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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
The factors that determine the minimum speed of an airplane

The factors that determine the minimum speed of an airplane

Date: March 1, 1921
Creator: Norton, F H
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.
Contributing Partner: UNT Libraries Government Documents Department
The testing of aviation engines

The testing of aviation engines

Date: December 1, 1924
Creator: Dubois, R N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theory of Lifting Surfaces, Part 2

Theory of Lifting Surfaces, Part 2

Date: August 1, 1920
Creator: Prandtl, L.
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.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of air flow on the penetration and distribution of oil sprays

Some effects of air flow on the penetration and distribution of oil sprays

Date: December 1, 1929
Creator: Rothrock, A M & Beardsley, E G
Description: Tests were made to determine the effects of air flow on the characteristics of fuel sprays from fuel injection valves. Curves and photographs are presented showing the airflow throughout the chamber and the effects of the air flow on the fuel spray characteristics. It was found that the moving air had little effect on the spray penetration except with the 0.006 inch orifice. The moving air did, however, affect the oil particles on the outside of the spray cone. After spray cut-off, the air flow rapidly distributed the atomized fuel throughout the spray chamber.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel force tests in wing systems through large angles of attack

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

Date: August 1, 1928
Creator: Wenzinger, Carl J & Harris, Thomas A
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.
Contributing Partner: UNT Libraries Government Documents Department
Notes on the N.A.C.A. control force recorder

Notes on the N.A.C.A. control force recorder

Date: July 1, 1923
Creator: Reeid, H J E
Description: Emphasized here is the desirability of using recording instruments in the investigation of the characteristics of airplanes with particular reference to the National Advisory Committee for Aeronautics (NACA) control force recorder. Given here are photographs, records, and a description of the instrument developed by NACA for investigations on different types of aircraft. Described here is an instrument for recording control forces. At present, this control force recorder registers only the forces exerted on the stick. However, attachments are being designed to enable the forces on the rudder bar also to be recorded. The instrument in its final form will consist of three parts, namely, the recorder, the controller for the stick, and the controller for the rudder. The first two are in use now. The theory of operation is simple. In the controller, which is slipped over and fastened to the stick, are small electrical resistances which vary with the force applied to the handle. The recording apparatus then consists of suitable variable resistances properly connected to galvanometers whose deflections are proportional to the forces applied to the stick.
Contributing Partner: UNT Libraries Government Documents Department
Notes on the theory of the accelerometer

Notes on the theory of the accelerometer

Date: May 1, 1920
Creator: Warner, E P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of the N.P.L. airship models in the variable density wind tunnel

Tests of the N.P.L. airship models in the variable density wind tunnel

Date: September 1, 1927
Creator: Higgins, George J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests on airfoil boundary control using a backward opening slot

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

Date: October 1, 1929
Creator: Knight, Montgomery & Bamber, Millard J
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.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests on an airfoil equipped with a split flap and a slot

Wind tunnel tests on an airfoil equipped with a split flap and a slot

Date: October 1, 1929
Creator: Bamber, Millard J
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.
Contributing Partner: UNT Libraries Government Documents Department
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