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 Decade: 1940-1949
 Year: 1943
 Collection: National Advisory Committee for Aeronautics Collection
Adaptor for measuring principal strains with Tuckerman strain gage

Adaptor for measuring principal strains with Tuckerman strain gage

Date: January 1, 1943
Creator: Mcpherson, A E
Description: An adapter is described which uses three Tuckerman optical strain gages to measure the displacement of the three vortices of an equilateral triangle along lines 120 degrees apart. These displacements are substituted in well-known equations in order to compute the magnitude and direction of the principal strains. Tests of the adaptor indicate that principal strains over a gage length of 1.42 inch may be measured with a systematic error not exceeding 4 percent and a mean observational error of the order of + or minus 0.000006. The maximum observed error in strain was of the order of 0.00006. The directions of principal strains for unidirectional stress were measured with the adaptor with an average error of the order of 1 degree.
Contributing Partner: UNT Libraries Government Documents Department
Additional design charts relating to the stalling of tapered wings

Additional design charts relating to the stalling of tapered wings

Date: January 1, 1943
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body -- NACA model 84 series

Aerodynamic and hydrodynamic tests of a family of models of flying hulls derived from a streamline body -- NACA model 84 series

Date: January 1, 1943
Creator: Parkinson, John B; Olson, Roland E; Draley, Eugene C & Luoma, Arvo A
Description: A series of related forms of flying-boat hulls representing various degrees of compromise between aerodynamic and hydrodynamic requirements was tested in Langley Tank No. 1 and in the Langley 8-foot high-speed tunnel. The purpose of the investigation was to provide information regarding the penalties in water performance resulting from further aerodynamic refinement and, as a corollary, to provide information regarding the penalties in range or payload resulting from the retention of certain desirable hydrodynamic characteristics. The information should form a basis for over-all improvements in hull form.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil

Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil

Date: January 1, 1943
Creator: Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude rating of electrical apparatus

Altitude rating of electrical apparatus

Date: January 1, 1943
Creator: Lebenbaum, Paul, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Date: January 1, 1943
Creator: Becker, John V & Baals, Donald D
Description: An analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft. Equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Contributing Partner: UNT Libraries Government Documents Department
The analysis of strains indicated by multiple-strand resistance-type wire strain gages used as rosettes

The analysis of strains indicated by multiple-strand resistance-type wire strain gages used as rosettes

Date: January 1, 1943
Creator: Dow, Norris F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of various methods for computing drag from wake surveys

Comparison of various methods for computing drag from wake surveys

Date: January 1, 1943
Creator: Davis, Wallace F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Derivation of charts for determining the horizontal tail load variation with any elevator motion

Derivation of charts for determining the horizontal tail load variation with any elevator motion

Date: January 1, 1943
Creator: Pearson, Henry A
Description: The equations relating the wing and tail loads are derived for a unit elevator displacement. These equations are then converted into a nondimensional form and charts are given by which the wing- and tail-load-increment variation may be determined under dynamic conditions for any type of elevator motion and for various degrees of airplane stability. In order to illustrate the use of the charts, several examples are included in which the wing and tail loads are evaluated for a number of types of elevator motion. Methods are given for determining the necessary derivatives from results of wind-tunnel tests when such tests are available.
Contributing Partner: UNT Libraries Government Documents Department
Derivation of charts for determining the horizontal tail load variation with any elevator motion

Derivation of charts for determining the horizontal tail load variation with any elevator motion

Date: January 1, 1943
Creator: Pearson, Henry A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of general relations for the behavior of turbulent boundary layers

Determination of general relations for the behavior of turbulent boundary layers

Date: January 1, 1943
Creator: Von Doenhoff, Albert E & Tetervin, Neal
Description: An analysis has been made of a considerable amount of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. It was found that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter. This parameter was chosen as the ratio of the displacement thickness to the momentum thickness of the boundary layer. The variables that control the development of the turbulent boundary layer apparently are: (1) the ratio of the nondimensional pressure gradient, expressed in terms of the local dynamic pressure outside the boundary layer and boundary-layer thickness, to the local skin-friction coefficient and (2) the shape of the boundary layer. An empirical equation has been developed in terms of these variables that, when used with the momentum equation and the skin-friction relation, makes it possible to trace the development of the turbulent boundary layer to the separation point.
Contributing Partner: UNT Libraries Government Documents Department
Drag Measurements of a Protruding.50-Caliber Machine Gun with Barrel Jacket Removed

Drag Measurements of a Protruding.50-Caliber Machine Gun with Barrel Jacket Removed

Date: January 1, 1943
Creator: Luoma, Arvo A.
Description: Tests were made in 8-ft high-speed wind tunnel to determine the drag reduction possible by eliminating the barrel jacket of a protruding 50-caliber aircraft gun. It was found that the drag of a standard aircraft gun protruding into the air stream at right angles to the flow can be reduced by 23% by discarding the barrel jacket. At 300 mph and sea-level conditions, this amounts to a decrease in drag of from 83 to 64 pounds. A rough surface finish on the barrel was found to have no adverse effects on the drag of the barrel, the drag being actually less at high Mach Numbers.
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

Date: January 1, 1943
Creator: Allen, H. Julian & Nitzberg, Gerald E.
Description: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It i s shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients . The available data indicate that for low-drag and high critical compressibility speed airfoils and bodies of revolution, this effect is favorable.
Contributing Partner: UNT Libraries Government Documents Department
The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

Date: January 1, 1943
Creator: Nitzberg, Gerald E
Description: Summary: The effective change in the velocity of flow past a wing section, caused by the presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. It is shown that for a symmetrical section at zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M^2 to take account of compressibility effects. The Mach number, M, corresponds to conditions in the wind-tunnel test section with the model removed (p. 1.).
Contributing Partner: UNT Libraries Government Documents Department
Effect of fillers and of mixing procedure on the strength of plastic materials

Effect of fillers and of mixing procedure on the strength of plastic materials

Date: January 1, 1943
Creator: Kynoch, William & Patronsky, L A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of mass distribution on the lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

The effect of mass distribution on the lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

Date: January 1, 1943
Creator: Campbell, John P & Seacord, Charles L , Jr
Description: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing moments of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet

Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet

Date: January 1, 1943
Creator: Rafel, Norman
Description: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
Contributing Partner: UNT Libraries Government Documents Department
Effect of Rivet Holes on the Ultimate Strength Developed by 24S-T and Alclad 75S-T Sheet in Incomplete Diagonal Tension

Effect of Rivet Holes on the Ultimate Strength Developed by 24S-T and Alclad 75S-T Sheet in Incomplete Diagonal Tension

Date: January 1, 1943
Creator: Levin, L. Ross & Nelson, David H.
Description: Strength tests were made of a number of 24S-T and Alclad 75S-T aluminum-alloy shear webs to determine the effect of rivet or bolt holes on the shear strength. Data were obtained for webs which approached a condition of pure shear stress as well as for webs with well-developed diagonal tension. The rivet factor, (pitch minus diameter) divided by pitch, was varied from approximately 0.81 to 0.62. These tests indicated that the shear stresses on the gross section were nearly constant for all values of the rivet factor investigated if the other properties of the web were not changed.
Contributing Partner: UNT Libraries Government Documents Department
The effect on stability and control of a pusher propeller behind conventional tail surfaces as determined by tests of a powered model in the free-flight tunnel

The effect on stability and control of a pusher propeller behind conventional tail surfaces as determined by tests of a powered model in the free-flight tunnel

Date: January 1, 1943
Creator: Hollingworth, Thomas A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The exact solution of shear-lag problems in flat panels and box beams assumed rigid in the transverse direction

The exact solution of shear-lag problems in flat panels and box beams assumed rigid in the transverse direction

Date: January 1, 1943
Creator: Hildebrand, Francis B
Description: A mathematical procedure is herein developed for obtaining exact solutions of shear-lag problems in flat panels and box beams: the method is based on the assumption that the amount of stretching of the sheets in the direction perpendicular to the direction of essential normal stresses is negligible. Explicit solutions, including the treatment of cut-outs, are given for several cases and numerical results are presented in graphic and tabular form. The general theory is presented in a from which further solutions can be readily obtained. The extension of the theory to cover certain cases of non-uniform cross section is indicated. Although the solutions are obtained in terms of infinite series, the present developments differ from those previously given in that, in practical cases, the series usually converge so rapidly that sufficient accuracy is afforded by a small number of terms. Comparisons are made in several cases between the present results and the corresponding solutions obtained by approximate procedures devised by Reissner and by Kuhn and Chiarito.
Contributing Partner: UNT Libraries Government Documents Department
Exhaust-stack nozzle area and shape for individual cylinder exhaust-gas jet-propulsion system

Exhaust-stack nozzle area and shape for individual cylinder exhaust-gas jet-propulsion system

Date: January 1, 1943
Creator: Pinkel, Benjamin; Turner, Richard; Voss, Fred & Humble, Leroy V
Description: This report presents the results of an investigation conducted on the effect of exhaust-stack nozzle area, shape, and length on engine power, jet thrust, and gain in net thrust (engine propeller plus jet). Single-cylinder engine data were obtained using three straight stacks 25, 44, and 108 inches in length; an S-shaped stack, a 90 degree bend, a 180 degree bend, and a short straight stack having a closed branch faired into it. Each stack was fitted with nozzles varying in exit area from 0.91 square inch to the unrestricted area of the stack of 4.20 square inches. The engine was generally operated over a range of engine speeds from 1300 to 2100 r.p.m, inlet-manifold pressures from 22 to 30 inches of mercury absolute, and a fuel-air ratio of 0.08. The loss in engine power, the jet thrust, and the gain in net thrust are correlated in terms of several simple parameters. An example is given for determining the optimum nozzle area and the overall net thrust.
Contributing Partner: UNT Libraries Government Documents Department
Experimental Investigation of Impact in Landing on Water

Experimental Investigation of Impact in Landing on Water

Date: January 1, 1943
Creator: Kreps, R. L.
Description: The extent of agreement of the theoretical impact computations with the actual phenomenon has not as yet been fully clarified. There is on the one hand a certain imperfection in the theory (simplifying assumptions made) and on the other an insufficiency in the experimental data available. The object of our present paper is to show how far test results agree with the available approximate computation methods, to investigate in greater detail the physical nature of impact on water, and to perfect the experimental method of studying the phenomenon.
Contributing Partner: UNT Libraries Government Documents Department
An experimental survey of flow across banks of elliptical and pointed tubes

An experimental survey of flow across banks of elliptical and pointed tubes

Date: January 1, 1943
Creator: Palmer, Carl B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane I : high-inlet-velocity cowling with propeller cuffs tested in high-speed level flight

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane I : high-inlet-velocity cowling with propeller cuffs tested in high-speed level flight

Date: January 1, 1943
Creator: Johnston, J Ford
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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