The Aerodynamic Characteristics of a Model Wing Having a Split Flap Deflected Downward and Moved to the Rear (open access)

The Aerodynamic Characteristics of a Model Wing Having a Split Flap Deflected Downward and Moved to the Rear

"Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear" (p. 1).
Date: May 1932
Creator: Weick, Fred E. & Harris, Thomas A.
System: The UNT Digital Library
The Avro 631 Training Airplane (British): A Two-Seat Light Biplane (open access)

The Avro 631 Training Airplane (British): A Two-Seat Light Biplane

Circular describing the Avro 631 training airplane, which is a British two-seat light biplane that is meant to be affordable and small. Details regarding the wings, fuselage, tail unit, landing gear, power plant, accommodation, characteristics, performance, drawings, and photographs are provided.
Date: May 1932
Creator: unknown
System: The UNT Digital Library
The Breguet 410 and 411 Military Airplanes (French): Multiplace Sesquiplane Fighters (open access)

The Breguet 410 and 411 Military Airplanes (French): Multiplace Sesquiplane Fighters

Circular presenting a description of the Breguet 410 and 411 military airplanes, which are both multiplace sesquiplane fighter aircraft. Details of the design, components, flying qualities, drawings, and photographs are provided.
Date: May 1932
Creator: Léglise, Pierre
System: The UNT Digital Library
Compression-ignition engine tests of several fuels (open access)

Compression-ignition engine tests of several fuels

"The tests reported in this paper were made to devise simple engine tests which would rate fuels as to their comparative value and their suitability for the operating conditions of the individual engine on which the tests are made. Three commercial fuels were used in two test engines having combustion chambers with and without effective air flow. Strictly comparative performance tests gave almost identical results for the three fuels. Analysis of indicator cards allowed a differentiation between fuels on a basis of rates of combustion" (p. 1).
Date: May 1932
Creator: Spanogle, J. A.
System: The UNT Digital Library
The D.H. "Fox Moth" Commercial Airplane (British): A Three-Passenger Light Cabin Biplane (open access)

The D.H. "Fox Moth" Commercial Airplane (British): A Three-Passenger Light Cabin Biplane

Circular describing the D.H. 83 "Fox Moth", which is a three-passenger light cabin biplane that is considered a commercial airplane despite taking many of its components from the company's existing two-seat touring and training light airplanes. A description of these components, design, flight characteristics, performance, drawings, and photographs are provided.
Date: May 1932
Creator: unknown
System: The UNT Digital Library
Determination of Stresses and Deformations of Aircraft Propellers (open access)

Determination of Stresses and Deformations of Aircraft Propellers

A method is described for testing the strength of propellers of any shape. It is shown that the shape of the propeller greatly affects the stresses, and that great caution must be exercised if the relieving effect of the centrifugal force, which exists in every propeller with a straight blade axis, is to be increased by curving the blade axis. In a numerical example, the calculation is made for a certain revolution speed at which the actual distortion is then measured. The results of the calculation agree satisfactorily with the experimental results.
Date: May 1932
Creator: Seewald, Friedrich
System: The UNT Digital Library
The Effect of Propellers and Nacelles on the Landing Speeds of Tractor Monoplanes (open access)

The Effect of Propellers and Nacelles on the Landing Speeds of Tractor Monoplanes

"This paper reports wind-tunnel tests giving the lift coefficients of large-scale wing-nacelle combinations both with and without the propeller. The tests were made to show the effect of nacelles, and idling and stopped propellers on the landing speeds of tractor monoplanes. Four types of nacelles with various cowlings were used in numerous positions with respect to both a Clark Y and a thick airfoil. The effect of both the idling and stopped propeller on lift, and consequently on landing speed, was negligible" (p. 1).
Date: May 1932
Creator: Windler, Ray
System: The UNT Digital Library
The Nature of Air Flow About the Tail of an Airplane in a Spin (open access)

The Nature of Air Flow About the Tail of an Airplane in a Spin

"Air flow about the fuselage and empennage during a high-angle-of-attack spin was made visible in flight by means of titanium-tetrachloride smoke and was photographed with a motion-picture camera. The angular relation of the direction of the smoke streamer to the airplane axes was computed and compared with the angular direction of the motion in space derived from instrument measurement of the spin of the airplane for a nearly identical mass distribution. The results showed that the fin and upper part of the rudder were almost completely surrounded by dead air, which would render them inoperative; that the flow around the lower portion of the rudder and the fuselage was nonturbulent; and that air flowing past the cockpit in a high-angle-of-attack spin could not subsequently flow around control surfaces" (p. 1).
Date: May 1932
Creator: Scudder, N. F. & Miller, M. P.
System: The UNT Digital Library
Procedure of the Purchasing and Supply Departments of the Miami Copper Company, Miami, Arizona (open access)

Procedure of the Purchasing and Supply Departments of the Miami Copper Company, Miami, Arizona

Report issued by the U.S. Bureau of Mines discussing the purchasing procedures documented by the Miami Copper Company in Arizona. Supplies, invoices, discounts, and accounting procedures are described in detail. This report includes tables, and illustrations.
Date: May 1932
Creator: Bishop, Fred L. & Keller, Albert E.
System: The UNT Digital Library
Properties of Crude Oil From the Greasewood Flat Area in Colorado (open access)

Properties of Crude Oil From the Greasewood Flat Area in Colorado

Report issued by the U.S. Bureau of Mines on two samples of crude oil collected from the Greasewood Flat area of northwestern Colorado. These samples were analyzed for many characteristics, and an approximate summary of those characteristics are presented. The report contains two tables of data.
Date: May 1932
Creator: Rue, H. P.
System: The UNT Digital Library
The Stieger ST. 4 Light Airplane (British): A Twin-Engine Four-Seat Low-Wing Cabin Monoplane (open access)

The Stieger ST. 4 Light Airplane (British): A Twin-Engine Four-Seat Low-Wing Cabin Monoplane

Circular describing the Stieger ST. 4, which is a twin-engine low-wing monoplane of the full cantilever type. Details regarding the wing, fuselage, power plant, landing gear, characteristics, drawings, and photographs are provided.
Date: May 1932
Creator: unknown
System: The UNT Digital Library
Torsional Vibration of Aircraft Engines (open access)

Torsional Vibration of Aircraft Engines

"Exhaustive torsional-vibration investigations are required to determine the reliability of aircraft engines. A general outline of the methods used for such investigations and of the theoretical and mechanical means now available for this purpose is given, illustrated by example. True vibration diagrams are usually obtained from vibration measurements on the completed engine. Two devices for this purpose and supplementing each other, the D.V.L. torsiograph and the D.V.L. torsion recorder, are described in this report" (p. 1).
Date: May 1932
Creator: Lürenbaum, Karl
System: The UNT Digital Library
Twelfth Rhon Soaring Contest, 1931 (open access)

Twelfth Rhon Soaring Contest, 1931

The crew of the "Fafnir" was given an excellent opportunity for collecting first-hand data as to the usefulness of gliders in the Alps. It is necessary to recount the remarkable glider achievements ahead of the Rhon Soaring Contest, in order to understand the tension and expectation with which the Rhon contest was anticipated. A description of some of the aircraft present at the event is provided.
Date: May 1932
Creator: Georgii, Walter
System: The UNT Digital Library
Wind-Tunnel Tests of a Hall High-Life Wing (open access)

Wind-Tunnel Tests of a Hall High-Life Wing

"Wind-tunnel tests have been made to find the lift, drag, and center-of-pressure characteristics of a Hall high-lift wing model. The Hall wing is essentially a split-flap airfoil with an internal air passage. Air enters the passage through an opening in the lower surface somewhat back of and parallel to the leading edge, and flows out through an opening made by deflecting the rear portion of the under surface downward as a flap. For ordinary flight conditions the front opening and the rear flap can be closed, providing in effect a conventional airfoil (the Clark Y in this case)" (p. 1).
Date: May 1932
Creator: Weick, Fred E. & Sanders, Robert
System: The UNT Digital Library
Wind-tunnel tests of the Fowler variable-area wing (open access)

Wind-tunnel tests of the Fowler variable-area wing

The lift, drag, and center of pressure characteristics of a model of the Fowler variable-area wing were measured in the NACA 7 by 10 foot wind tunnel. The Fowler wing consists of a combination of a main wing and an extension surface, also of airfoil section. The extension surface can be entirely retracted within the lower rear portion of the main wing or it can be moved to the rear and downward. The tests were made with the nose of the extension airfoil in various positions near the trailing edge of the main wing and with the surface at various angular deflections. The highest lift coefficient obtained was C(sub L) = 3.17 as compared with 1.27 for the main wing alone.
Date: May 1932
Creator: Weick, Fred E. & Platt, Robert C.
System: The UNT Digital Library
Lift and drag characteristics and gliding performance of an autogiro as determined in flight (open access)

Lift and drag characteristics and gliding performance of an autogiro as determined in flight

From Summary: "This report presents the results of flight test of the Pitcairn "PCA-2" autogiro. Lift and drag coefficients with the propeller stopped have been determined over approximately a 90 degree range of angles of attack. Based on the sum of fixed-wing and swept-disk areas, the maximum lift coefficient is 0.895, the minimum drag coefficient with propeller stopped is 0.015, and the maximum l/d with propeller stopped is 4.8. Lift coefficients were found also with the propeller delivering positive thrust and did not differ consistently from those found with propeller stopped. Curves of gliding performance included in this report show a minimum vertical velocity of 15 feet per second at an air speed of 36 miles per hour and a flight-path angle of -17 degrees. In vertical descent the vertical velocity is 35 feet per second."
Date: May 2, 1932
Creator: Wheatley, John B.
System: The UNT Digital Library
Fuel vaporization and its effect on combustion in a high-speed compression-ignition engine (open access)

Fuel vaporization and its effect on combustion in a high-speed compression-ignition engine

"The tests discussed in this report were conducted to determine whether or not there is appreciable vaporization of the fuel injected into a high-speed compression-ignition engine during the time available for injection and combustion. The effects of injection advance angle and fuel boiling temperature were investigated. The results show that an appreciable amount of the fuel is vaporized during injection even though the temperature and pressure conditions in the engine are not sufficient to cause ignition either during or after injection, and that when the conditions are such as to cause ignition the vaporization process affects the combustion. The results are compared with those of several other investigators in the same field" (p. 629).
Date: May 4, 1932
Creator: Rothrock, A. M. & Waldron, C. D.
System: The UNT Digital Library
Characteristics of Clark Y airfoils of small aspect ratios (open access)

Characteristics of Clark Y airfoils of small aspect ratios

This report presents the results of a series of wind tunnel tests showing the force, moment, and autorotational characteristics of Clark Y airfoils having aspect ratios varying from 0.5 to 3. An airfoil of rectangular plan form was tested with rectangular tips, flared tips, and semicircular tips. Tests were also made on one airfoil of circular plan form and two airfoils of elliptical plan form. The tests revealed a marked delay of the stall and a decided increase in values of maximum lift coefficient and maximum resultant force coefficient for aspect ratios of the order of 1 as compared with values for aspect ratios of 2 and 3.
Date: May 5, 1932
Creator: Zimmerman, C. H.
System: The UNT Digital Library
Force measurements on a 1/40-scale model of the U. S. Airship "Akron" (open access)

Force measurements on a 1/40-scale model of the U. S. Airship "Akron"

This report describes a series of tests made on a 1/40-scale model of the U. S. Airship "Akron" (ZRS-4) for the purpose of determining the drag, lift, and pitching moments of the bare hull and of the hull equipped with two different sets of fins. Measurements were also made of the elevator forces and hinge moments.
Date: May 6, 1932
Creator: Freeman, Hugh B.
System: The UNT Digital Library
Tests of nacelle-propeller combinations in various positions with reference to wings 2: thick wing - various radial-engine cowlings - tractor propeller (open access)

Tests of nacelle-propeller combinations in various positions with reference to wings 2: thick wing - various radial-engine cowlings - tractor propeller

This report is the second of a series giving the results obtained in the 20-foot wind tunnel of the National Advisory Committee for Aeronautics on the interference drag and propulsive efficiency of nacelle-propeller-wing combinations. The first report gave the results of the test of a N.A.C.A. cowled air-cooled engine nacelle located in 21 positions with reference to a thick wing. The present report gives results of tests of a normal engine nacelle with several types of cowling and fairings in four of the positions with reference to the same wing. (author).
Date: May 12, 1932
Creator: Wood, Donald H.
System: The UNT Digital Library
Rates of fuel discharge as affected by the design of fuel-injection systems for internal-combustion engines (open access)

Rates of fuel discharge as affected by the design of fuel-injection systems for internal-combustion engines

Using the method of weighing fuel collected in a receiver during a definite interval of the injection period, rates of discharge were determined, and the effects noted, when various changes were made in a fuel-injection system. The injection system consisted primarily of a by-pass controlled fuel pump and an automatic injection valve. The variables of the system studied were the pump speed, pump-throttle setting, discharge-orifice diameter, injection-valve opening and closing pressures, and injection-tube length and diameter.
Date: May 15, 1932
Creator: Gelalles, A. G. & Marsh, E. T.
System: The UNT Digital Library
The effect of area aspect ratio on the yawing moments of rudders at large angles of pitch on three fuselages (open access)

The effect of area aspect ratio on the yawing moments of rudders at large angles of pitch on three fuselages

This reports presents the results of measurements made of yawing moments produced by rudder displacement for seven rudders mounted on each of three fuselages at angles of pitch of 0 degree, 8 degrees, 12 degrees, 20 degrees, 30 degrees and 40 degrees. The dimensions of the rudders were selected to cover the range of areas and aspect ratios commonly used, while the ratios of rudder area to fin area and of rudder chord to fin chord were kept approximately constant. An important result of the measurements is to show that increased aspect ratio gives increased yawing moments for a given area, provided the maximum rudder displacement does not exceed 25 degrees. If large rudder displacements are used, the effect of aspect ratio is not so great.
Date: May 16, 1932
Creator: Dryden, Hugh L. & Monish, B. H.
System: The UNT Digital Library
The International Metric System of Weights and Measures (open access)

The International Metric System of Weights and Measures

General overview of the metric system.
Date: May 26, 1932
Creator: unknown
System: The UNT Digital Library