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Memorandum on Chemical Reactors and Reactor Hazards

Description: Two important problems in the investigation of reactor hazards are the chemical reactivity of various materials employed in reactor construction and the chracteristics of heat transfer under transient conditions, specifically heat transfer when driven by an exponentially increasing heat source (exp t/T). Although these problems are independent of each other, when studied in relation to reactor hazards they may occur in a closely coupled sequence. For example the onset of a dangerous chemical re… more
Date: July 5, 1951
Creator: Mills, M.M.; Pearlman, H.; Ruebsamen, W. & Steele, G., Chrisney, J.
Partner: UNT Libraries Government Documents Department
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Investigation of altitude ignition, acceleration and steady-state operation with single combustor of J47 turbojet engine

Description: Report describing an investigation conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady-state operating characteristics. Results regarding ignition, acceleration, altitude operational limits, combustion efficiency, and pressure loss are provided.
Date: March 5, 1951
Creator: Cook, William P. & Butze, Helmut F.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of air-cooled turbine blades in turbojet engine 9: evaluation of the durability of noncritical rotor blades in engine operation

Description: The durability of five different structural or cooling configurations or combination of both of air-cooled blades made of noncritical materials was investigated in a modified turbojet engine. The greater part of the investigation was conducted at an engine speed of 11,500 rpm, a turbine-inlet temperature of approximately 1670 degrees F, and a cooling-air to combustion gas flow ratio per blade of 0.05. The results of the investigation indicated that air-cooled blades made of noncritical metals c… more
Date: December 5, 1951
Creator: Stepka, Francis S. & Hickel, Robert O.
Partner: UNT Libraries Government Documents Department
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Comparison of Transonic Characteristics of Lifting Wings From Experiments in a Small Slotted Tunnel and the Langley High-Speed 7- by 10-Foot Tunnel

Description: Report presenting a comparison of the transonic aerodynamic characteristics of unswept and 45 degree sweptback wings in the high-speed tunnel and slotted tunnel. The purpose of the investigation was to explore the possibilities and limitations associated with transonic testing of relatively large wings in a rectangular slotted tunnel. Results regarding lift, pitching moments, drag, bending moments, and Schileren photographs are provided.
Date: November 5, 1951
Creator: Sleeman, William C., Jr.; Klevatt, Paul L. & Linsley, Edward L.
Partner: UNT Libraries Government Documents Department
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Investigation of dynamic characteristics of a turbine-propeller engine

Description: Time constants that characterize engine speed response of a turbine-propeller engine over the cruising speed range for various values of constant fuel flow and constant blade angle were obtained both from steady-state characteristics and from transient operation. Magnitude of speed response to changes in fuel flow and blade angle was investigated and is presented in the form of gain factors. Results indicate that at any given value of speed in the engine cruising speed range, time constants obt… more
Date: September 5, 1951
Creator: Oppenheimer, Frank L. & Jacques, James R.
Partner: UNT Libraries Government Documents Department
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Measurements in Flight of the Longitudinal Characteristics of Two Jet Aircraft, One With a Diving Tendency and the Other With a Climbing Tendency at High Mach Numbers

Description: Memorandum presenting flight tests conducted on two straight-wing jet airplanes of generally similar configuration, one exhibiting a diving tendency and the other a climbing tendency, in order to investigate the cause for the particular type of behavior of each airplane at high Mach numbers. The results showed that the diving tendency experienced by the one airplane was due to the predominant effect of an increased angle of attack of the horizontal tail.
Date: October 5, 1951
Creator: Anderson, Seth B.
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a Wedge With Various Holder Configurations for Static-Pressure Measurements in Subsonic Gas Streams

Description: The characteristics of a wedge static-pressure sensing element with various holder configurations were determined and compared with the characteristics of the conventional tube. The probes were tested over a range of Mach number from 0.3 to 0.95 and at various pitch and yaw angles. The investigation showed that the spike-mounted wedge sensing element has a pressure coefficient comparable with the conventional subsonic static-pressure probe and the pressure coefficient of the wedge varied less t… more
Date: September 5, 1951
Creator: Gettelman, Clarence C. & Krause, Lloyd N.
Partner: UNT Libraries Government Documents Department
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Investigation of the effects of geometric changes in an underwing pylon suspended external store installation on the aerodynamic characteristics of a 45 degree sweptback wing at high subsonic speeds

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel through a range of Mach numbers to determine the effects of external-store fineness ratio, store shape, store chordwise position, pylon thickness, pylon length, and pylon sweep angle on the aerodynamic characteristics of a number of underwing pylon-suspended external stores in combination with a 45 degree sweptback semispan wing and fuselage.
Date: March 5, 1951
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Partner: UNT Libraries Government Documents Department
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Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution, cambered and twisted for a trapezoidal span load distribution

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, which has been twisted and cambered for a trapezoidal span load distribution at subsonic and supersonic Mach numbers.
Date: February 5, 1951
Creator: Smith, Willard G. & Phelps, E. Ray
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach n… more
Date: September 5, 1951
Creator: Conrad, E. William & McAulay, John E.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of tail-pipe-burner design variables

Description: Report summarizing several experimental tail-pipe-burner investigations to indicate the effects of tail-pipe-burner design variables on the performance and operating characteristics. Most of the configurations were investigated over a wide range of altitudes and flight Mach numbers. The results indicate the desirable design features of a tail-pipe burner that will operate with high combustion efficiency and exhaust-gas temperature up to an altitude of approximately 50,000 feet.
Date: March 5, 1951
Creator: Fleming, W. A.; Conrad, E. William & Young, W. A.
Partner: UNT Libraries Government Documents Department
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Characteristics of flow over inclined bodies of revolution

Description: From Summary: "Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly ac… more
Date: March 5, 1951
Creator: Allen, H. Julian & Perkins, Edward W.
Partner: UNT Libraries Government Documents Department
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Flight determined buffet boundaries of ten airplanes and comparisons with five buffeting criteria

Description: Report presenting the flight-determined buffet boundaries of ten airplanes. Comparisons are made with five possible buffeting criteria related to airfoil-section characteristics. The primary factors that determine buffeting criteria are critical Mach number, Mach number of sonic flow at the crest, lift-divergence Mach number, lift-peak Mach number, and empirical buffeting criterion are provided.
Date: January 5, 1951
Creator: Gadeberg, Burnett L. & Ziff, Howard L.
Partner: UNT Libraries Government Documents Department
open access

Experimental Pressure Distributions Over Two Wing-Body Combinations at Mach Number 1.9

Description: Memorandum presenting pressure distributions on two wing-body combinations obtained at a Mach number of 1.9 to investigate the wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body with an ogive nose were studied alone and in combination. The pressure distributions over the wing-body combination compared favorably with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of the wings where … more
Date: February 5, 1951
Creator: Moskowitz, Barry & Maslen, Stephen H.
Partner: UNT Libraries Government Documents Department
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The effect of thickness ratio on section thrust distribution as determined from a study of wake surveys of the NACA 4-(0)(03)-045 and 4-(0)(08)-045 two-blade propellers up to forward Mach numbers of 0.925

Description: Report presenting testing of two two-blade propellers in the 8-foot high-speed tunnel for a range of blade angles and Mach numbers. The results show that changes in thrust loading due to compressibility effects were much smaller for the thin-blade propeller than for the thick-blade propeller.
Date: April 5, 1951
Creator: Harrison, Daniel E. & Milillo, Joseph R.
Partner: UNT Libraries Government Documents Department
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Steady-state engine windmilling and engine speed decay characteristics of an axial-flow turbojet engine

Description: A wind tunnel investigation has been conducted to determine the steady-state windmilling and engine speed decay characteristics of the J34-WE-32 turbo-jet over a range of altitudes from 5000 to 50,000 feet and simulated flight Mach numbers from 0.19 to 1.06. The effect of an engine accessory load on the speed decay characteristics was also determined. The accessory load was about 7.8 horsepower for engine speeds above 4000 rpm and decreased with decreasing engine speed. An analysis of the speed… more
Date: December 5, 1951
Creator: Sobolewski, A. E. & Farley, J. M.
Partner: UNT Libraries Government Documents Department
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Preliminary results of turbojet-engine altitude-starting investigation

Description: A spark energy of 2.13 joules per spark at 1 spark per second produced ignition to an altitude of 50,000 feet at a flight Mach number of 0.6. The minimum power requirements for ignition were obtained from a combination of low spark repetition rates and high spark energy. The altitude-ignition limit was also increased by increasing spark-gap immersion, fuel temperature, inlet-air temperature, and fuel volatility, and by decreasing flight Mach number. The maximum altitude at which flame propagati… more
Date: November 5, 1951
Creator: Wilsted, H. D. & Armstrong, J. C.
Partner: UNT Libraries Government Documents Department
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A Multiple-Range Self-Balancing Thermocouple Potentiometer

Description: "A multiple-range potentiometer circuit is described that provides automatic measurement of temperatures or temperature differences with any one of several thermocouple-material pairs. Techniques of automatic reference junction compensation, span adjustment, and zero suppression are described that permit rapid selection of range and wire material, without the necessity for restandardization, by setting of two external tap switches" (p. 1).
Date: November 5, 1951
Creator: Warshawsky, I. & Estrin, M.
Partner: UNT Libraries Government Documents Department
open access

Variation of the pressure limits of flame propagation with tube diameter for propane-air mixtures

Description: An investigation was made of the variation of the pressure limits of flame propagation with tube diameter for quiescent propane with tube diameter for quiescent propane-air mixtures. Pressure limits were measured in glass tubes of six different inside diameters, with a precise apparatus. Critical diameters for flame propagation were calculated and the effect of pressure was determined. The critical diameters depended on the pressure to the -0.97 power for stoichiometric mixtures. The pressure d… more
Date: December 5, 1951
Creator: Belles, Frank E. & Simon, Dorothy M.
Partner: UNT Libraries Government Documents Department
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Comparison of Semispan and Full-Span Tests of a 47.5 Degrees Sweptback Wing With Symmetrical Circular-Arc Sections and Having Drooped-Nose Flaps, Trailing-Edge Flaps, and Ailerons

Description: Report presenting an investigation to compare the characteristics of a full-span and a semispan highly swept wing in order to evaluate the general validity of the semispan wing testing technique. Results regarding the lift, drag, and pitching-moment characteristics are provided.
Date: December 5, 1951
Creator: Lipson, Stanley & Barnett, U. Reed, Jr.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85

Description: "An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for s… more
Date: November 5, 1951
Creator: Jack, John R.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the aerodynamic characteristics of a 1/15-scale model of the Northrop MX-775A missile

Description: Report presenting the results of a wind-tunnel investigation to determine the control effectiveness and variations of forces and moments as functions of angles of attack and sideslip for a scale model of the MX-775A missile at a range of Mach and Reynolds numbers. Results regarding the static longitudinal stability and control characteristics, Reynolds number effects, lateral-control characteristics, and clipped-wing configuration characteristics are provided.
Date: October 5, 1951
Creator: Phelps, E. Ray & Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department
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