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Analysis of Circular Shell-Supported Frames

Description: From Summary: "This paper deals with the single problem if circular shell-supported frames subjected to concentrated loadings. A mathematical attack is developed and presented in the form of nondimensional-coefficient curves."
Date: May 1944
Creator: Wignot, J. E.; Combs, Henry & Ensrud, A. F.
Partner: UNT Libraries Government Documents Department
open access

Plastic Mountings for Aircraft Windshields

Description: Note presenting an investigation of several laminated glass windshields to determine their suitability for use in airplanes with pressurized cabins. The various constructions of the extended portions of the windshields which serve for mounting purposes included plastic alone, plastic and one sheet of glass extended, plastic extension reinforced with an aluminum strip, and plastic extension reinforced with a steel strip. The results indicated that the laminated windshields with plastic-mounting … more
Date: May 1944
Creator: Bradley, Kathryn H. & Axilrod, B. M.
Partner: UNT Libraries Government Documents Department
open access

Charts for rapid analysis of 45 degree strain-rosette data

Description: From Summary: "Charts are presented for rapidly determining the principal strains and stresses, the maximum shear strain and stress, and the orientation of principal axes from data on 45 degree strain rosettes. The charts may be used for analyzing the conventional data consisting of strains measured along three gage lines 45 degrees apart, but their application is more direct if the rosette data are obtained by means of special circuits that require the use of four gages 45 degrees apart."
Date: May 1944
Creator: Manson, S. S.
Partner: UNT Libraries Government Documents Department
open access

An automatic electrical analyzer for 45 degree strain-rosette data

Description: Report presenting a device that automatically analyses the data from a 45 degree strain rosette. The rosette strains are properly combined by means of an electric circuit to yield a direct meter reading of maximum shear strain and major and minor principal strains.
Date: May 1944
Creator: Manson, S. S.
Partner: UNT Libraries Government Documents Department
open access

Maximum Rates of Control Motion Obtained From Ground Tests

Description: Report discusses the results of testing to determine the maximum rates of control stick (elevator) motion and corresponding maximum stick forces that could be exerted based on experiments with several pilots. The main topics explored were the comparison of the maximum rates of push and pull, maximum rates of push and pull when a mental restriction was placed on the pilot, and maximum rates at which the pilot though he would apply the elevator control forces versus the actual application of forc… more
Date: May 1944
Creator: Beeler, De E.
Partner: UNT Libraries Government Documents Department
open access

An Automatically Variable Control Linkage and Its Effect on the Lateral-Control Characteristics of a High-Speed Fighter Airplane

Description: Report discusses an analysis and preliminary design of a control linkage that varies automatically with dynamic pressure. The advantages of the device, including greater lateral control than a fixed control linkage without additional aerodynamic balance, are detailed. The effect of variable linkage on lateral-control characteristics is also described.
Date: May 1944
Creator: Gillis, Clarence L.
Partner: UNT Libraries Government Documents Department
open access

Analysis of available data on the effectiveness of ailerons without exposed overhang balance

Description: From Introduction: "As a part of the general lateral-control investigation by the NACA, the large amount of two- and three-dimensional data on the rolling effectiveness of ailerons without exposed overhang balance is collected and analyzed in the present paper."
Date: May 1944
Creator: Crandall, Stewart M. & Swanson, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Estimation of Pressures on Cockpit Canopies, Gun Turrets, Blisters, and Similar Protuberances

Description: Report presenting methods for estimating pressure distributions over protuberances such as cockpit canopies, gun turrets, blisters, scoops, and sighting domes. The methods are applied to the estimation of the pressure distributions over spherical segment and faired gun turrets and over the protuberances on the Brewster SB2A-1 airplane. The effects of compressibility, interference, and flow separation are discussed.
Date: May 1944
Creator: Wright, Ray H.
Partner: UNT Libraries Government Documents Department
open access

Effect of Changes in Aileron Rigging on the Stick Forces of a High-Speed Fighter Airplane

Description: "The effects of changes in aileron rigging between 2 deg up and 2 deg down on the stick forces were determined from wind-tunnel data for a finite-span wing model. These effects were investigated for ailerons deflecting equally in both directions and linearly with stick deflection. Data were analyzed for a Frise, a sealed internally balanced, and a beveled-trailing-edge aileron" (p. 1).
Date: May 1944
Creator: Murray, Harry E. & Warren, S. Anne
Partner: UNT Libraries Government Documents Department
open access

An Analytical Investigation of the Effects of Elevator-Fabric Distortion on the Longitudinal Stability and Control of an Airplane

Description: From Summary: "The results of an analytical investigation to determine the qualitative effects of elevator-fabric distortion on the stick-force characteristics of an airplane are presented. These results indicate that serious alteration of intended stick-force characteristics can be produced by elevator-fabric distortion."
Date: May 1944
Creator: Mathews, Charles W.
Partner: UNT Libraries Government Documents Department
open access

A proposed method of measuring engine charge air flow in flight

Description: From Summary: "A method is outlined for determining in flight the weight rate of air flow to the engine equipped with a Bendix-Stromberg injection-type carburetor. The method has the advantage that no additional equipment need be inserted in the charge-air system and only a few simple measurements are necessary. The analysis of an air-box calibration of the carburetor to be used in interpreting the flight measurements is shown by an example."
Date: May 1944
Creator: Voglewede, T. J.
Partner: UNT Libraries Government Documents Department
open access

Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers

Description: Field measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of fluctuating tail … more
Date: May 8, 1944
Creator: Flight Research Maneuvers Section
Partner: UNT Libraries Government Documents Department
open access

A method for studying the hunting oscillations of an airplane with a simple type of automatic control

Description: "A method is presented for predicting the amplitude and frequency, under certain simplifying conditions, of the hunting oscillations of an automatically controlled aircraft with lag in the control system or in the response of the aircraft to the controls. If the steering device is actuated by a simple right-left type of signal, the series of alternating fixed-amplified signals occurring during the hunting may ordinarily be represented by a "square wave." Formulas are given expressing the respon… more
Date: May 5, 1944
Creator: Jones, Robert T.
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of rectangular exhaust-gas ejectors applicable for engine cooling

Description: "An experimental investigation of rectangular exhaust-gas ejector pumps was conducted to provide data that would serve as a guide to the design of ejector applications for aircraft engines with marginal cooling. The pumping characteristics of rectangular ejectors actuated by the exhaust of a single-cylinder aircraft engine were determined for a range of ejector mixing-section area from 20 to 50 square inches, over-all length from 12 to 42 inches, aspect ratio from 1 to 5, diffusing exit area fr… more
Date: May 1, 1944
Creator: Manganiello, Eugene J. & Bogatsky, Donald
Partner: UNT Libraries Government Documents Department
open access

The Theory of Propellers 1: Determination of the Circulation Function and the Mass Coefficient for Dual-Rotating Propellers

Description: "Values of the circulation function have been obtained for dual-rotating propellers. Numerical values are given for four, eight, and twelve-blade dual-rotating propellers and for advance ratios from 2 to about 6. In addition, the circulation function has been determine for single-rotating propellers for the higher values of the advance ratio. The mass coefficient, another quantity of significance in propeller theory, has been introduced" (p. 35).
Date: May 27, 1944
Creator: Theodorsen, Theodore
Partner: UNT Libraries Government Documents Department
open access

Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes

Description: "The results of measurements in the Langley full-scale tunnel of the maximum lift coefficients and stalling characteristics of airplanes have been collected. The data have been analyzed to show the nature of the effects on maximum lift and stall of wing geometry, fuselages and nacelles, propeller slipstream, surface roughness, and wing leading-edge appendages such as ducts, armaments, tip slats, and airspeed heads. Comparisons of full-scale-tunnel and flight measurements of maximum lift and sta… more
Date: May 19, 1944
Creator: Sweberg, Harold H. & Dingeldein, Richard C.
Partner: UNT Libraries Government Documents Department
open access

Cowling and Cooling Tests of a Fleetwings Model 33 Airplane in Flight

Description: Report presenting an investigation of the cooling of a Franklin 6-AC-29S horizontally opposed cylinder air-cooled engine installed in a Fleetwings model 33 trainer. The cowling on the airplane did not provide satisfactory cooling, but several alterations were tested, including with cylinder baffles. Results regarding engine cooling, aerodynamics of the cowling installation, and predicted versus actual cowling performance are provided.
Date: May 1944
Creator: Ellerbrock, Herman H., Jr. & Wilson, Herbert A., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Effect of Sideslip on Lateral Stability Characteristics 1: Circular Fuselage with Variations in Vertical-Tail Area and Tail Length With and Without Horizontal Tail Surface

Description: Report presenting the results of tests of a circular fuselage with various combinations of tail lengths and vertical tail surfaces with and without the horizontal tail surface in the 6- by 6-foot test section of the stability tunnel in the form of diagrams of variation of coefficients of lateral force and yawing moment with angle of yaw and angle of attack.
Date: May 1944
Creator: Fehlner, Leo F. & MacLachlan, Robert
Partner: UNT Libraries Government Documents Department
open access

Profile-Drag Coefficients of Conventional and Low-Drag Airfoils as Obtained in Flight

Description: Results of flight tests indicate that profile-drag coefficients which were obtained with the low-drag airfoils were lower than with the conventional types over the range of light coefficients tested. For comparable conditions of the lift coefficient and Reynolds Number, the low-drag airfoils have profile-drag coefficients which may be 27 percent lower than the profile drag of the conventional airfoils tested. Detailed results are presented graphically.
Date: May 1944
Creator: Zalovcik, John A.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a 1/20-Scale Powered Model of a Four-Engine Transport Airplane

Description: Report presenting tests on a scale model of a four-engine transport airplane to determine the stability characteristics, empennage control-surface effectiveness, the effect of propeller rotation on longitudinal stability, and a method for carrying spare wing panels under the fuselage. The effect of two models of wing power operation on the characteristics of the model was studied. The results indicate that the model possess satisfactory stick-fixed longitudinal stability for all normal flight c… more
Date: May 30, 1944
Creator: Stevens, Victor I.; Douglass, William M. & Dods, Jules B., Jr.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Oil Consumption and Piston Cooling on Knock-Limited Aircraft-Engine Performance

Description: Report discusses the "effects of oil introduced into the combustion chamber and of oil-spray piston cooling on the knock-limited performance of aircraft engines" (from Summary). A CFR engine and Allison V-1710 cylinder were used to test the rate of oil consumption, knock, and knock-limited brake mean effective pressure.
Date: May 1944
Creator: Huppert, Merle C.; Imming, Harry S. & Richard, Paul H.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel tests of dual-rotating propellers with systematic differences in number of blades, blade setting, and rotational speed of front and rear propellers

Description: Report presenting the results of aerodynamic tests of seven-blade propellers which were considered as a possible arrangement to avoid vibration difficulties. Variations of relative blade angle and rotational speeds of the front and rear components of a six-blade dual-rotating propeller were also investigated.
Date: May 1944
Creator: Gray, W. H.
Partner: UNT Libraries Government Documents Department
open access

Tests and Approximate Analysis of Bending Stresses Due to Torsion in a D-Section Box

Description: "Strain surveys were made on the stringers reinforcing a D-section box loaded in torsion and restrained from warping at the root. On the basis of the tests, a procedure is suggested for estimating the bending stresses due to torsion that occur near the flange of a D-section box. A similar test of a triangular-section box showed that for such a section there were no significant bending stresses due to torsion, a fact which was also shown theoretically" (p. 1).
Date: May 1944
Creator: Duberg, John E. & Brilmyer, Harold G.
Partner: UNT Libraries Government Documents Department
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