calculation of these stresses. The formula is derived by using the customary least work equation and considering each bay separately" (p. 1).
Date: September 1924
Creator: Younger, John E.
Partner: UNT Libraries Government Documents Department
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Testing Airplane Fabrics

Description: "The following considerations determine the strength of airplane fabrics: 1. maximum air forces acting on the surfaces (including local stresses); 2. tensions produced in the fabrics, in the directions of both warp and filling; 3. factor of safety required. The question of the permissible depression of the fabric as affecting the aerodynamic requirements in regard to the maintenance of shape of the section, the tenacity and extensibility of the layer of dope, its strength and its permeability t… more
Date: April 1924
Creator: Pröll, A.
Partner: UNT Libraries Government Documents Department
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A Study of Static Stability of Airships

Description: The first section deals with the theoretical side of statical stability of airships in general. The second section deals with preliminary tests of the model and experiments for the determination of effects due to change of tail area, aspect ratio, tail form, and tail thickness.
Date: September 1924
Creator: Rizzo, Frank
Partner: UNT Libraries Government Documents Department
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High Altitude Flying

Description: This note investigates the effect of high altitude or low atmospheric pressure upon the operation of an engine and the effect of the low pressure and lack of oxygen and of the very low temperatures upon the pilot and upon the performance of the airplane itself.
Date: May 1924
Creator: King, Paul B. & Carroll, Thomas
Partner: UNT Libraries Government Documents Department
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The Logarithmic Polar Curve - Its Theory and Application to the Predetermination of Airplane Performance

Description: "The logarithmic polar curve has for several years been used by the most prominent aerodynamical laboratories as well as by airplane manufacturers in Europe. To show more clearly the practical application of the polar curve, a series of examples are given with suggestions for solution. After a discussion of the theory and the practical application of the polar curve, the following problems are discussed: climbing flight, speed at various altitudes, and the characteristics of two seater observat… more
Date: October 1924
Creator: Cronstedt, Val
Partner: UNT Libraries Government Documents Department
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A method of determining the dimensions and horsepower of an airship for any given performance

Description: A simple and easily applied method of calculating the dimensions and horsepower necessary for an airship to have any given performance is described and illustrated by examples. The method includes means for estimating the changes in performance or in size when modifications or new features are introduced into a design, involving increase or saving in weights, or changes in resistance or propulsive efficiency.
Date: May 1924
Creator: Burgess, C. P.
Partner: UNT Libraries Government Documents Department
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Structural Weight of Aircraft as Affected by the System of Design

Description: Various details of design or arrangement of the parts of airplane structures are shown and discussed, the use of these devices having resulted in the production of structures of adequate strength, yet of a weight less than one-half of the usual construction.
Date: November 1924
Creator: Hall, Charles Ward
Partner: UNT Libraries Government Documents Department
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On the Distribution of Lift Along the Span of an Airfoil With Displaced Ailerons

Description: "The effect of an aileron displacement on the distribution of the lift along the span is computed for an elliptic wing of aspect ratio 6 for three conditions. The lift distribution caused by the aileron displacement is uniform and extends normally beyond the inner end of the ailerons. Hence, the displacement of an aileron with constant chord length may bring about passing the stalling point of the adjacent wing sections, if these were near this point before" (p. 1).
Date: June 1924
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department
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Significance of the expression CL³/CD²

Description: Report presenting an analysis of the title coefficient as used in Kahn's formula for the ceiling.
Date: January 1924
Creator: von Sanden, H.
Partner: UNT Libraries Government Documents Department
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Airplanes in horizontal curvilinear flight

Description: The report discussing single and two-seater airplanes as well as larger airplanes.
Date: January 1924
Creator: Kann, Heinrich
Partner: UNT Libraries Government Documents Department
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The Induction Factor Used for Computing the Rolling Moment Due to the Ailerons

Description: In the following note, prepared for the National Advisory Committee for Aeronautics, this induction factor is determined from the result of a model test, and compared with a formula recently developed by the author. The two results are found to be in substantial agreement.
Date: April 1924
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department
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Longitudinal oscillation of an airplane Part 1: problem and method

Description: Report presenting some theoretical calculations for determining the problems of accelerated and disturbed motion, phenomena in an accidental or intentional disturbance through the deflection of the rudder or elevator, or any other change in the conditions of flight.
Date: April 1924
Creator: Fuchs, R. & Hopf, L.
Partner: UNT Libraries Government Documents Department
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Tests on a model of the D airplane T 39 of the "Deutsche Flugzeug Werke" (German Airplane Works)

Description: 'Experiments similar to those carried out with the A.E.G (Allgemeine Elektrizitats-Gesellschaft) were made in the small wind tunnel of the Gottingen laboratory on a model of the D.F.W. airplane T-29. Three series of tests were carried out on the model with a velocity head (or dynamic pressure) of 5 kg/sq m (1.02 lb/sq ft), during which one of the movable surfaces was deflected at various angles, while both the others were retained in their central positions. Of special interest among the result… more
Date: January 1924
Creator: Molthan, Wilhelm
Partner: UNT Libraries Government Documents Department
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Curvilinear Flight of Airplanes

Description: Note presenting an investigation of curvilinear flight, which is defined as steady horizontal flight in a circle in which no side slip occurs. The investigation occurred under very specific circumstances and rests on two basic assumptions, which are that the airplane lies correctly in the turn so the resultant of gravity and centrifugal force falls in the plane of symmetry and that the airplane must lie in the turn so that the axis coincides with the direction of motion.
Date: January 1924
Creator: Salkowski, E.
Partner: UNT Libraries Government Documents Department
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Note on the Relative Effect of the Dihedral and the Sweep Back of Airplane Wings

Description: "Dihedral and sweep back can properly be compared only to the extent to which their action is similar in a side slip. In general the rolling moments due to side slip are about three to six times greater for a given dihedral angle than for an equal angle of sweep back" (p. 1).
Date: January 1924
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department
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Triplane Tests

Description: "These experiments were carried out to determine the aerodynamic characteristics of various triplanes, which differed in the relative positions of the wings and, more especially, in the stagger, and in the shape of the wing sections. The tests were restricted to such dispositions as appeared constructively adapted to the plan form considered. Four different sets of wings were used in these tests, three of which had the same cross-section but differed in aspect ratio and in area" (p. 1).
Date: February 1924
Creator: Wieselsberger, C.
Partner: UNT Libraries Government Documents Department
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