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Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with bypasses discharging in an axial direction

Description: Report presenting an investigation of an axially symmetric nacelle-type conical spike inlet with two bypasses located in the horizontal plane and on opposite sides of the nacelle in the 8- by 6-foot supersonic tunnel at several Mach numbers and angles of attack. Results regarding the performance with open bypasses and with closed bypasses are provided.
Date: January 30, 1953
Creator: Allen, J. L. & Beke, Andrew
Partner: UNT Libraries Government Documents Department
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Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Description: Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.
Date: January 30, 1958
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department
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Comparison of performance of experimental and conventional cage designs and materials for 75-millimeter-bore cylindrical roller bearings at high speed

Description: From Summary: "The results of two investigations, one to determine the relative merits of four experimental and two conventional design 75-millimeter-bore (size 215) cylindrical roller bearings and one to determine the relative merits of nodular iron and bronze as cage materials for this size and type of bearing, are presented in this report. Nine test bearings were operated over a range of dn values (product of bearing bore in mm and shaft speed in r.p.m) from 0.3 x 10(6) to 2.3 x 20(6), radia… more
Date: June 30, 1954
Creator: Anderson, William J.; Macks, E. Fred & Nemeth, Zolton N.
Partner: UNT Libraries Government Documents Department
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Flight and Wind-Tunnel Investigation to Determine the Aileron-Vibration Characteristics of 1/4-Scale Wing Panels of the Douglas D-558-2 Research Airplane

Description: Report presenting a flight and wind-tunnel investigation to determine the aerodynamic vibration characteristics of ailerons for the Douglas D-558-2 airplane. Testing was conducted to investigate the possibilities of a single-degree-of-freedom flutter known as aileron "buzz" or aileron compressibility flutter. Results regarding the three types of aileron vibration observed and vibration amplitudes are provided.
Date: November 30, 1948
Creator: Angle, Ellwyn E. & Lundstrom, Reginald R.
Partner: UNT Libraries Government Documents Department
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A Summary and Analysis of Wind-Tunnel Data on the Lift and Hinge-Moment Characteristics of Control Surfaces Up to a Mach Number of 0.90

Description: Report presenting an extensive collection of lift and hinge-moment characteristics of control surfaces up to a Mach number of 0.90 in a high-speed wind tunnel. A wide variety of control-surface profiles, plan forms, and aerodynamic balances are included. Results regarding elevator hinge moments and longitudinal control, aileron hinge moments and lateral control, control-surface characteristics, and transonic flutter are highlighted.
Date: April 30, 1948
Creator: Axelson, John A.
Partner: UNT Libraries Government Documents Department
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Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination

Description: Report presenting an exploratory study of the screaming tendency of the gaseous-hydrogen-liquid-oxygen propellant combination in 200-pound-thrust rocket engines. Four injector classes in a total of 12 different configurations were tested in a variety of chamber lengths over the usable mixture-ratio range. Results regarding acoustic oscillations, unclassified oscillations, driving and damping mechanisms, and effects of screaming on heat transfer are provided.
Date: September 30, 1958
Creator: Baker, Louis, Jr. & Steffen, Fred W.
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Description: From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbe… more
Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D.
Partner: UNT Libraries Government Documents Department
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Effect of Fuel Volatility on Performance of Tail-Pipe Burner

Description: Fuels having Reid vapor pressures of 6.3 and 1.0 pounds per square inch were investigated in a tail-pipe burner on an axial-flow-type turbojet engine at a simulated flight Mach number of 0.6 and altitudes from 20,000 to 45,000 feet. With the burner configuration used in this investigation, having a mixing length of only 8 inches between the fuel manifold and the flame holder, the low-vapor-pressure fuel gave lower combustion efficiency at a given tail-pipe fuel-air ratio. Because the exhaust-no… more
Date: April 30, 1951
Creator: Barson, Zelmar & Sargent, Arthur F., Jr.
Partner: UNT Libraries Government Documents Department
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Performance of J-33-A-21 Turbojet-Engine Compressor I - Over-All Performance Characteristics at Equivalent Impeller Speeds from 6000 to 13,400 RPM

Description: "The NACA is investigating a series of J-33 turbojet-engine compressors to determine the over-all and component performances and to improve theories of flow through large centrifugal compressors, The production model J-33-A-21 was operated over a range of inlet temperatures from 80 to -40 F and inlet pressures from 14 to 5 inches mercury absolute for equivalent impeller speeds from 6000 to 13,400 rpm. At the equivalent design speed of 11,500 rpm, the compressor had a peak pressure ratio of 3.98… more
Date: March 30, 1948
Creator: Beede, William L.; Kovach, Karl & Creagh, John W. R.
Partner: UNT Libraries Government Documents Department
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Off-Design Performance of Divergent Ejectors

Description: Report presenting an investigation of the off-design performance of fixed- and variable-geometry divergent ejectors. Results regarding fixed geometry and low secondary flow, fixed geometry and high secondary flow, variable geometry and low secondary flow, variable geometry and high secondary flow, and ejectors with full afterburning are provided.
Date: September 30, 1958
Creator: Beheim, Milton A.
Partner: UNT Libraries Government Documents Department
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Off-Design Performance of Divergent Ejectors

Description: "The off-design performance of fixed- and of variable-geometry divergent ejectors was investigated. The ejectors, which were designed for turbojet operation at Mach 3, were investigated in the Mach number range of 0.8 to 2. The performance of a fixed-geometry ejector with high secondary-flow rates was competitive with that of more complex variable-geometry ejectors. Variable-geometry ejectors with compromises to reduce mechanical complexity produced performance reasonably close to that of an id… more
Date: September 30, 1958
Creator: Beheim, Milton A.
Partner: UNT Libraries Government Documents Department
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Spin-Tunnel Investigation of the Jettisoning of External Fuel Tanks in Spins

Description: "A spin-tunnel investigation has been made to determine the probability of external fuel tanks striking an airplane after being jettisoned in a spin. The investigation showed that for straight-wing fighter-type designs in any case in which jettisoning of tanks in a spin might aid spin recovery the tanks would probably clear all parts of the airplane" (p. 1).
Date: November 30, 1949
Creator: Berman, Theodore
Partner: UNT Libraries Government Documents Department
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Transonic Investigation of an Axial-Flow Compressor Rotor With a Hub-Tip Ratio of 0.75 and Blades Having NACA A(Sub 2)I(Sub 8b) Mean Lines

Description: Report presenting a blade-element analysis of a compressor rotor with blade sections with NACA A(sub 2)I(Sub 8b) mean lines and 65-series thickness distributions in Freon-12 gas. Results regarding blade loss, angle of attack associated with minimum loss, peak efficiencies, and comparison with other transonic rotors are provided.
Date: September 30, 1957
Creator: Bernot, Peter T. & Savage, Melvyn
Partner: UNT Libraries Government Documents Department
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Exploratory Investigation of the Flow in the Separated Region Ahead of Two Blunt Bodies at Mach Number 2

Description: Memorandum presenting an investigation of flow separation from a flat plate ahead of two blunt two-dimensional bodies in detail at Mach number 2. Interferograms were obtained for the separated regions, and the pitot-pressure distribution and flow directions were surveyed in one of the regions. Results regarding recovery factors and static pressures, density, total pressure, Mach number distribution, and flow-direction survey are provided.
Date: June 30, 1955
Creator: Bernstein, Harry & Brunk, William E.
Partner: UNT Libraries Government Documents Department
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Preliminary Internal Performance Data for a Variable-Ejector Assembly on the XJ79-GE-1 Turbojet Engine, 2, Afterburning Configurations

Description: Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in two representative after-burning positions. Jet-thrust and air-handling data were obtained in quiescent air for 4 selected ejector configurations over a wide range of secondary to primary airflow ratios and primary-nozzle pressure ratios. The experimental ejector data are presented in both graphical and tabulated form.
Date: July 30, 1957
Creator: Bloomer, Harry E. & Groesbeck, Donald E.
Partner: UNT Libraries Government Documents Department
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Preliminary Altitude Performance Characteristics of the J57-P-1 Turbojet Engine with Fixed-Area Exhaust Nozzle

Description: An investigation to determine the altitude performance of the J57-P-1 turbojet engine and components was conducted at the NACA Lewis altitude wind tunnel. Data were obtained over a corrected inboard rotor speed range from 56 to 106 percent of rated speed, with intercompressor bleeds both open and closed, at altitudes from 15,000 to 50,000 feet and at a flight Mach number of 0.81. The corresponding range of Reynolds number indices was from 0.858 to 0.213. All data presented were obtained with a … more
Date: April 30, 1954
Creator: Bloomer, Harry E. & Miller, Robert R.
Partner: UNT Libraries Government Documents Department
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Calculated Reactivity of Uranyl-Fluoride - Water Criticality Experiments

Description: Memorandum presenting a modified group method used to calculate the reactivity of the uranyl-fluoride-water experimental critical assemblies which are part of the Oak Ridge critical mass studies. The method relates the experimental slowing-down length for water to that in fluoride solutions and includes the effects of epithermal absorption and fission.
Date: March 30, 1956
Creator: Bogart, Donald & Soffer, Leonard
Partner: UNT Libraries Government Documents Department
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Surface-Pressure Distributions on a Systematic Group of NACA 1-Series Cowlings With and Without Spinners

Description: "A method for calculating the flow fields of axially symmetric bodies from their pressure distributions is reported in NACA RM No. L8I17. In order to facilitate application of this method to the important case of the cowling-spinner combination, for use in the design of propellers, the present paper presents static-pressure distributions on the tops of 79 high-critical-speed NACA 1-series cowling-spinner combinations over wide ranges of inlet-velocity ratio at angles of attack of 0 degrees, 2 d… more
Date: November 30, 1948
Creator: Boswinkle, Robert W., Jr. & Keith, Arvid L., Jr.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Effect of Entrance Width-to-Height Ratio on the Performance of an Auxiliary Scoop-Type Inlet at Mach Numbers From 0 to 1.3

Description: Memorandum presenting an investigation of variable-area auxiliary inlets intended to provide for the variation of engine air requirements with speed and altitude. Three auxiliary scoop inlets were tested in combination with a nose inlet at a range of Mach numbers tested at zero angle of attack.
Date: July 30, 1953
Creator: Brajnikoff, George B. & Stroud, John F.
Partner: UNT Libraries Government Documents Department
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Experimental and theoretical studies of area suction for the control of the laminar boundary layer on an NACA 64A010 airfoil

Description: From Summary: "A low-turbulence wind-tunnel investigation was made of an NACA 64A010 airfoil having a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of suction to produce continuous inflow through the surface of the airfoil (area suction). In addition to the experimental investigation, a related theoretical analysis was made to provide a basis of comparison for the test results."
Date: March 30, 1951
Creator: Braslow, Albert L.; Burrows, Dale L.; Tetervin, Neal & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department
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Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration With a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers From 1.2 to 2.1

Description: Report presenting flight testing of a rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Results regarding the lift coefficient, dynamic stability, static stability, control effectiveness, and drag are provided.
Date: September 30, 1957
Creator: Brown, Clarence A., Jr.
Partner: UNT Libraries Government Documents Department
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Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration With a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers From 1.2 to 2.1

Description: Report presenting testing of a full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Static and dynamic longitudinal stability and control derivatives were determined at low angles of attack and for a range of Mach numbers.
Date: September 30, 1957
Creator: Brown, Clarence A., Jr.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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