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Aerodynamic Design of Axial-Flow Compressors: Volume 1

Description: Compendium presenting a comprehensive integration of available aerodynamic design information on axial-flow compressors. The subjects of the first volume of this investigation are objectives and scope, compressor design requirements, compressor design system, potential flow in two-dimensional cascades, and viscous flow in two-dimensional cascades.
Date: August 1, 1956
Creator: Members of the Compressor and Turbine Research Division
Partner: UNT Libraries Government Documents Department
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Aerodynamic Design of Axial-Flow Compressors, Volume 2

Description: "Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss" (p. 1).
Date: August 1, 1956
Creator: Members of the Compressor and Turbine Research Division
Partner: UNT Libraries Government Documents Department
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Aerodynamic design of axial-flow compressors: Volume 3

Description: Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimension… more
Date: August 1, 1956
Creator: Johnsen, Irving A.; Bullock, Robert O.; Graham, Robert W.; Costilow, Eleanor L.; Huppert, Merle C.; Benser, William A. et al.
Partner: UNT Libraries Government Documents Department
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Analysis of laminar incompressible flow on semiporous channels

Description: From Introduction: "Experimental results for flow in a rectangular channel with injection through a porous wall are given in reference 1. As part of the study to guide future experiments, laminar flow in a semiporous channel is investigated herein. In the present investigation, a third-order perturbation solution for laminar incompressible flow in a semiporous channel is presented."
Date: August 1956
Creator: Donoughe, Patrick L.
Partner: UNT Libraries Government Documents Department
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An Analytic Study of Turbojet Engine Thrust Augmentation With Liquid Hydrogen, Pentaborane, Magnesium Slurry, and JP-4 Afterburner Fuels and a 220-Second Impulse Rocket

Description: Memorandum presenting a computation and comparison of the thrust augmentation and accompanying total fuel flow for four afterburner fuels and a rocket. Four turbojet engines burning JP-4 primary fuel and several operating conditions were selected for the analyses.
Date: August 15, 1956
Creator: Morris, James F.
Partner: UNT Libraries Government Documents Department
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The Appearance of a Boric Oxide Exhaust Cloud From a Turbojet Engine Operating on Trimethylborate Fuel

Description: Memorandum presenting an investigation conducted on the size and density of the boric oxide exhaust cloud from a J47-25 turbojet engine operating on trimethyl-borate fuel at sea-level static conditions. Movies and still photographs were taken from the ground and from a helicopter. Results regarding the visual observation and oxide fallout and concentration are provided.
Date: August 10, 1956
Creator: Lord, Albert M. & Kaufman, Warner B.
Partner: UNT Libraries Government Documents Department
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Attenuation in a Shock Tube Due to Unsteady-Boundary-Layer Action

Description: "A method is presented for obtaining the attenuation of a shock wave in a shock tube due to the unsteady boundary layer along the shock-tube walls. It is assumed that the boundary layer is thin relative to the tube diameter and induces one-dimensional longitudinal pressure waves whose strength is proportional to the vertical velocity at the edge of the boundary layer. The contributions of the various regions in a shock tube to shock attenuation are indicated" (p. 1).
Date: August 1956
Creator: Mirels, Harold
Partner: UNT Libraries Government Documents Department
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Boundary-layer transition at supersonic speeds

Description: "Recent results of the effects of Mach number, stream turbulence, leading-edge geometry, leading-edge sweep, surface temperature, surface finish, pressure gradient, and angle of attack on boundary-layer transition are summarized. Factors that delay transition are nose blunting, surface cooling, and favorable pressure gradient. Leading-edge sweep and excessive surface roughness tend to promote early transition. The effects of leading-edge blunting on two-dimensional surfaces and surface cooling … more
Date: August 3, 1956
Creator: Low, George M.
Partner: UNT Libraries Government Documents Department
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Calculations of the flow over an inclined flat plate at free-stream Mach number 1

Description: Report presenting a numerical solution of the complete equations of inviscid compressible flow for the case of an inclined flat plate at free-stream Mach number 1. The results for the flow field show that the large changes of velocity that occur near the leading edge are confined to a surprisingly small part of the field. Results regarding the flow field and pressure distribution are provided.
Date: August 1956
Creator: Vincenti, Walter G.; Wagoner, Cleo B. & Fisher, Newman H., Jr.
Partner: UNT Libraries Government Documents Department
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Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Note presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: August 1956
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Partner: UNT Libraries Government Documents Department
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Comparison of flight and wind-tunnel measurements of high-speed-airplane stability and control characteristics

Description: Report presenting a comparison of wind-tunnel and flight-measured values of stability and control characteristics. Generally, wind tunnels were found to predict all trends of characteristics reasonably well, but there are differences in parameters for certain values.
Date: August 1956
Creator: Williams, Walter C.; Drake, Hubert M. & Fischel, Jack
Partner: UNT Libraries Government Documents Department
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Compressibility Factor, Density, Specific Heat, Enthalpy, Entropy, Free-Energy Function, Viscosity, and Thermal Conductivity of Steam

Description: Note presenting tables of thermal properties of stream that have been prepared in an NBS-NACA series. They include, for real gas, the compressibility factor, the density, the specific heat at constant pressure, the enthalpy, the entropy, the free-energy function, the viscosity, and the thermal conductivity.
Date: August 1956
Creator: Fano, Lilla; Hubbell, John H. & Beckett, Charles W.
Partner: UNT Libraries Government Documents Department
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Compressive and Torsional Buckling of Thin-Wall Cylinders in Yield Region

Description: Note presenting a general set of equilibrium differential equations for the plastic buckling of cylinders, which are based on assumptions that have led to the best agreement between theory and test data on inelastic buckling of flat plates. Test data are presented which indicate satisfactory agreement with the theoretical plasticity-reduction factors in most cases. Some of the topics addressed include compressive buckling and torsional buckling.
Date: August 1956
Creator: Gerard, George
Partner: UNT Libraries Government Documents Department
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Concluding Report on Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

Description: "An investigation has been completed in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine its spin and recovery characteristics. An interim report, Research Memorandum SL55G20, was published earlier and the present report concludes the presentation of results of the investigation. Primarily, the present report presents results obtained with engine gyroscopic moments simulated on the model. Also, the current results were obtained with a re… more
Date: August 14, 1956
Creator: Bowman, James S., Jr.
Partner: UNT Libraries Government Documents Department
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Effect of Design Over-All Compressor Pressure Ratio Division on Acceleration Characteristics of Three Hypothetical Two-Spool Turbojet Engines

Description: The engines, each with a compressor overall total-pressure ratio of 12 and a design inner-turbine-inlet temperature of 2500 degrees R, were investigated at static sea-level conditions to determine the effect on transient performance of varying the desitn pressure ratio divisions 2-6, 3-4, and 4-3 between the outer and inner compressors. The transient considered was an acceleration from 40 to 100 percent design thrust. When the outer compressor of each engine reached design speed, the inner comp… more
Date: August 20, 1956
Creator: Filippi, Richard E. & Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
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Effects of external stores on the static longitudinal aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations on the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Results regarding accuracy and remarks on effects of stores are provided.
Date: August 23, 1956
Creator: Foster, Gerald V. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department
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Effects of Intermittent Versus Continuous Heating upon the Tensile Properties of 2024-T4, 6061-T6 and 7075-T6 Alloys

Description: In some applications, aluminum alloys are subjected to intermittent heating at elevated temperature. It is generally considered that the effects of such intermittent heating are cumulative, and therefore are the same as if the heating had been continuous for the same total length of time. The object of these tests was to determine the effects of intermittent and continuous heating at 300 and 400 F, for total periods of 100 and 200 hr, upon the tensile properties of 2024-T4 and 6061-T6 alloy rol… more
Date: August 1956
Creator: Stickley, G. W. & Anerson, H. L.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 3: blade-element and over-all performance at three solidity levels

Description: Report presenting two low-solidity configurations tested to provide data on the effects of solidity on overall and blade-element performance. Results regarding weight flow, pressure ratio, and efficiency, stall characteristics, rotor-inlet conditions, total-pressure ratio, work coefficient, and efficiency are provided.
Date: August 17, 1956
Creator: Tysl, Edward R. & Schwenk, Francis C.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of air-cooled turbine rotor blade temperatures in a turbojet engine operating at turbine-inlet temperatures up to 2580 R and altitudes of 50,000 and 60,000 feet

Description: Report presenting temperature data for air-cooled turbine rotor blades obtained during an experimental investigation conducted in an altitude test chamber to determine some of the problems pertinent to the operation of air-cooled turbojet engines at a range of turbine-inlet temperatures. Results regarding local blade temperatures, effect of blade-inlet cooling-air temperature on average rotor blade temperature with two types of cooling, effect of cooling-air flow on average rotor blade temperat… more
Date: August 20, 1956
Creator: Slone, Henry O.; Cochran, Reeves P. & Dengler, Robert P.
Partner: UNT Libraries Government Documents Department
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Fatigue-Crack Propagation in Aluminum Alloy Box Beams

Description: Report presenting fatigue testing of eighteen box beams constructed according to four designs in order to study fatigue-crack propagation and accompanying stress redistribution. Two designs had stiffeners riveted to the cover, one had stiffeners bonded to the cover, and one had an integrally stiffened cover machined from a plate. Results regarding crack initiation, crack propagation, and stress distribution are provided.
Date: August 1956
Creator: Hardrath, Herbert F.; Leybold, Herbert A.; Landers, Charles B. & Hauschild, Louis W.
Partner: UNT Libraries Government Documents Department
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The Fatigue Strength of Riveted Joints and Lugs

Description: This report deals with a number of tests on riveted joints and lugs for the primary purpose of comparing the several types of riveted joints and to study the effect of various factors on the fatigue strength of lugs. A check was made to ascertain whether or not an estimate of the fatigue life at a certain loading could be made from the dimensions of the joint and the fatigue data of the unnotched materials. Recommendations are made on the proportioning of joints to obtain better fatigue behavio… more
Date: August 1956
Creator: Schijve, J.
Partner: UNT Libraries Government Documents Department
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Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department
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