21 Matching Results

Search Results

Secondary Flows in Annular Cascades and Effects on Flow in Inlet Guide Vanes

Description: Qualitative discussion is presented of the general nature of secondary flows in stationary annular cascades with thin wall boundary layers and radial design variation of circulation. Deviations from ideal mean outlet flows (based on blade-element performance) exist in potential-flow region of vanes because of conditions imposed by end-wall boundaries, displacement of wall boundary layers toward blade suction surfaces, and irrotationality requirement. As a consequence of existence of nonuniform radial flow across blade spacing, it may not generally be possible to obtain an arbitrarily specified design variation of the turning angle along the radial height of a blade row.
Date: August 24, 1951
Creator: Lieblein, Seymour & Ackley, Richard H.
Partner: UNT Libraries Government Documents Department

Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 3: Static Stability With Twin Vertical Fins

Description: "Low-speed wind-tunnel tests were made of a triangular wing with two arrangements of twin vertical fins. With these twin fins mounted either symmetrically or wholly above the wing chord plane, approximately constant effectiveness in proportion to the fin size was obtained throughout the angle-of-attack range. The addition of these fins, however, resulted in a decrease in maximum lift and a reduction in static longitudinal stability at lift coefficients above 0.4" (p. 1).
Date: August 24, 1948
Creator: Rose, Leonard M.
Partner: UNT Libraries Government Documents Department

Penetration and Duration of Fuel Sprays From a Pump Injection System

Description: "High-speed motion pictures were taken of individual fuel sprays from a pump injection system. The changes in the spray-tip penetration with changes in the pump speed, injection-valve opening and closing pressures, discharge-orifice area, injection-tube length and diameter, and pump throttle setting were measured. The pump was used with and without a check valve" (p. 241).
Date: August 24, 1931
Creator: Rothrock, A. M. & Marsh, E. T.
Partner: UNT Libraries Government Documents Department

Some Effects of Solidity on Turning Through Constant-Thickness Circular-Arc Guide Vanes in Axial Annular Flow

Description: Memorandum presenting an investigation conducted on sheet metal, circular-arc compressor inlet guide vanes in an annular cascade with untapered walls to determine the effect of solidity on turning through a blade row. Guide vanes of 30 and 40 degrees camber were investigated over a range of solidity from 0.5 to 4.0. Results regarding the effect of solidity on turning angle, comparison with two-dimensional methods, application of results, and total-pressure losses are provided.
Date: August 24, 1951
Creator: Mankuta, Harry & Guentert, Donald C.
Partner: UNT Libraries Government Documents Department

Correlation of Analog Solutions With Experimental Sea-Level Transient Data for Controlled Turbine-Propeller Engine, Including Analog Results at Altitudes

Description: Memorandum presenting a satisfactory correlation obtained between experimental sea-level transient data at constant flight speed and solutions from the analog representation. The representation is accomplished by transfer functions formed from a frequency-response analysis, which is then used to compute system response at altitude.
Date: August 24, 1951
Creator: Lazar, James & DeRocher, Wilfred L., Jr.
Partner: UNT Libraries Government Documents Department

Effect of Distribution of Basket-Hole Area on Simulated Altitude Performance of 25 1/2-Inch-Diameter Annular-Type Turbojet Combustor

Description: A simulated altitude performance of a 25 1/2-inch-diameter annular-type turbojet combustor was performed to determine the effect of the distribution of basket-hole area on the altitude operational limits of the engine as imposed by the combustor.Total pressure drop was recorded, as well as the effect of fuel-nozzle flow capacity,and fuel-nozzle spray angle for one basket configuration. General observations were made for all configurations regarding flames, extent of afterburning, and durability of the baskets.
Date: August 24, 1948
Creator: Olson, Walter T. & Schroeter, Thomas T.
Partner: UNT Libraries Government Documents Department

Investigation of effect of increased diffusion of rotor-blade suction-surface velocity on performance of transonic turbine

Description: Report presenting the results of an experimental investigation of a transonic turbine designed for a diffusion parameter of 0.30. The experimental performance of the turbine is compared with the experimental performance obtained for another transonic turbine designed for a diffusion parameter of 0.15. Results regarding the overall performance, survey investigation, and loss patterns are provided.
Date: August 24, 1954
Creator: Wong, Robert Y.; Monroe, Daniel E. & Wintucky, William T.
Partner: UNT Libraries Government Documents Department

Interpretation of boundary-layer pressure-rake data in flow with a detached shock

Description: From Summary: "A procedure is presented for determining boundary-layer quantities from pressure-rake data, which include the combined effects of viscous and shock losses. The problem is analyzed using schileren photographs of the shock configuration, the continuity of mass relationship, and the characteristics of the turbulent boundary layer that its outer edge is defined by a rapid change in slope in the Mach-number profiles in the vicinity of the edge."
Date: August 24, 1950
Creator: Luidens, Roger W. & Madden, Robert T.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of a Modified 1/20-Scale Model of the Convair MX-1554 Airplane at Mach Numbers of 1.41 and 2.01

Description: Report presenting an investigation of a model of the Convair MX-1554 airplane in the 4- by 4-foot supersonic pressure tunnel to evaluate the effects of extending the length of the fuselage afterbody and to provide longitudinal and lateral stability and control data. Results indicated that extension of the fuselage afterbody length caused little change in the minimum longitudinal force coefficient and drag due to lift.
Date: August 24, 1953
Creator: Hilton, John H., Jr. & Palazzo, Edward B.
Partner: UNT Libraries Government Documents Department

Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings

Description: Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.
Date: August 24, 1948
Creator: Amer, Kenneth B.
Partner: UNT Libraries Government Documents Department

Investigation of the I-40 jet-propulsion engine in the Cleveland altitude wind tunnel 1: performance and windmilling drag characteristics

Description: Report presenting the performance characteristics of the I-40 jet propulsion engine and an analysis for a range of altitudes and ram pressure ratios. Results regarding the component efficiencies, engine performance, generalizing factors, and windmilling drag characteristics are provided.
Date: August 24, 1948
Creator: Gendler, Stanley L. & Koffel, William K.
Partner: UNT Libraries Government Documents Department

Theory of self-excited mechanical oscillations of helicopter rotors with hinged blades

Description: Vibrations of rotary-wing aircraft may derive their energy from the rotation of the rotor rather than from the air forces. A theoretical analysis of these vibrations is described and methods for its application are explained in Chapter one. Chapter two reports the results of an investigation of the mechanical stability of a rotor having two vertically hinged blades mounted upon symmetrical supports, that is, of equal stiffness and mass in all horizontal directions. Chapter three presents the theory of ground vibrations of a two-blade helicopter rotor on anisotropic flexible supports.
Date: August 24, 1956
Creator: Coleman, Robert P. & Feingold, Arnold M.
Partner: UNT Libraries Government Documents Department

Longitudinal Stability and Control With Special Reference to Slipstream Effects

Description: Report presents the results of a study of data obtained in the NACA full-scale wind tunnel concerning the effects of interference and of propeller operation on longitudinal stability and control. The data include pitching moments for various power conditions for airplanes with tails removed and with tails set at various stabilizer and elevator angles. A number of surveys of the dynamic pressure and the flow direction in the region of the horizontal tail surface are also included.
Date: August 24, 1939
Creator: Katzoff, S.
Partner: UNT Libraries Government Documents Department

A Study of the Radiation From Laminar and Turbulent Open Propane-Air Flames as a Function of Flame Area, Equivalence Ratio, and Fuel Flow Rate

Description: Report presenting radiation measurements on open propane-air flames to find the extent to which radiant flux intensity can be used to measure the surface area of flames. Turbulent burning velocities calculated using this method and the average surface method are compared. Results regarding the laminar flame intensity measurements at different flow rates and equivalence ratios, filter intensity-ratio method, and surface intensity variations in the flames are provided.
Date: August 24, 1954
Creator: Clark, Thomas P. & Bittker, David A.
Partner: UNT Libraries Government Documents Department

Investigation of performance of Bumblebee 18-inch ram jet with a can-type flame holder

Description: Report presenting the results of an investigation in the altitude wind tunnel to determine the performance of a Bumblebee 18-inch ram jet equipped with a can-type flame holder. Results regarding the ramjet combustion performance and ramjet overall performance are provided.
Date: August 24, 1948
Creator: Sterbentz, W. H. & Nussdorfer, T. J.
Partner: UNT Libraries Government Documents Department

An apparatus for varying effective dihedral in flight with application to a study of tolerable dihedral on a conventional fighter airplane

Description: From Summary: "An apparatus for varying effective dihedral in flight by means of servo actuation of the ailerons in response to sideslip angle is described. The results of brief flight tests of the apparatus on a conventional fighter airplane are presented and discussed. The results of an investigation employing the apparatus to determine the tolerable (safe for normal fighter operation) range of effective dihedral on the test airplane are presented."
Date: August 24, 1949
Creator: Kauffman, William M.; Liddell, Charles J., Jr.; Smith, Allan & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Experimental determination of aerodynamic forces normal to the chord due to rotating stall acting on compressor blading

Description: Report presenting an investigation conducted on an NACA axial-flow single-stage compressor with a 14-inch diameter and a 0.9 hub-tip ratio to determine the magnitude of the blade force variation due to the flow fluctuations caused by rotating stall. Results regarding steady-state blade forces, shapes of steady-state force curves, time variation in weight flow, oscillograms of strain-gage output, and effect of damping are provided.
Date: August 24, 1954
Creator: Johnson, Donald F. & Costilow, Eleanor L.
Partner: UNT Libraries Government Documents Department

Effect of Retractable Ignition Plug on Plug Fouling by Carbon Deposits

Description: Memorandum presenting an investigation conducted using a single combustor from a 4600-pound-thrust turbojet engine to determine if ignition-plug fouling by carbon deposits could be prevented by retracting the plug from the combustion zone during operation after ignition had taken place. The fuels used were normally conducive to forming carbon. The results indicated that retracting the ignition plug from the combustion zone after ignition prevented plug fouling by carbon.
Date: August 24, 1950
Creator: Wear, Jerrold D. & Locke, Theodore E.
Partner: UNT Libraries Government Documents Department

Effect of an Increase in Hull Length-Beam Ratio From 15 to 20 on the Hydrodynamic Characteristics of Flying Boats

Description: Report presenting an investigation of the effect of hull length-beam ratio on the hydrodynamic characteristics of flying boats that extend to a length-beam ratio of 20. The results are compared with flying boats having a length-beam ratio of 15. Results regarding longitudinal stability, spray characteristics, take-off performance, taxiing and take-off behavior in waves, landing behavior in waves, and a summary chart are provided.
Date: August 24, 1949
Creator: Carter, Arthur W. & Whitaker, Walter E., Jr.
Partner: UNT Libraries Government Documents Department

Damping in Roll of Rectangular Wings of Several Aspect Ratios and Naca 65a-Series Airfoil Sections of Several Thickness Ratios at Transonic and Supersonic Speeds as Determined With Rocket-Powered Models

Description: Report presenting rocket-powered flight tests to determine the damping in roll of rectangular wings of various aspect ratios and thickness ratios using NACA airfoil sections. The experimental damping in roll was consistently lower than what was predicted theoretically.
Date: August 24, 1950
Creator: Edmondson, James L.
Partner: UNT Libraries Government Documents Department

Investigation of the I-40 Jet-Propulsion Engine in the Cleveland Altitude Wind Tunnel 1: Performance and Windmilling Drag Characteristics

Description: Report presenting the performance characteristics of the I-40 jet-propulsion engine for a range of altitudes and ram pressure ratios. Results regarding component efficiencies, engine performance, generalizing factors, and windmilling drag characteristics are provided.
Date: August 24, 1948
Creator: Gendler, Stanley L. & Koffel, William K.
Partner: UNT Libraries Government Documents Department