National Advisory Committee for Aeronautics (NACA) - 117 Matching Results

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Experiments on the Resistance of Airplane Wheels and Radiators

Description: Experiments were made on the resistance of four airplane wheels of different sizes and coverings and two Lamblin radiators. The results show the important influence of the wheel coverings. The closing of a shutter, which was fitted to one of the radiators, considerably lessened the resistance.
Date: July 1924
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ultra-Light Alloys and Their Utilization on Aircraft

Description: Memorandum presenting an overview of ultra-light alloys and their potential use on an aircraft. A definition of ultra-light alloys, some of the present possibilities of ultra-light alloys, and some of the principles governing the use of the alloys in aircraft are provided.
Date: May 1924
Creator: Portevin, A. M. & DeFleury, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Specializing for Record-Breaking

Description: This report seeks to determine what constitutes airplane performance and what line should be followed in seeking to break records if the designer is given a free hand. Some of the considerations for designers include the ratio of engine power to wing area, minor refinements, low wing loading, and duration.
Date: February 1924
Creator: Warner, Edward P.
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Partner: UNT Libraries Government Documents Department
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Loss of the Dixmude

Description: The causes of the destruction of the Dixmude are discussed and some conclusions are drawn. The author believes a gasoline fire instead of a lightning strike was probably responsible, but the public believes otherwise.
Date: April 1924
Creator: Eckener, Hugo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Inertia Coefficients of an Airship in a Frictionless Fluid

Description: The apparent inertia of an airship hull is examined. The exact solution of the aerodynamical problem is studied for hulls of various shapes with special attention given to the case of an ellipsoidal hull. So that the results for the ellipsoidal hull may be readily adapted to other cases, they are expressed in terms of the area and perimeter of the largest cross section perpendicular to the direction of motion by means of a formula involving a coefficient kappa which varies only slowly when the … more
Date: 1924
Creator: Bateman, H.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Note on the Pressure Distribution Over the Hull of Elongated Airships With Circular Cross Section

Description: "This note, prepared for the National Advisory Committee for Aeronautics, contains the demonstration that the pressure around the circular cross section of an elongated airship, plotted against the diameter of symmetry, can be expected to be represented by a straight line" (p. 1).
Date: May 1924
Creator: Munk, Max M.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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