National Advisory Committee for Aeronautics (NACA) - 19 Matching Results

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Air Flow Investigation for Location of Angle of Attack Head on a JN4h Airplane

Description: The technical staff of the NACA at Langley Field, has made a series of free flight tests with a JN4h airplane in order to find the best place for an instrument for measuring the angle of attack. A "neutral zone" was found where the air remains either at rest relative to the undisturbed air beyond the influence of the airplane, or is set in motion parallel to the motion of the airplane. This zone is about midway between the two wings and slightly in front of, or at the vertical plane through the… more
Date: August 1925
Creator: Freeman, R. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of the Lift and Drag Characteristics of an Airplane in Flight

Description: Flight tests to determine lift and drag characteristics are discussed. A review is given of the fundamental principles on which the tests are based and on the forces acting on an airplane in the various conditions of steady flight. Glide with and without propeller thrust and the relation between angle of attack and the indicated airspeed for different conditions of steady flight are discussed. The glide test procedure and the problem of the propeller are discussed.
Date: August 1925
Creator: Green, Maurice W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Distribution on the Nose of an Airship in Circling Flight

Description: In recent tests on the pressures occurring on the envelope and control surfaces of the naval airship C-7, it was noted that the pressures on the nose of the airship, while flying in level circling flight, were symmetrically distributed. Such a condition can only occur when the nose of the airship is pointed directly into the wind, and to accomplish this in circling flight, the axis of the airship must then be parallel to the direction of the motion of the nose. The question was raised as to whe… more
Date: August 1925
Creator: Fairbanks, Karl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Propeller Scale Effect and Body Interference

Description: "This note shows that the main part of the discrepancy between full flight propeller performance and the performance of models in a wind tunnel is due to a scale effect, and that a minor part is caused by body interference. Analyses are made of propeller performances on several standard airplanes, and the actual brake horsepower compared with the power as calculated from model test data. The calculated power is based on that absorbed by a wind tunnel propeller model which is geometrically simil… more
Date: September 1925
Creator: Weick, Fred E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Velocity Distribution Caused by an Airplane at the Points of a Vertical Plane Containing the Span

Description: "A formula for the computation of the vertical velocity component on all sides of an airplane is deduced and discussed. The formation is of value for the interpretation of such free flight tests where two airplanes fly alongside each other to facilitate observation" (p. 1).
Date: March 1925
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Note on the Air Forces on a Wing Caused by Pitching.

Description: Report containing information on the air forces on a wing produced by its pitching at a finite rate of angular velocity. The condition of smooth flow at the region of the trailing edge is maintained. The wing then experiences the same lift as if moving with the momentary velocity of the rear edge.
Date: March 1925
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Estimation of Airplane Performance From Wind Tunnel Tests on Conventional Airplane Models

Description: Calculations of the magnitude of the correction factors and the range of their variations for wind tunnel models used in making aircraft performance predictions were made for 23 wind tunnel models. Calculated performances were compared with those actually determined for such airplanes as have been built and put through flight test. Except as otherwise noted, all the models have interplane struts and diagonal struts formed to streamwise shape. Wires were omitted in all cases. All the models were… more
Date: May 1925
Creator: Warner, Edward P. & Ober, Shatswell
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The comparison of well-known and new wing sections tested in the variable density wind tunnel

Description: Three groups of airfoils have been tested in the variable density wind tunnel. The first group contains three airfoils. The second group is a systematic series of twenty-seven airfoils. The third group consists of several frequently used wing sections.
Date: May 1925
Creator: Higgins, George J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Drift of an Aircraft Guided Towards Its Destination by Directional Receiving of Radio Signals Transmitted From the Ground

Description: Following a curved path increases the distance to be flown, and a type of radio navigation that forces the adoption of such a path is therefore less efficient than one that marks out a definite straight line between the point of departure and the intended destination, and holds the airplane to that line. To determine the loss of efficiency resulting from curvature of the path, calculations were made for two particular cases by the method of step-by-step integration. The calculations were based … more
Date: June 1925
Creator: Warner, Edward P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Model Tests on the Economy and Effectiveness of Helicopter Propellers

Description: The average velocity of helicopter blades relative to the air is greater than that of airplane wings. The helicopter may turn out to be more economical than the airplane wing for extreme velocities of horizontal flight, the airplane then requiring a very great speed range.
Date: 1925
Creator: Munk, Max M.
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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Determination and Classification of the Aerodynamic Properties of Wing Sections

Description: The following note, prepared for the NACA, contains several remarks on the possible improvement of the experimental determination of the aerodynamic properties of wing sections. It shows how errors of observation can subsequently be partially eliminated, and how the computation of the maxima or minima of aerodynamic characteristics can be much improved.
Date: September 1925
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Flettner Rotor Ship in the Light of the Kutta-Joukowski Theory and of Experimental Results

Description: "In this paper the fundamental principles of the Flettner rotor ship (Reference I) are discussed in the light of the Kutta-Joukowski theory and available experimental information on the subject. A brief exposition of the Kutta-Joukowski theory is given and the speed of the rotor ship Buckau computed, first by using effective propulsive force obtained by the above theory, and then by direct application of wind tunnel data" (p. 1).
Date: October 1925
Creator: Rizzo, Frank
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Altitude Chamber for the Study and Calibration of Aeronautical Instruments

Description: "The design and construction of an altitude chamber, in which both pressure and temperature can be varied independently, was carried out by the NACA at the Langley Memorial Aeronautical Laboratory for the purpose of studying the effects of temperature and pressure on aeronautical research instruments. Temperatures from +20c to -50c are obtained by the expansion of CO2from standard containers. The chamber can be used for the calibration of research instruments under altitude conditions simulatin… more
Date: November 1925
Creator: Reid, H. J. E. & Kirchner, Otto E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Simplified Propeller Design for Low-Powered Airplanes

Description: "The object of this report is to furnish the designer and builder of small airplanes a simple system for designing the propeller and making the drawing. An empirical design method is used, based on tests of model propellers in a wind tunnel and full scale tests of propellers in flight. The actual designing is accomplished by means of charts and involves very little calculation" (p. 1).
Date: January 1925
Creator: Weick, Fred E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aircraft Engine Design

Description: From Introduction: "The subject of this paper is so broad in scope that a large volume might be devoted to it. In a short paper of this kind it is possible simply to sketch in the high lights of aircraft engine design showing the development to date, the possibilities of the future, and the underlying fundamental principles. Summarizing this development and referring to the graph (Fig.1), we that there is now a water-cooled engine in every power from 150 to 800 HP. and an air-cooled engine in t… more
Date: January 1925
Creator: Wilson, E. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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