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 Decade: 1920-1929
 Serial/Series Title: NACA Technical Notes
 Collection: Technical Report Archive and Image Library
Tests on duralumin columns for aircraft construction

Tests on duralumin columns for aircraft construction

Date: November 1, 1924
Creator: Lee, John G
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.
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
Resistance of a fifteen-centimeter disk

Resistance of a fifteen-centimeter disk

Date: December 1, 1926
Creator: Shoemaker, James M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Characteristics of the N.A.C.A 97, Clark Y, and N.A.C.A. M6 Airfoils with Particular Reference to the Angle of Attack

The Characteristics of the N.A.C.A 97, Clark Y, and N.A.C.A. M6 Airfoils with Particular Reference to the Angle of Attack

Date: December 1, 1927
Creator: Higgins, George J.
Description: No abstract available.
Contributing Partner: UNT Libraries Government Documents Department
Precision of wing sections and consequent aerodynamic effects

Precision of wing sections and consequent aerodynamic effects

Date: January 1, 1927
Creator: Rizzo, Frank
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The influence of inlet air temperature and jacket water temperature on initiating combustion in a high speed compression ignition engine

The influence of inlet air temperature and jacket water temperature on initiating combustion in a high speed compression ignition engine

Date: March 1, 1924
Creator: Matthews, Robertson & Gardiner, Arthur W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement of the moments of inertia of full scale airplanes

Measurement of the moments of inertia of full scale airplanes

Date: January 1, 1927
Creator: Green, M W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of tube length upon the recorded pressures from a pair of static orifices in a wing panel

The effect of tube length upon the recorded pressures from a pair of static orifices in a wing panel

Date: November 1, 1926
Creator: Carroll, T & Mixon, R E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the Resistance of spheres and ellipsoids in wind tunnels

On the Resistance of spheres and ellipsoids in wind tunnels

Date: January 1, 1921
Creator: Riabouchinsky, D P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of the inflow theory of the propeller

Development of the inflow theory of the propeller

Date: November 1, 1920
Creator: Betz, A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The drag of airships

The drag of airships

Date: January 1, 1926
Creator: Havill, C H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of protruding gasoline tanks upon the characteristics of an airfoil

Effect of protruding gasoline tanks upon the characteristics of an airfoil

Date: October 1, 1926
Creator: Jacobs, Eastman 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
Compressive Strength of Tapered Airplane Struts

Compressive Strength of Tapered Airplane Struts

Date: December 1, 1923
Creator: Lewe, Viktor
Description: Methods are here given for ascertaining the value of n in Euler's simplified formula, P = n (EI/l(sup 2)), for the compressive strength of tapered airplane struts, by estimating from curves and by calculation.
Contributing Partner: UNT Libraries Government Documents Department
Drag or negative traction of geared-down supporting propellers in the downward vertical glide of a helicopter

Drag or negative traction of geared-down supporting propellers in the downward vertical glide of a helicopter

Date: September 1, 1920
Creator: Toussaint, A
Description: Discussed here are computations of drag or negative traction of geared down supporting propellers in the downward vertical glide of a helicopter. By means of Frounde's Theory, the maximum value of the drag of a windmill is calculated. For wooden propellers, the author finds that the difference between the drag and the weight is proportional to the number of blades and is larger for propellers of small diameter; thus it is 25 kg. for a six blade propeller with a diameter of 2 m. 50. The author notes that if we are to adopt large propellers, we must have recourse to a different method of construction, resulting in large dimension propellers much lighter than those made of wood. In discussing insufficient drag, the author notes that the question of the drag of geared down supporting propellers can only be decided by experiment.
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 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
Wind tunnel tests on a model of a monoplane wing with floating ailerons

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

Date: September 1, 1929
Creator: Knight, Montgomery & Bamber, Millard J
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.
Contributing Partner: UNT Libraries Government Documents Department
Resistance of streamline wires

Resistance of streamline wires

Date: March 1, 1928
Creator: Defoe, George L
Description: This note contains the results of tests to determine the resistance of four sizes of streamline wire. The investigation was conducted in the six-inch wind tunnel of the National Advisory Committee for Aeronautics. The tests were made at various velocities and it was found that the resistance of streamline wires was considerably less than that of round wires of equivalent strength. Scale effect was also found since, with an increase of Reynolds Number, a decrease in the resistance coefficient was obtained.
Contributing Partner: UNT Libraries Government Documents Department
A dangerous seaplane landing condition

A dangerous seaplane landing condition

Date: May 1, 1928
Creator: Carroll, Thomas
Description: A peculiar phenomena in seaplane landing is observed and reported. The seaplane having executed a normal fast landing at low incidence, a forward movement of the control stick effected an unusual condition in that the seaplane left the water suddenly in an abnormal attitude. The observations describing this phenomena are offered as a warning against possible accident and as a conjectural cause of seaplane landing accidents of a certain kind.
Contributing Partner: UNT Libraries Government Documents Department
The formation of ice upon airplanes in flight

The formation of ice upon airplanes in flight

Date: August 1, 1929
Creator: Carroll, Thomas & Mcavoy, William H
Description: This report describes the atmospheric conditions under which ice is formed upon the exposed parts of airplanes in flight. It identifies the formation found under different conditions, and describes some studies of preventative means.
Contributing Partner: UNT Libraries Government Documents Department
The variation in pressures in the cockpit fan airplane in flight

The variation in pressures in the cockpit fan airplane in flight

Date: November 1, 1928
Creator: Carroll, Thomas & Mcavoy, Wm H
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.
Contributing Partner: UNT Libraries Government Documents Department
The use of wheel brakes on airplanes

The use of wheel brakes on airplanes

Date: July 1, 1929
Creator: Carroll, Thomas & Defrance, Smith J
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.
Contributing Partner: UNT Libraries Government Documents Department
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