National Advisory Committee for Aeronautics (NACA) - 412 Matching Results

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Effect of fuel-orifice diameter on performance of heptane-oxygen rocket-engines

Description: A study of the effect of fuel-orifice diameter on the performance of heptane-oxygen rocket engines with single-element injectors. Five engines with a range of thrust were tested with parallel-sheet, triplet, and parallel-jet injectors. Decreasing the fuel-orifice diameter was found to increase the performance for a fixed chamber length. Results regarding injector performance and a comparison of experimental and analytical results are provided.
Date: February 25, 1958
Creator: Priem, Richard J. & Hersch, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Elevated-Temperature Combined Stress-Rupture Plus Fatigue Strength of Waspaloy Having Different Aging Treatments and/or Molybdenum Contents

Description: Report presenting an investigation to determine if the combined stress-rupture plus fatigue strengths of three groups of Waspaloy with different aging treatments and/or molybdenum contents could be correlated with their stress-rupture ductilities and notch-rupture strengths. Waspaloy is of interest as a gas turbine-bucket alloy because it has low strategic material content and relatively good stress-rupture properties. Results regarding metallurgical evaluation of the failed specimens are also … more
Date: February 25, 1958
Creator: Hoffman, C. A. & Hornak, M. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Study of the Effect of Boric Oxide Deposits on the Performance of Two Selected Turbine Stator-Blade Shapes

Description: Report discussing testing on the performance of two stator-blade shapes with and without boric oxide deposits. The deposits were found to cause total pressure losses and decreases in the blade-exit flow angle. Information about the cascade throat area, boundary-layer momentum thickness, total pressure ratio, and exit flow angle and tangential component of velocity is provided.
Date: February 25, 1958
Creator: Setze, Paul C. & Nusbaum, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A preliminary study of the effect of boric oxide deposits on the performance of two selected turbine stator-blade shapes

Description: Report presenting the performance of two stator-blade shapes with and without boric oxide deposits, which was determined in a two-dimensional cascade. The differences between the blades were the amount of curvature and suction-surface diffusion downstream of the throat. Results regarding the cascade throat area, boundary-layer momentum thickness, total-pressure ratio, and exit flow angle and tangential component of velocity.
Date: February 25, 1958
Creator: Setze, Paul C. & Nusbaum, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-Oxygen Mixtures Assuming Equilibrium Composition

Description: "Theoretical rocket performance for equilibrium composition during expansion was calculated for JP-4 fuel with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity… more
Date: February 25, 1958
Creator: Gordon, Sanford
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Behavior of Some Materials and Shapes in Supersonic Free Jets at Stagnation Temperatures Up to 4,210 Degrees F, and Descriptions of the Jets

Description: Report presenting testing of a number of materials and shapes in two supersonic free jets at stagnation temperatures of up to 4,210 degrees Fahrenheit. Some testing was conducted in a supersonic chemical jet and some was conducted in a ceramic-heated air jet. Materials tested included aluminum alloy, copper, Inconel, magnesium, mild steel, molybdenum, stainless steel, titanium, alumina, zirconia, graphite, bakelite, and nylon.
Date: February 24, 1958
Creator: Fields, E. M.; Hopko, Russell N.; Swain, Robert L. & Trout, Otto F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-speed landing loads measured on the Douglas X-3 research airplane

Description: Report presenting an investigation of the landing conditions and landing-gear loads on the Douglas X-3 research airplane during routine research flights. Results regarding the vertical-flight profiles, oscillograph records, time histories of landing-gear loads and airplane center-of-gravity normal accelerations, and peak drag load are provided.
Date: February 24, 1958
Creator: Marcy, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of supersonic store interference in the vicinity of a 22 degree swept-wing-fuselage configuration at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation in the supersonic pressure tunnel at Mach numbers 1.61 and 2.01 in which separate forces and moments were measured on a store (with five components), on a 22 degree swept wing (three components), and on a 22 degree swept-wing-fuselage combination (three components) for a range of store positions.
Date: February 24, 1958
Creator: Geier, Douglas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests

Description: Memorandum presenting the buffet characteristics of a scale model of an attack airplane over a range of Mach numbers. The wing had a modified delta plan form with an NACA 0008 airfoil section at the root and an NACA 0005 airfoil section at the tip, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding the frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet inpu… more
Date: February 21, 1958
Creator: Davis, Don D., Jr. & Wornom, Dewey E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests

Description: Report presenting an investigation of the buffet characteristics of a model of an attack airplane at a variety of Mach numbers. The wing had a modified delta plan form with two NACA airfoils, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet input force are provided.
Date: February 21, 1958
Creator: Davis, Don D., Jr. & Wornom, Dewey E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tabulated pressure data for a 60 degree delta-wing-body-tail model with a hot jet exhausting from a pylon-mounted nacelle

Description: Report presenting an investigation in the 16-foot transonic tunnel at a variety of Mach numbers to determine the interference effects of a hot jet exhaust on the pressure distribution of a 60 degree delta wing. Results regarding the tabulated pressure coefficients for the wing and nacelle for the complete range of test conditions are provided.
Date: February 21, 1958
Creator: Lee, Edwin E., Jr. & Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Load Distribution on a 45 Degree Sweptback Wing With Leading-Edge Chord-Extensions at Transonic Speeds, Including Effects of a Spoiler-Slot-Deflector Aileron

Description: Report discussing the aerodynamic loading characteristics of a 45 degree sweptback wing with leading-edge chord extensions, including the effects of a spoiler-slot-deflector aileron. The wing section loading, wing-panel loading, and chord-extension loading are described.
Date: February 20, 1958
Creator: Schmeer, James W.; Whitcomb, Charles F. & West, F. E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation at Mach Numbers From 0.8 to 1.5 of the Effect of a Fuselage Indentation on the Zero-Lift Drag of a 52.5 Degree Sweptback-Wing-Body Configuration With Symmetrically Mounted Stores on the Fuselage

Description: Memorandum presenting two rocket-propelled models flight tested at Mach numbers from 0.8 to 1.5 to determine the effect of a fuselage indentation on the drag of a 52.5 degree sweptback-wing-body configuration with two large strut-mounted store symmetrically located above and below the fuselage. The fuselage had a symmetrical, Mach number 1.0 indentation designed to cancel the wing area normal to the plane of symmetry. Results regarding total drag and pressure drag are provided.
Date: February 20, 1958
Creator: Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-flight transonic model investigation of jet effects on a fighter-type configuration employing a tail boom and three horizontal-tail positions

Description: Report presenting the results of a limited research program initiated to study the effects of a hot propulsive jet on the longitudinal stability characteristics of a fighter-type airplane configuration. The data was obtained from a rocket-boosted free-flight model investigation over a range of Mach numbers using four models that differed only in the position and size of the horizontal tail. Results regarding the time histories, trim, normal force, pitching moment, aerodynamic-center location, d… more
Date: February 20, 1958
Creator: Jackson, Bruce G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Limited investigation of noise suppression by injection of water into exhaust of afterburning jet engine

Description: Report presenting an analysis of the injection of water into the jet-engine exhaust in order to suppress noise during static ground operation of jet engines. The investigation is conducted with a simple rig which pumps high-pressure water into the exhaust of an afterburning jet engine. Results regarding the overall sound-pressure levels and frequency spectra of the noise are provided.
Date: February 20, 1958
Creator: Kurbjun, Max C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Wind-Tunnel Investigation of the Effect of Horizontal Tail on Longitudinal Stability of Two 60 Degree Sweptback-Wing-Body Configurations with Aspect Ratios of 2.67 and 4.00

Description: Memorandum presenting an investigation of the effect of a 60 degree sweptback horizontal tail at two vertical locations on the static longitudinal stability of two 60 degree sweptback wing-body configurations with aspect ratios of 2.67 and 4.00 in the 8-foot transonic pressure tunnel. Tests were made at Mach numbers from 0.80 to 1.18 for angles of attack from -3 degrees to about 15 degrees.
Date: February 20, 1958
Creator: Brooks, Joseph D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical investigation of multistage-turbine efficiency characteristics in terms of work and speed requirements

Description: From Introduction: "This report presents an analytical investigation of this aerodynamic interdependence in terms of the effect of variations in the turbine specific work output, blade speed, and stage number on turbine efficiency."
Date: February 18, 1958
Creator: Stewart, Warner L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Forging Temperature and Heat Treatment on the Performance of Inconel 700 Buckets at 1625 Degrees F in a J33-9 Turbojet Engine

Description: Report presenting an investigation to determine the effects of forging temperatures and solution treatments on the engine performance of Inconel 700 buckets. The buckets were tested in a J33-9 turbojet engine at 1625 degrees F in 20-minute cycles. Testing demonstrated that the buckets are capable of operating for more than 450 hours at rated speed.
Date: February 18, 1958
Creator: Gyorgak, C. A.; Springsteen, D. F. & Johnston, J. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Behavior of Pentaborane-Air Combustion Products During Expansion in a Convergent Divergent Nozzle

Description: "In order to evaluate the post combustion behavior of boric oxide, pentaborane-air mixtures, burned to completion at a combustor pressure of 3 atmospheres, were expanded through a 7.1-inch-long convergent-divergent nozzle having a 4-inch-diameter throat and an exit-to-throat area ratio of 1.68. The experimentally determined thrust performance was in good agreement with the ideal equilibrium performance at stagnation temperatures of 3300 deg R and lower. The boric oxide vapor at the combustor ex… more
Date: February 18, 1958
Creator: Branstetter, J. Robert & Setze, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental behavior of pentaborane-air combustion products during expansion in a convergent-divergent nozzle

Description: Report presenting an evaluation of the postcombustion behavior of boric oxide using pentaborane-air mixtures burned to completion at a combustor pressure of 3 atmospheres expanded through a convergent-divergent nozzle. Results regarding the symmetry of flow in nozzle, behavior of liquid boric oxide in nozzle, abrupt condensation phenomena, effect of abrupt condensation on performance, and effect of oxide films are provided.
Date: February 18, 1958
Creator: Branstetter, J. Robert & Setze, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Reynolds number effect on performance of an eight-stage axial-flow research compressor with long- and medium-chord lengths in the two transonic inlet stages

Description: Report presenting an investigation of the Reynolds number effects on an axial-flow compressor with two of the transonic inlet stages doubled as compared to the original compressor. Results regarding the long-chord-compressor performance, effect of Reynolds number on compressor performance, and a comparison of long- and medium-chord compressor performance are provided.
Date: February 18, 1958
Creator: Sievers, Gilbert K.; Geye, Richard P. & Lucas, James G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A method for rapid selection of design characteristics of 1-, 1 1/2-, and 2-stage turbines with optimum annulus taper

Description: Report presenting a method for the rapid selection of a turbine design within specified aerodynamic limits. Tables are provided with the overall design parameters and velocity-diagram variables of each design. Detailed design information is also included for ranges of blade-speed parameter and exit radius ratio.
Date: February 18, 1958
Creator: Yohner, Peggy L. & English, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: longitudinal characteristics of an unswept wing and canard

Description: Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers. The configuration had an unswept wing, an unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. Data are presented for various combinations of the canard, wing, and vertical tail for a range of angles of attack and canard deflection angles.
Date: February 17, 1958
Creator: Peterson, Victor L. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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