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Annual report of the National Advisory Committee for Aeronautics (4th).administrative report including Technical Reports nos. 24 to 50

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, expenditures, problems, recommendations, and a compilation of technical reports produced.
Date: 1920
Item Type: Report
Partner: UNT Libraries Government Documents Department

The factors that determine the minimum speed of an airplane

Description: The author argues that because of a general misunderstanding of the principles of flight at low speed, there are a large number of airplanes that could be made to fly several miles per hour slower than at present by making slight modifications. In order to show how greatly the wing section affects the minimum speed, curves are plotted against various loadings. The disposition of wings on the airplane slightly affects the lift coefficient, and a few such cases are discussed. Another factor that has an effect on minimum speed is the extra lift exerted by the slip stream on the wings. Also discussed are procedures to be followed by the pilot, especially with regard to stick movements during low speed flight. Also covered are stalling, yaw, rolling moments, lateral control, and the effectiveness of ailerons and rudders.
Date: March 1, 1921
Creator: Norton, F. H.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Theory of Lifting Surfaces, Part 2

Description: A mathematical model is presented towards a theory of lifting and resistance on wings. It consists of a theory of multiplanes, conditions of flow at a great distance from the wing, lifting systems of minimum resistance, and free stream and stream limited by walls.
Date: August 1, 1920
Creator: Prandtl, L.
Item Type: Report
Partner: UNT Libraries Government Documents Department

Wind tunnel tests on a model of a monoplane wing with floating ailerons

Description: This report describes preliminary wind tunnel tests on a model of a monoplane wing equipped with wing tip floating ailerons. Lift and drag, as well as rolling and yawing moments, were measured.
Date: September 1, 1929
Creator: Knight, Montgomery & Bamber, Millard J
Item Type: Report
Partner: UNT Libraries Government Documents Department

Wind tunnel tests on airfoil boundary control using a backward opening slot

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. The greatest increase in maximum lift was 96 per cent, the greatest decrease in minimum drag was 27 per cent, and the greatest increase in the ratio, maximum lift coefficient/minimum drag coefficient, was 151 per cent.
Date: October 1, 1929
Creator: Knight, Montgomery & Bamber, Millard J
Item Type: Report
Partner: UNT Libraries Government Documents Department

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 the air flowed out of the slot rather than in through it, and in consequence, the maximum lift coefficient was decreased.
Date: October 1, 1929
Creator: Bamber, Millard J
Item Type: Report
Partner: UNT Libraries Government Documents Department

Soaring flight in Guinea

Description: The term soaring is applied here to the flight of certain large birds which maneuver in the air without moving their wings. The author explains the methods of his research and here gives approximate figures for the soaring flight of the Egyptian Vulture and the African White backed Vulture. Figures are given in tabular form for relative air speed per foot per second, air velocity per foot per second, lift/drag ratio, and selected coefficients. The author argues that although the figures given were taken from a very limited series of observations, they have nevertheless thrown some light on the use by birds of the internal energy of the air.
Date: August 1, 1920
Creator: Idrac, P.
Item Type: Report
Partner: UNT Libraries Government Documents Department

The determination of the effective resistance of a spindle supporting a model airfoil

Description: An attempt was made to determine the effect of spindle interference on the lift of the airfoil by measuring moments about the axis parallel to the direction of air flow. The values obtained are of the same degree as the experimental error, and for the present this effect will be neglected. The results obtained using a U.S.A. 15 wing (plotted here) show that the correction is nearly constant from 0 degrees to 10 degrees incidence and that at greater angles its value becomes erratic. At such angles, however, the wing drag is so high that the spindle correction and its attendant errors become relatively small and unimportant.
Date: January 1, 1921
Creator: Davidson, W E & Bacon, D L
Item Type: Report
Partner: UNT Libraries Government Documents Department

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 1, 1925
Creator: Green, Maurice W
Item Type: Report
Partner: UNT Libraries Government Documents Department

Model supports and their effects on the results of wind tunnel tests

Description: The airflow about a model while being tested is often sufficiently affected by the model support to lead to erroneous conclusions unless appropriate corrections are used. In this paper some new material on the subject is presented, together with a review of the airfoil support corrections used in several other laboratories.
Date: February 1, 1923
Creator: Bacon, David L
Item Type: Report
Partner: UNT Libraries Government Documents Department

The N.A.C.A. recording tachometer and angle of attack recorder

Description: This note contains photos and descriptions of airplane flight apparatus for use in conjunction with a recording galvanometer. In measuring the angle of attack a variable resistance is used, being controlled by a vane in the airstream. Thus it is only necessary to measure the change of resistance.
Date: August 1, 1923
Creator: Reid, H J E
Item Type: Report
Partner: UNT Libraries Government Documents Department

The NACA CYH airfoil section

Description: The NACA CYH airfoil section is described and its aerodynamic characteristics are given as tested in the NACA variable density wind tunnel at twenty atmosphere pressure. This section has a low drag, a high maximum lift, and a small travel of center of pressure.
Date: June 1, 1926
Creator: Higgins, George J
Item Type: Report
Partner: UNT Libraries Government Documents Department

NACA flight-path angle and air-speed recorder

Description: A new trailing bomb-type instrument for photographically recording the flight-path angle and air speed of aircraft in unaccelerated flight is described. The instrument consists essentially of an inclinometer, air-speed meter and a film-drum case. The inclinometer carries an oil-damped pendulum which records optically the flight-path angle upon a rotating motor-driven film drum. The air-speed meter consists of a taut metal diaphragm of high natural frequency which is acted upon by the pressure difference of a Prandtl type Pitot-static tube. The inclinometer record and air-speed record are made optically on the same sensitive film. Two records taken by this instrument are shown.
Date: April 1, 1926
Creator: Coleman, Donald G
Item Type: Report
Partner: UNT Libraries Government Documents Department

Airfoil lift with changing angle of attack

Description: Tests have been made in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics to determine the effects of pitching oscillations upon the lift of an airfoil. It has been found that the lift of an airfoil, while pitching, is usually less than that which would exist at the same angle of attack in the stationary condition, although exceptions may occur when the lift is small or if the angle of attack is being rapidly reduced. It is also shown that the behavior of a pitching airfoil may be qualitatively explained on the basis of accepted aerodynamic theory.
Date: September 1, 1927
Creator: Reid, Elliott G
Item Type: Report
Partner: UNT Libraries Government Documents Department

The use of wheel brakes on airplanes

Description: The results of tests to determine the effect of wheel brakes on the landing run of an airplane under conditions of load and at various wind velocities are presented.
Date: July 1, 1929
Creator: Carroll, Thomas & Defrance, Smith J
Item Type: Report
Partner: UNT Libraries Government Documents Department

The variation in pressures in the cockpit fan airplane in flight

Description: The results of an investigation to determine the pressures in the open cockpit of a Vought VE-7 airplane are given. The observed values are small and the effect upon instruments is inconsiderable.
Date: November 1, 1928
Creator: Carroll, Thomas & Mcavoy, Wm H
Item Type: Report
Partner: UNT Libraries Government Documents Department

Wall interference in closed type wind tunnels

Description: A series of tests has been conducted by the National Advisory Committee for Aeronautics, in the variable density wind tunnel on several airfoils of different sizes and sections to determine the effect of tunnel wall interference and to determine a correction which can be applied to reduce the error caused thereby. The use of several empirical corrections was attempted with little success. The Prandtl theoretical correction gives the best results and its use is recommended for correcting closed wind tunnel results to conditions of free air.
Date: March 1, 1927
Creator: Higgins, George J
Item Type: Report
Partner: UNT Libraries Government Documents Department