National Advisory Committee for Aeronautics (NACA) - 78 Matching Results

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Airfoil in Sinusoidal Motion in a Pulsating Stream

Description: "In the present paper, under the same lineaeizing assumptions as are made in the derivation in reference 1 but with the explicit consideration and simplification of the form of the wake extending from the rear of the airfoil, the methods of Theodorsen (reference 2) have been extended to obtain the forces on the airfoil not only at a fixed angle of attack but also in arbitrary motion" (p. 1).
Date: June 1947
Creator: Greenberg, J. Mayo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Performance of Jet Engine From Characteristics of Components 1: Aerodynamic and Matching Characteristics of Turbine Component Determined With Cold Air

Description: "The performance of the turbine component of an NACA research jet engine was investigated with cold air. The interaction and the matching of the turbine with the NACA eight-stage compressor were computed with the combination considered as a jet engine. The over-all performance of the engine was then determined. The internal aerodynamics were studied to the extent of investigating the performance of the first stator ring and its influence on the turbine performance" (p. 397).
Date: June 6, 1947
Creator: Goldstein, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

Description: "Requirements of an automatic engine control, as affected by engine characteristics, have been analyzed for a direct-coupled turbojet engine. Control parameters for various conditions of engine operation are discussed. A hypothetical engine control is presented to illustrate the use of these parameters. An adjustable speed governor was found to offer a desirable method of over-all engine control. The selection of a minimum value of fuel flow was found to offer a means of preventing unstable bur… more
Date: June 13, 1947
Creator: Novik, David & Otto, Edward W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of compressible flows past aerodynamic shapes by use of the streamline curvature

Description: "A simple approximate method is given for the calculation of isentropic irrotational flows past symmetrical airfoils, including mixed subsonic-supersonic flows. The method is based on the choice of suitable values for the streamline curvature in the flow field and the subsequent integration of the equations of motion. The method yields limiting solutions for potential flow. The effect of circulation is considered" (p. 1).
Date: June 1947
Creator: Perl, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calibration and Measurement in Turbulence Research by the Hot-Wire Method

Description: "The problem of turbulence in aerodynamics is at present being attacked both theoretically and experimentally. In view of the fact however that purely theoretical considerations have not thus far led to satisfactory results the experimental treatment of the problem is of great importance. Among the different measuring procedures the hot wire methods are so far recognized as the most suitable for investigating the turbulence structure" (p. 1).
Date: June 1947
Creator: Kovasznay, Laszlo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for the Minimum-Weight Design of Multiweb Wings in Bending

Description: Report presenting a method for the calculation of the buckling stress of a multiweb wing in bending as well as design charts based on this method for the minimum-weight design of 24S-T aluminum alloy sheets, extruded 75S-T aluminum alloy, and extruded 0-1HTA magnesium alloy. An example of the use of the charts is also provided.
Date: June 1947
Creator: Schuette, Evan H. & McCulloch, James C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A comparison of three theoretical methods of calculating span load distribution on swept wings

Description: From Summary: "Three methods for calculating span load distribution, those developed by V.M Falkner, Wm. Mutterperl, and J. Weissinger, have been applied to five swept wings. The angles of sweep ranged from -45 degrees to +45 degrees. These methods were examined to establish their relative accuracy and case of application. Experimentally determined loadings were used as a basis for judging accuracy. For the convenience of the readers the computing forms and all information requisite to their ap… more
Date: June 9, 1947
Creator: Van Dorn, Nicholas H. & DeYoung, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compression Shocks of Detached Flow

Description: "It is known that compression shocks which lead from supersonic to subsonic velocity cause the flow to separate on impact on a rigid wall. Such shocks appear at bodies with circular symmetry or wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high a back pressure. The form of the compression shocks observed therein is investigated" (p. 1).
Date: June 1947
Creator: Eggink
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Combinations of Shear and Longitudinal Direct Stress for Long Plates With Transverse Curvature

Description: Note presenting a theoretical solution for the buckling stresses of long plates with transverse curvature loaded in shear and longitudinal direct stress. The theoretical critical-stress combinations for plates with either simply supported or clamped edges are given in figures and tables and a comparison is made with previous theoretical solutions. Results regarding the theoretical results, empirical results and design curves, and some interaction formulas are provided.
Date: June 1947
Creator: Batdorf, S. B.; Schildcrout, Murry & Stein, Manuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Combinations of Torsion and Direct Axial Stress for Thin-Walled Cylinders

Description: "A theoretical solution is presented for the determination of the combinations of direct axial stress and torsion which cause thin-walled cylinders with either simply supported or clamped edges to buckle. This theoretical solution is used in conjunction with available test data to develop empirical curves and formulas for use in design. Comparisons are made with theoretical and empirical solutions obtained in other investigations" (p. 1).
Date: June 1947
Creator: Batdorf, S. B.; Stein, Manuel & Schildcrout, Murry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Shear Stress of Long Plates With Transverse Curvature

Description: "A theoretical solution is presented for the buckling stress of long plates with transverse curvature loaded in shear. The results are given in the form of curves and formulas for plates with simply supported or clamped edges for a wide range of plate dimensions. Comparisons are made with theoretical solutions obtained in previous investigations" (p. 1).
Date: June 1947
Creator: Batdorf, S. B.; Schildcrout, Murry & Stein, Manuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical Stress of Thin-Walled Cylinders in Axial Compression

Description: "Empirical design curves are presented for the critical stress of thin-walled cylinders loaded in axial compression. These curves are plotted in terms of nondimensional parameters of small-deflection theory and are compared with theoretical curves derived for the buckling of cylinders with simply supported and clamped edges. An empirical equation is given for the buckling of cylinders having a length-radius ratio greater than about 0.75" (p. 1).
Date: June 1947
Creator: Batdorf, S. B.; Shildcrout, Murry & Stein, Manuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Critical Stress of Thin-Walled Cylinders in Torsion

Description: Note presenting a theoretical solution for the critical stress of thin-walled cylinders loaded in torsion. The results are presented in terms of simple formulas and curves which are applicable to a wide range of cylinder dimensions. The theoretical results are found to be in fairly good agreement with experimental results.
Date: June 1947
Creator: Batdorf, S. B.; Stein, Manuel & Schildcrout, Murry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Crystal Structure at Room Temperature of Six Cast Heat-Resisting Alloys

Description: The crystal structures of alloys 61, X-40,X-50, 422-19, 6059, and Vitallium, derived from x-ray diffraction, are discussed. The alloys have been, or are being considered for use in gas turbine applications. The predominant phase was a solid solution of the face centered cubic type of the principal constituent elements.The lattice parameters were found to be between 3.5525 and 3.5662.
Date: June 3, 1947
Creator: Rosenbaum, Burt M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Description of Russian Aircraft Engines "AM 35" and "AM 38"

Description: The Russian AM 35 and AM 38 aircraft engines have superchargers with a swirl throttle, which appears to be a purely Russian development. This paper gives the results of test runs of the two engines, including the effects of the swirl throttle on engine performance.
Date: June 1947
Creator: Denkmeier, H. & Gross, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Aerodynamic Refinement on the Aerodynamic Characteristics of a Flying-Boat Hull

Description: Note presenting an investigation to determine the reduction in drag that could be obtained for a conventional-type flying-boat hull by means of aerodynamic refinements. For comparisons, tests were made on a streamline body simulating the fuselage of a modern transport airplane.
Date: June 1947
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Critical Mach Number and Flutter on Maximum Power Loading of Ducted Fans

Description: Report presenting flutter tests of two wind-tunnel-fan models, one with conventional Clark Y airfoil sections and one with high-camber blade sections. The results indicated that higher flutter speeds were present for high lift coefficients for high-camber blades. Results regarding lift coefficients, blade-tip twisting, power loading, critical Mach numbers, flutter point, vibrational frequencies, and stall-flutter tip Mach number are provided.
Date: June 1947
Creator: Regier, Arthur A.; Barmby, John G. & Hubbard, Harvey H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Distance on Airplane Noise

Description: Report presenting a review of literature to determine the frequency of sound of a given source strength that is loudest at various distances from the source. Frequencies in the range from 500 to 1000 cycles per second were found to be the easiest to hear, even at a distance of several miles. Sound data obtained from a light trainer airplane showed good agreement with predictions.
Date: June 1947
Creator: Regier, Arthur A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Horizontal-Tail Position on the Hinge Moments of an Unbalanced Rudder in Attitudes Simulating Spin Conditions

Description: Report presenting an investigation in the free-spinning tunnel to determine the effect of horizontal-tail position on rudder hinge moments in simulated spinning conditions. Hinge-moment measurements were made on an unbalanced rudder on a rectangular vertical tail at six positions on the horizontal tail. Results regarding rudder hinge moments, tuft tests, and application of the hinge-moment data are provided.
Date: June 1947
Creator: Stone, Ralph W., Jr. & Burk, Sanger M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Length-Beam on the Aerodynamic Characteristics of Flying-Boat Hulls

Description: Report presenting a wind-tunnel investigation to determine the effect of length-beam ratio on the aerodynamic characteristics of a family of flying-boat hulls in the presence of a wing. The hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Results regarding the two-dimensional and three-dimensional mounting setups, drag reduction, and aerodynamic refinement effects are provided.
Date: June 1947
Creator: Yates, Campbell C. & Riebe, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Screens in Wide-Angle Diffusers

Description: "An experimental investigation at low airspeeds was made of the filling effect observed when a screen or similar resistance is placed across a diffuser. The filling effect is found to be real in that screens can prevent separation or restore separated flow in diffusers even of extreme divergence and to depend principally on screen location and pressure-drop coefficient of the screen. Results are given for three different diffusers of circular cross section with a variety of screen arrangements.… more
Date: June 26, 1947
Creator: Schubauer, G. B. & Spangenberg, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Slot-Entry Skirt Extensions on Aerodynamic Characteristics of a Wing Section of the XB-36 Airplane Equipped with a Double Slotted Flap

Description: "An investigation was made in the Langley two-dimensional low-turbulence tunnel on a wing section for the XB-36 airplane equipped with a double slotted flap to determine the effect on lift and drag of various slot-entry skirt extension. A skirt extension of 0.787 deg. was found to provide the best combination of high maximum lift with flap deflected and law drag with flap retracted. The data showed that the maximum lift at intermediate (20 deg. to 45 deg.) flap deflections was lowered considera… more
Date: June 30, 1947
Creator: Cahill, Jones F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000

Description: Wind-tunnel investigations were made in pitch and yaw with and without split flaps. Presence of the fuselage had negligible effect on values of maximum lift coefficient and slope of lift curve, but caused a destabilizing shift in the rate of change of pitching moment with lift. Effects of fuselage position on drag characteristics were small for wings without flaps, but were appreciable when split flaps were on.
Date: June 10, 1947
Creator: Salmi, Reino J.; Conner, D. William & Graham, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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