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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Collection: National Advisory Committee for Aeronautics Collection
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
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.; Olson, Roland E. & House, Rufus O.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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
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. & Clauser, F.
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
Strength tests on thin-walled duralumin cylinders in torsion

Strength tests on thin-walled duralumin cylinders in torsion

Date: August 1, 1932
Creator: Lundquist, Eugene E
Description: This report is the first of a series presenting the results of strength tests on thin-walled cylinders and truncated cones of circular and elliptical section; it comprises the results obtained to date from torsion (pure shear) tests on 65 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The effect of variations in the length/radius and radius/thickness ratios on the type of failure is indicated, and a semi-empirical equation for the shearing stress at maximum load is given.
Contributing Partner: UNT Libraries Government Documents Department
Strength tests on paper cylinder in compression, bending and shear

Strength tests on paper cylinder in compression, bending and shear

Date: April 1, 1931
Creator: Rhodes, Richard V & Lundquist, Eugene E
Description: Static tests on paper cylinders were conducted at the Langley Memorial Aeronautical Laboratory at Langley Field, Virginia, to obtain qualitative information in connection with a study of the strength of stressed-skin fuselages. The effects of radius-thickness ratio and bulkhead spacing were investigated with the cylinders in compression, bending, combined bending and shear, and torsion.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of air and fuel oil temperatures on spray penetration and dispersion

Some effects of air and fuel oil temperatures on spray penetration and dispersion

Date: May 1, 1930
Creator: Gelalles, A G
Description: Presented here are experimental results obtained from a brief investigation of the appearance, penetration, and dispersion of oil sprays injected into a chamber of highly heated air at atmospheric pressure. The development of single sprays injected into a chamber containing air at room temperature and at high temperature was recorded by spray photography equipment. A comparison of spray records showed that with the air at the higher temperature, the spray assumed the appearance of thin, transparent cloud, the greatest part of which rapidly disappeared from view. With the chamber air at room temperature, a compact spray with an opaque core was obtained. Measurements of the records showed a decrease in penetration and an increase in the dispersion of the spray injected into the heated air. No ignition of the fuel injected was observed or recorded until the spray particles came in contact with the much hotter walls of the chamber about 0.3 second after the start of injection.
Contributing Partner: UNT Libraries Government Documents Department
The nature of air flow about the tail of an airplane in a spin

The nature of air flow about the tail of an airplane in a spin

Date: May 1, 1932
Creator: Scudder, N F & Miller, M P
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Tests of six symmetrical airfoils in the variable density wind tunnel

Tests of six symmetrical airfoils in the variable density wind tunnel

Date: July 1, 1931
Creator: Jacobs, Eastman N
Description: This paper is the first of a series covering an investigation of a family of airfoils all formed from a basic profile. It gives in preliminary form the results of six symmetrical airfoils, differing only in maximum thickness. The maximum thickness-to-chord ratios are 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21.
Contributing Partner: UNT Libraries Government Documents Department
Remarks on the elastic axis of shell wings

Remarks on the elastic axis of shell wings

Date: April 1, 1936
Creator: Kuhn, Paul
Description: The definitions of flexural center, torsional center, elastic center, and elastic axis are discussed. The calculation of elastic centers is dealt with in principle and a suggestion is made for the design of shear webs.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel research comparing lateral control devices, particularly at high angles of attack XI : various floating tip ailerons on both rectangular and tapered wings

Wind tunnel research comparing lateral control devices, particularly at high angles of attack XI : various floating tip ailerons on both rectangular and tapered wings

Date: May 1, 1933
Creator: Weick, Fred E & Harris, Thomas A
Description: Discussed here are a series of systematic tests being conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present tests were made with six different forms of floating tip ailerons of symmetrical section. The tests showed the effect of the various ailerons on the general performance characteristics of the wing, and on the lateral controllability and stability characteristics. In addition, the hinge moments were measured for the most interesting cases. The results are compared with those for a rectangular wing with ordinary ailerons and also with those for a rectangular wing having full-chord floating tip ailerons. Practically all the floating tip ailerons gave satisfactory rolling moments at all angles of attack and at the same time gave no adverse yawing moments of appreciable magnitude. The general performance characteristics with the floating tip ailerons, however, were relatively poor, especially the rate of climb. None of the floating tip ailerons entirely eliminated the auto rotational moments at angles of attack above the stall, but all of them gave lower moments than a plain wing. Some of the floating ailerons fluttered if given sufficiently large deflection, but this could have been eliminated by ...
Contributing Partner: UNT Libraries Government Documents Department
Development of an impinging-jet fuel-injection valve nozzle

Development of an impinging-jet fuel-injection valve nozzle

Date: April 1, 1931
Creator: Spanogle, J A & Hemmeter, G H
Description: During an investigation to determine the possibilities and limitations of a two-stroke-cycle engine and ignition, it was necessary to develop a fuel injection valve nozzle to produce a disk-shaped, well dispersed spray. Preliminary tests showed that two smooth jets impinging upon each other at an angle of 74 degrees gave a spray with the desired characteristics. Nozzles were built on this basis and, when used in fuel-injection valves, produced a spray that fulfilled the original requirements. The spray is so well dispersed that it can be carried along with an air stream of comparatively low velocity or entrained with the fuel jet from a round-hole orifice. The characteristics of the spray from an impinging-jet nozzle limits its application to situations where wide dispersion is required by the conditions in the engine cylinder and the combustion chamber.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of three methods for calculating the compressive strength of flat and slightly curved sheet and stiffener combinations

Comparison of three methods for calculating the compressive strength of flat and slightly curved sheet and stiffener combinations

Date: March 1, 1933
Creator: Lundquist, Eugene E
Description: This report gives a comparison of the accuracy of the three methods for calculating the compressive strength of flat sheet and stiffener combinations such as occur in stressed-skin or monocoque structures for aircraft. Of the three methods based upon various assumptions with regard to the interaction of sheet and stiffener, the method based upon mutual action of the stiffener and an effective width as a column gave the best agreement with the results of the tests. An investigation of the effect of small curvature resulted in the conclusion that the compressive strength of the curved panels is, for all practical purposes, equal to the strength of flat panels except for thick sheet where non-uniform curvature throughout the length may cause the strength of the curved panel to be 10 to 15 percent less than that of a corresponding flat panel.
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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
Tests on thrust augmenters for jet propulsion

Tests on thrust augmenters for jet propulsion

Date: September 1, 1932
Creator: Jacobs, Eastman N & Shoemaker, James M
Description: This series of tests was undertaken to determine how much the reaction thrust of a jet could be increased by the use of thrust augmenters and thus to give some indication as to the feasibility of jet propulsion for airplanes. The tests were made during the first part of 1927 at the Langley Memorial Aeronautical Laboratory. A compressed air jet was used in connection with a series of annular guides surrounding the jet to act as thrust augmenters. The results show that, although it is possible to increase the thrust of a jet, the increase is not large enough to affect greatly the status of the problem of the application of jet propulsion to airplanes.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of the Fowler variable-area wing

Wind-tunnel tests of the Fowler variable-area wing

Date: May 1, 1932
Creator: Weick, Fred E & Platt, Robert C
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Spinning characteristics of wings II : rectangular Clark Y biplane cellule: 25 percent stagger; 0 degree decalage; gap/chord 1.0

Spinning characteristics of wings II : rectangular Clark Y biplane cellule: 25 percent stagger; 0 degree decalage; gap/chord 1.0

Date: April 1, 1935
Creator: Bamber, M J
Description: General methods of theoretical analysis of airplane spinning characteristics have been available for some time. Some of these methods of analysis might be used by designers to predict the spinning characteristics of proposed airplane designs if the necessary aerodynamic data were known. The present investigation, to determine the spinning characteristics of wings, is planned to include variations in airfoil sections, plan forms, and tip shapes of monoplane wings and variations in stagger, gap, and decalage for biplane cellules. The first series of tests, made on a rectangular Clark Y monoplane wing, are reported in reference 1. That report also gives an analysis of the data for predicting the probable effects of various important parameters on the spin for normal airplanes using such a wing. The present report is the second of the series. It gives the aerodynamic characteristics of a rectangular Clark Y biplane cellule in spinning attitudes and includes a discussion of the data, using the method of analysis given in reference 1.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several airfoils of low aspect ratio

Aerodynamic characteristics of several airfoils of low aspect ratio

Date: August 1, 1935
Creator: Zimmerman, C H
Description: This paper presents the results of wind-tunnel tests of several airfoils of low aspect ratio. The airfoils included three circular Clark Y airfoils with different amounts of dihedral, two Clark Y airfoils with slots in their portions, and three flat-plate airfoils. Lift, drag, and pitching-moment characteristics of the slotted airfoils with slots open and closed; pitching moment characteristics of one of the slotted airfoils with slots open and closed; and lift characteristics of the flat-plate airfoils are included. The results reveal a definite improvement of lift, drag, and pitching-moment characteristics with increase in dihedral of the circular Clark Y wing. Lift characteristics near the stall were found to depend markedly on the shape of the extreme tip but were not greatly affected by slots through the after portion of the airfoils. Changes in plan form of the flat-plate airfoils gave erroneous indications of the effect to be expected from changes in plan form of an airfoil of Clark Y section. The minimum drag characteristics of the circular Clark Y airfoils were found to be substantially the same as for a Clark Y airfoil of conventional aspect ratio.
Contributing Partner: UNT Libraries Government Documents Department
A study of factors affecting the steady spin of an airplane

A study of factors affecting the steady spin of an airplane

Date: August 1, 1933
Creator: Scudder, Nathan F
Description: Data from wind-tunnel tests on a model of the NY-1 airplane were used in a study of the effect on the steady spin of a number of factors considered to be important. The factors were of two classes, mass distribution effects and aerodynamic effects. The study indicated that mass extended along the longitudinal axis has no detrimental effect or is even slightly beneficial, mass extended along the lateral axis is detrimental if the airplane spins with the inner wing tip far down, and mass extended along the normal axis, if of considerable magnitude, has a strong favorable effect. The aerodynamic effects considered in terms of rolling, pitching, and yawing moments added to those for a conventional airplane showed that added stable rolling moment could contribute favorable effect on the spin only in decreasing the amount of inward sideslip required for equilibrium. Negative pitching moment of moderate magnitude has unfavorable effect on a high-angle-of-attack spin, and stable yawing moment has pronounced beneficial effect on the spin. Experimental data from various sources were available to verify nearly all the deductions resulting from the study of the curves. When these results were considered for the purpose of deciding upon the best means to ...
Contributing Partner: UNT Libraries Government Documents Department
Basic requirements of fuel-injection nozzles for quiescent combustion chambers

Basic requirements of fuel-injection nozzles for quiescent combustion chambers

Date: June 1, 1931
Creator: Spanogle, J A & Foster, H H
Description: This report presents test results obtained during an investigation of the performance of a single-cylinder, high-speed, compression-ignition test engine when using multiple-orifice fuel-injection valve nozzles in which the number and the direction of the orifices were varied independently.
Contributing Partner: UNT Libraries Government Documents Department
A balanced diaphragm type of maximum cylinder pressure indicator

A balanced diaphragm type of maximum cylinder pressure indicator

Date: December 1, 1930
Creator: Spanogle, J A & Collins, John H , Jr
Description: A balanced diaphragm type of maximum cylinder pressure indicator was designed to give results consistent with engine operating conditions. The apparatus consists of a pressure element, a source of controlled high pressure and a neon lamp circuit. The pressure element, which is very compact, permits location of the diaphragm within 1/8 inch of the combustion chamber walls without water cooling. The neon lamp circuit used for indicating contact between the diaphragm and support facilitates the use of the apparatus with multicylinder engines.
Contributing Partner: UNT Libraries Government Documents Department
Combustion-engine temperatures by the sodium line-reversal method

Combustion-engine temperatures by the sodium line-reversal method

Date: March 1, 1936
Creator: Brevoort, Maurice J
Description: The sodium line-reversal method has been used in some preliminary measurements of flame temperature. Improvements in the method involving a photographic recorder and a means of correcting for the dirtiness of the windows are described. The temperatures so obtained are compared with those calculated from pressure diagrams.
Contributing Partner: UNT Libraries Government Documents Department
A complete tank test of the hull of the Sikorsky S-40 flying boat - American Clipper Class

A complete tank test of the hull of the Sikorsky S-40 flying boat - American Clipper Class

Date: December 1, 1934
Creator: Dawson, John R
Description: The results of a complete test in the N.A.C.A. tank on a model of the hull of Sikorsky S-40 flying boat ('American Clipper') are reported. The test data are given in tables and curves. From these data non-dimensional coefficients are derived for use in take-off calculations and the take-off time and run for the S-40 are computed. The computed take-off time was obtained by the Sikorsky Aviation Corporation in performance tests of the actual craft.
Contributing Partner: UNT Libraries Government Documents Department
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