National Advisory Committee for Aeronautics (NACA) - 49 Matching Results

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The aerodynamics of a wind-tunnel fan

Description: From Introduction: "This paper deals only with the aerodynamics of the fan proper and demonstrates the manner in which the radial distribution of axial velocity of fluid through a fan is governed by geometry of the fan itself."
Date: August 1941
Creator: Corson, Blake W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Ground Effect on the Lifting Airscrew

Description: "A study is presented of ground effect as applied to the lifting airscrew of the type used in modern gyroplanes and helicopters. The mathematical analysis of the problem has been verified by tests made of three rotor models in the presence of a large circular "ground plane." The results of the study are presented in the form of convenient charts" (p. 1).
Date: December 1941
Creator: Knight, Montgomery & Hefner, Ralph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Determination of Control System Pulley-Axis Angles

Description: From Introduction: "The ideas developed in this paper are presented as a means of saving the designer's time and as a method of reduction of control-system friction by an accurate calculation of pulley-axis angles without the errors and difficult checking incident to any graphical method."
Date: September 1941
Creator: Driggs, I. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Calculation of Span Load Distributions of Swept-Back Wings

Description: "Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9" (p. 1).
Date: December 1941
Creator: Mutterperl, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combined Beam-Column Stresses of Aluminum-Alloy Channel Sections

Description: "The results of tests of 65 specimens of aluminum-alloy channel sections are graphed for stresses due to axial and bending loads as functions of the ratio of length of specimen to its radius of gyration, and from these data a suggested design chart is derived that is suitable for ready use" (p. 1).
Date: September 1941
Creator: Hutton, J. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of stress-strain curves obtained by single-thickness and pack methods

Description: Report presenting an apparatus for supporting a single thickness of sheet against buckling so that its compressive yield strength can be determined by the single-thickness method. The results of testing are compared with those from two other methods. This method results in substantial cost savings as compared to the pack method.
Date: August 1941
Creator: Paul, D. A.; Howell, F. M. & Grieshaber, H. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Description: "The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces" (p. 1).
Date: July 1941
Creator: Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compression tests of some 17S-T aluminum-alloy specimens of I cross section

Description: Report presenting testing of specimens cut from a specially extruded I-beam of 17S-T aluminum alloy with one flange wider than the other under axial compression. Only the two longest specimens failed as columns, while the shorter ones failed by local buckling. The agreement between experimental and calculated values of critical stress can be improved by considering the effect of restraint at the loaded edges of the web and adopting a more accurate buckling treatment beyond the elastic range.
Date: March 1941
Creator: Hill, H. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Compressive Yield Strength of Extruded Shapes of 24ST Aluminum Alloy

Description: The following report discusses an investigation that was made to determine the tensile and the compressive properties of a large number of 24ST extruded shapes selected at random from commercial production in order to investigate the interrelation of these properties.
Date: January 1941
Creator: Templin, R. L.; Howell, F. M. & Hartmann, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling and Performance Tests of a Continental A-75 Engine

Description: Note presenting an investigation to determine the performance of a small airplane with two Continental A-75 air-cooled engines enclosed in the wings. The object of the tests was to determine the quantity of air and the pressure difference required for satisfactory cooling of the engine at sea level and at altitude. The engine could be cooled satisfactorily at sea level with wide-open throttle and maximum-power mixture with a pressure difference of 4.5 inches of water and 1.06 pounds of cooling … more
Date: July 1941
Creator: Ellerbrock, Herman H., Jr. & Bullock, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling Effects of an Airplane Equipped With an NACA Cowling and a Wing-Duct Cooling System

Description: Report presenting cooling tests of a Northrop A-17A attack airplane equipped with a conventional NACA cowling and then with a wing-duct cooling system. Ground cooling for the wing-duct system without cowl flap was better than for the cowling with flap, but was improved by installing a cowl flap. Satisfactory temperatures were maintained in climb and high-speed flight, but a greater quantity of cooling air was needed for the wing-duct system.
Date: June 1941
Creator: Turner, L. I., Jr.; Bierman, David & Boothby, W. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correction of the Lifting-Line Theory for the Effect of the Chord

Description: "It is shown that a simple correction for the chord of a finite wing can be deduced from the three-dimensional potential flow around an elliptic plate. When this flow is compared with the flow around a section of an endless plate, it is found that the edge velocity is reduced by the factor 1/E, where E is the ratio of the semiperimeter to the span. Applying this correction to the circulation brings the theoretical lift into closer agreement with experiments" (p. 1).
Date: July 1941
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Damping characteristics of dashpots

Description: An investigation of the damping characteristics of dashpots was carried out combining theory and experiment. Laminar flow was assumed and three equations for the steady velocity of a piston moving in a cylinder filled with liquid were derived. In the first equation, the piston was assumed coaxial in the cylinder and, in the second equation, the piston was assumed eccentric in the cylinder with an element of the piston in contact with the cylinder wall. The third equation is for a piston of circ… more
Date: October 1941
Creator: Peterson, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of control-surface characteristics from NACA plain-flap and tab data

Description: From Summary: "The data from previous NACA pressure-distribution investigations of plain flaps and tabs have been analyzed and are presented in this paper in a form readily applicable to the problems of control-surface design. The experimentally determined variation of aerodynamic parameters with flap chord and tab chord are given in chart form and comparisons are made with the theory. With the aid of these charts and the theoretical relationships for a thin airfoil, the aerodynamic characteris… more
Date: February 1941
Creator: Ames, Milton B., Jr. & Sears, Richard I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Aging on Mechanical Properties of Aluminum-Alloy Rivets

Description: "Curves and tabular data present the results of strength tests made during and after 2 1/2 years of aging on rivets and rivet wire of 3/16-inch nominal diameter. The specimens were of aluminum alloy: 24S, 17S, and A17S of the duralumin type and 53S of the magnesium-silicide type" (p. 1).
Date: April 1941
Creator: Roop, Frederick C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Alternately High and Low Repeated Stresses Upon the Fatigue Strength of 25S-T Aluminum Alloy

Description: "Fatigue tests were made on one lot of 3/4 inch diameter rolled-and-drawn 25S-T aluminum-alloy rod normal in composition and tensile properties. The specimens were tested at 3500 cycles per second in a rotating-beam fatigue test machine. Tests were made for three ratios (20:1, 50:1, and 200:1) of the number of cycles applied at low stress to the number applied at high stress. In general, failure occurred when the number of cycles at either the low or the high stress approached the ordinary fati… more
Date: January 1941
Creator: Stickley, G. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Methods of Testing on the Ultimate Loads Supported by Stiffened Flat Sheet Panels Under Edge Compression

Description: Note presenting testing of two series of stiffened flat sheet specimens tested under edge compression using various end conditions: round ends, flat ends, and continuous panels. The specimens consisted of aluminum-alloy flat sheet stiffened by three hat-shaped extruded aluminum-alloy stiffeners. The results indicated that the length of the specimen has an insignificant effect on the ultimate compressive load.
Date: June 1941
Creator: Holt, Marshall
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of several supercharger control methods on engine performance

Description: Report presenting an analytical comparison of a variety of superchargers using the same hypothetical engine, which include a single-speed, a two-speed, and a variable-speed DVL centrifugal supercharger, the Szydlowski-Planiol supercharger with a single-speed and a two-speed transmission, and a turbosupercharger.
Date: February 1941
Creator: Wasielewski, Eugene W. & King, J. Austin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effects of Aerodynamic Heating on Ice Formations on Airplane Propellers

Description: Report presenting an investigation of the effect of aerodynamic heating on propeller-blade temperatures and its relation to propeller icing. Test results indicate that the outermost station at which ice formed on a propeller blade as determined by the blade temperature rise resulting from the aerodynamic heating at that point.
Date: March 1941
Creator: Rodert, Lewis A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Some Present-Day Airplane Design Trends on Requirements for Lateral Stability

Description: Note presenting computations made to determine the effects of some airplane design trends on the fin area and the dihedral angle required for lateral stability. The specific factors studied were wing loading, moments of inertia in roll and yaw, wing chord, and tail length. The results of the computations are presented in the form of diagrams of variations of fin area with dihedral angle for neutral stability.
Date: June 1941
Creator: Bamber, Millard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The End-Plate Effect of a Horizontal-Tail Surface on Vertical Tail Surface

Description: Note presenting the end-plate effect of the horizontal-tail surface on the vertical-tail surface as theoretically studied by derivation of the flow corresponding to the condition of minimum induced drag and by solution of the usual lifting-line equations. The results obtained by the two methods were considerably different, indicated that the condition derived is not a close approximation to the actual condition.
Date: February 1941
Creator: Katzoff, S. & Mutterperl, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hydrodynamic Tests of a 1/10-Size Model of the Hull of the Latécoère 521 Flying Boat: NACA Model 83

Description: From Summary: "A 1/10-size model of the hull of the French flying boat Latecoere 521 was tested in the NACA tank. This model is one of a series of models of the hulls of actual flying boats of both foreign and domestic type that are being tested in the NACA tank to provide information regarding the water characteristics of a variety of forms of hull and to illustrate the development of present-day types of flying boat. The lines and the offsets of the hull were obtained from the manufacturer th… more
Date: December 1941
Creator: Olson, Roland E. & Lina, Lindsay J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method of Determining the Equilibrium Performance and the Stability of an Engine Equipped With an Exhaust Turbosupercharger

Description: "The performance of an exhaust turbine driving a supercharger is investigated by means of a sample calculation based on reasonable assumptions for the purpose of determining whether the assumed installation is stable with respect to changes in the mass of gas handled, boost pressure, etc. The arrangement was found to be stable throughout the entire range of operation. The method developed can be generally applied" (p. 1).
Date: November 1941
Creator: Rea, James Buchanan
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Methods of Analyzing Wind-Tunnel Data for Dynamic Flight Conditions

Description: "The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind-tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedra… more
Date: October 1941
Creator: Donlan, C. J. & Recant, I. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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