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 Decade: 1930-1939
 Collection: National Advisory Committee for Aeronautics Collection
Determination of the profile drag of an airplane wing in flight at high Reynolds numbers

Determination of the profile drag of an airplane wing in flight at high Reynolds numbers

Date: January 1, 1939
Creator: Bicknell, J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Application of the Von Karman-millikan Laminar Boundary-layer Theory and Comparison With Experiment

An Application of the Von Karman-millikan Laminar Boundary-layer Theory and Comparison With Experiment

Date: October 1, 1935
Creator: Doenhoff, A. E. V.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Design of Airplane-engine Superchargers

The Design of Airplane-engine Superchargers

Date: October 1, 1937
Creator: Von Der Null, W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of curvature on the transition from laminar to turbulent boundary layer

The effect of curvature on the transition from laminar to turbulent boundary layer

Date: September 1, 1937
Creator: Clauser, M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Hydrodynamic and aerodynamic tests of a family of models of seaplane floats with varying angles of dead rise

Hydrodynamic and aerodynamic tests of a family of models of seaplane floats with varying angles of dead rise

Date: July 1, 1939
Creator: Parkinson, John B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of the aerodynamic characteristics of the normal and three reflexed airfoils in the variable density wind tunnel

A comparison of the aerodynamic characteristics of the normal and three reflexed airfoils in the variable density wind tunnel

Date: August 1, 1931
Creator: Defoe, George L
Description: An investigation was made of the aerodynamic effects of reflexing the trailing edge of three commonly used airfoils. Six airfoils were used in the investigation: three having the normal profiles of the Navy 60, the Boeing 106, and the Gottingen 398, and three having these profiles modified to obtain a reflexed trailing edge with the mean camber line changed to give Cmc/4=0. The tests were conducted at a value of the Reynolds Number of approximately 3,100,000 in the variable density wind tunnel of the National Advisory Committee for Aeronautics. Measurements of lift, drag, and pitching moment were made on each of the six airfoils. The expected reduction of the center of pressure travel was obtained. The maximum lift was reduced approximately 12 per cent and the minimum profile drag approximately 4 per cent.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of airplane landing speeds

An investigation of airplane landing speeds

Date: September 1, 1930
Creator: Ridley, Kenneth F
Description: This paper describes an investigation on airplane landing speeds which was made to determine the applicability of accepted aerodynamic theory to the prediction of this particular performance characteristic. The experimental work consisted in measuring the landing speed of several monoplanes by a new photographic method. The results of these tests supplemented by available information regarding biplanes were compared with predictions made with basic aerodynamic theory. The prediction makes use of the fundamental relation between wing loading, lift coefficient, and speed of level flight, and the effects of aspect ratio and proximity to the ground on lift curve slope.
Contributing Partner: UNT Libraries Government Documents Department
The N.A.C.A. apparatus for studying the formation and combustion of fuel sprays and the results from preliminary tests

The N.A.C.A. apparatus for studying the formation and combustion of fuel sprays and the results from preliminary tests

Date: September 1, 1931
Creator: Rothrock, A M
Description: Described here is an apparatus for studying the formation and combustion of fuel sprays under conditions closely simulating those in a high speed compression-ignition engine. The apparatus consists of a single-cylinder modified test engine, a fuel injection system so designed that a single charge of fuel can be injected into the combustion chamber, an electric driving motor, and a high-speed photographic apparatus. The cylinder head of the engine has a vertical disk form of combustion chamber whose sides are glass windows. When the fuel is injected into the combustion chamber, motion pictures at the rate of 2000 per second are taken of the spray formation by means of spark discharges. When combustion takes place, the light of combustion is recorded on the same photographic film as the spray photographs. Included here are the results of some tests to determine the effect of air temperature, air flow, and nozzle design on the spray formation. The results show that the compression temperature has little effect on the penetration of the fuel spray, but does not affect the dispersion, that air velocities of about 300 feet per second are necessary to destroy the core of the spray, and that the effect of air ...
Contributing Partner: UNT Libraries Government Documents Department
Span load distribution on two monoplanes wing models as affected by twist and sweepback

Span load distribution on two monoplanes wing models as affected by twist and sweepback

Date: July 1, 1930
Creator: Knight, Montgomery
Description: The results presented in this note show the effect of twist and sweepback on the span load distribution over two monoplane wing models. The tests were made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The data are taken from the results of an investigation dealing primarily with lateral stability. As presented, they are suitable as an aid in the structural design of certain monoplane wings.
Contributing Partner: UNT Libraries Government Documents Department
The prevention of the ice hazard on airplanes

The prevention of the ice hazard on airplanes

Date: July 1, 1930
Creator: Geer, William C
Description: A review of various methods to prevent ice formation and adhesion to aircraft surfaces is given. It was concluded that the adhesion of ice to a surface may be reduced somewhat by the application of certain waxes and varnishes. In the experiments described, the varnishes containing calcium stearate and calcium oleate gave the best results. In wind tunnel tests, the adhesion was further reduced by the application of these waxes and varnishes to a thin, heat insulating layer of rubber. The adhesion of ice is greatly reduced when the surface consists of a vehicle which carries an oil in sufficient quantity so that the surface of the vehicle is self lubricating. Ice may be removed from wings, struts, wires and other parts of an airplane during flight by the inflation of properly constructed pneumatic rubber members, providing that these members have been previously treated with a suitable low adhesion oil.
Contributing Partner: UNT Libraries Government Documents Department
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