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A method for the analysis of compounds containing boron, carbon, and hydrogen

Description: Report presenting a method for analyzing each of the elements, boron, carbon, and hydrogen from the quantitative analysis of a single sample of an organoboron compound. The method is helpful for the analysis of volatile hydrocarbons and polynuclear aromatic compounds.
Date: March 3, 1955
Creator: Allen, Harrison, Jr. & Tannenbaum, Stanley
Partner: UNT Libraries Government Documents Department

Performance of a double-cone inlet with and without a shroud at below-design Mach numbers

Description: Report presenting values of zero angle-of-attack performance of a double-cone inlet with and without a shroud through a range of mass-flow ratios and Mach numbers. Maximum propulsive thrust was computed to be higher with the shrouded inlet at all supersonic Mach numbers tested. Results regarding internal diffuser performance, drag, and engine performance are provided.
Date: March 3, 1955
Creator: Pennington, Donald; Rabb, Leonard & Simpkinson, Scott H.
Partner: UNT Libraries Government Documents Department

A correlation of two-dimensional data on lift coefficient available with blowing-, suction-, slotted-, and plain-flap high-lift devices

Description: Report presenting a correlation of the available data on various flap-type high-lift devices in two-dimensional form for flap-chord ratios ranging from 20 to 40 percent. Data for plain, single-slotted, and double-slotted flaps, and for suction and blowing flaps, are provided. Analysis regarding the effect of wing thickness and slot width is also provided for the various types of flaps.
Date: October 3, 1955
Creator: Riebe, John M.
Partner: UNT Libraries Government Documents Department

Drag and rolling-moment effectiveness of trailing-edge spoilers at Mach numbers 2.2 and 5.0

Description: Report presenting free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on low-aspect-ratio wings with both laminar and turbulent boundary layers at two different Mach numbers. The effect of a spoiler deflected from the surface of a wing is to cause boundary-layer separation upstream.
Date: October 3, 1955
Creator: Canning, Thomas N. & DeRose, Charles E.
Partner: UNT Libraries Government Documents Department

Internal performance of a series of circular auxiliary-air inlets immersed in a turbulent boundary layer : Mach number range: 1.5 to 2.0

Description: Report presenting an experimental investigation to determine the internal performance characteristics of a series of circular, open-nose auxiliary air inlets immersed into the supersonic, turbulent boundary layer generated by the 8- by 6-foot supersonic wind tunnel. Inlet critical total-pressure and mass-flow ratios were reasonably predicted by theory at all conditions investigated. Results regarding boundary-layer flow, inlet performance, and diffuser-exit pressure fluctuations are provided.
Date: March 3, 1955
Creator: Simon, Paul C.
Partner: UNT Libraries Government Documents Department

Effect of surface-active additives on physical properties of slurries of vapor-process magnesium

Description: The presence of 3 to 5 percent surface-active additive gave the lowest Brookfield apparent viscosity, plastic viscosity, and yield value that were obtained for slurry fuels containing approximately 50 percent vapor-process magnesium in JP-1 fuel. The slurries settled little and were easily remixed. A polyoxyethylene dodecyl alcohol was the most effective of 13 additives tested in reducing the Brookfield apparent viscosity and the yield value of the slurry. The seven most effective additives all had a hydroxyl group plus an ester or polyoxethylene group in the molecule. The densities of some of the slurries were measured.
Date: November 3, 1955
Creator: Pinns, Murray L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel measurements of the dynamic cross derivative (rolling moment due to yawing velocity and to acceleration in sideslip) of the Douglas D-558-II airplane and its components at supersonic speeds including description of the technique

Description: Report presenting a technique and the results obtained of wind-tunnel forced-oscillation tests on a model of the Douglas D-558-II airplane which was instrumented to obtain the dynamic cross derivative and static derivative. Tests were conducted for a range of Mach numbers and angles of attack. Results regarding sample calculations of the period and damping of the full-scale airplane are provided despite not being conclusive due to the inadequate number of flight conditions investigated.
Date: November 3, 1955
Creator: Boatright, William B.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at Mach 1.9 of multijet-missile base pressures

Description: From Summary: "An experimental wind-tunnel investigation was conducted at Mach 1.9 to determine the pressures acting on the base of a multijet missile using unheated air and carbon dioxide as jet fluids. The variation of base pressure with jet static-pressure ratio was compared with results estimated for an axisymmetric single-jet model and some correlation was observed."
Date: March 3, 1955
Creator: Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Performance of four experimental high btu-per-gallon fuels in a single turbojet combustor

Description: Performance characteristics of four hydrocarbon fuels having high Btu per gallon were determined in a single turbojet combustor. At simulated low-altitude operating conditions, the fuels with high Btu per gallon generally produced more carbon than did JP-4 and JP-5 fuels. The deposits were reduced appreciably with a fuel-oil additive. At high-altitude conditions, the high Btu-per-gallon fuels gave lower efficiencies than did JP-4 or JP-5 fuels. No attempts were made to improve performance by combustor design modification.
Date: November 3, 1955
Creator: Jonash, Edmund R.; Metzler, Allen J. & Butze, Helmut F.
Partner: UNT Libraries Government Documents Department

Temperature recovery factors on a slender 12 degree cone-cylinder at Mach numbers from 3.0 to 6.3 and angles of attack up to 45 degrees

Description: Report presenting measurements of recovery temperatures on a slender cone-cylinder with a 12 degree vertex angle and a 1.25-inch-diameter cylinder for a range of Mach numbers. Results regarding the visual evidence, temperature distributions, pressure distributions, summary figures, correlation of temperature patterns with boundary-layer transition and separation, and recovery factors are provided.
Date: October 3, 1955
Creator: Reller, John O. & Hamaker, Frank M.
Partner: UNT Libraries Government Documents Department

Temperature in a J47-25 Turbojet-Engine Combustor and Turbine Sections During Steady-State and Transient Operation in a Sea-Level Test Stand

Description: From Summary: "In order to determine the conditions of engine operation causing the most severe thermal stresses in the hot parts of a turbojet engine, a J47-25 engine was instrumented with thermocouples and operated to obtain engine material temperatures under steady-state and transient conditions. Temperatures measured during rated take-off conditions of nozzle guide vanes downstream of a single combustor differed on the order of 400 degrees F depending on the relation of the blades position to the highest temperature zone of the burner. Under the same operation conditions, measured midspan temperatures in a nozzle guide vane in the highest temperature zone of a combustor wake ranged from approximately 1670 degrees F at leading and trailing edges to 1340 degrees F at midchord on the convex side of the blade."
Date: June 3, 1955
Creator: Morse, C. R. & Johnston, J. R.
Partner: UNT Libraries Government Documents Department

Error in airspeed measurement due to the static-pressure field ahead of an airplane at transonic speeds

Description: The magnitude and variation of the static-pressure error for various distances ahead of sharp-nose bodies and open-nose air inlets and for a distance of 1 chord ahead of the wing tip of a swept wing are defined by a combination of experiment and theory. The mechanism of the error is discussed in some detail to show the contributing factors that make up the error. The information presented provides a useful means for choosing a proper location for measurement of static pressure for most purposes.
Date: August 3, 1955
Creator: O'Bryan, Thomas C.; Danforth, Edward C. B. & Johnston, J. Ford
Partner: UNT Libraries Government Documents Department

A method for determining the composition of methanol-trimethyl borate mixtures

Description: A study of mixtures of pure methanol and trimethyl borate showed that the composition can be accurately obtained by a simple density determination. The refractive-index determination gives the composition with much less accuracy. The potentiometric titration of boric acid is also discussed.
Date: November 3, 1955
Creator: Kaye, Samuel & Sordyl, Frank
Partner: UNT Libraries Government Documents Department

Experimental investigation of the zero-lift wave drag of seven pairs of delta wings with constant and varying thickness ratios at Mach numbers of 1.62, 1.93, and 2.41

Description: Report presenting seven pairs of wings tested at Mach numbers of 1.63, 1.93, and 2.41 to determine the validity of NACA TN 2858, which predicts that delta wings with linearly varying thickness ratio have less wave drag than a constant-thickness-ratio delta wing. Results regarding the zero-lift wave drag, values of lift, total drag, pitching moment, and lift-drag ratios for an angle of attack range are provided.
Date: June 3, 1955
Creator: Henderson, Arthur, Jr.
Partner: UNT Libraries Government Documents Department

Effects of boundary-layer separation on normal force and center of pressure of a cone-cylinder model with a large base flare at Mach numbers from 3.00 to 6.28

Description: Report presenting testing of a body with a 22.5 degree conical nose, a 4-diameter-long cylindrical midsection, and a 20 degree cone-frustum tail flare. The tests were made over a variety of angles of attack and Mach numbers. Results regarding spark shadowgraph pictures and predictions versus the actual values were provided.
Date: October 3, 1955
Creator: Dennis, David H. & Syvertson, Clarence A.
Partner: UNT Libraries Government Documents Department

Performance of as-forged, heat-treated, and overaged S-816 blades in a turbojet engine

Description: Report presenting an investigation to study the effects of several heat treatments on the operating life of turbine blades in a J33-33 turbojet engine operated without an afterburner. As-forged blades, blades solution treated at temperatures high enough to produce germinated grains, blades given a double-aging treatment, and blades overaged by overtemperature heat treatments are evaluated. Results regarding the engine operating results and blade performance, metallurgical studies of as-heat-treated specimens, and metallurgical studies of failed blades are provided.
Date: March 3, 1955
Creator: Weeton, J. W.; Clauss, F. J. & Johnston, J. R.
Partner: UNT Libraries Government Documents Department

Boundary-Layer Transition at High Reynolds Numbers as Obtained in Flight of a 20 Degree Cone-Cylinder With Wall to Local Stream Temperature Ratios Near 1.0

Description: Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimensional) and Van Driest (two-dimensional), respectively.
Date: November 3, 1955
Creator: Rabb, Leonard & Disher, John H.
Partner: UNT Libraries Government Documents Department

NACA Conference on Engine Stall and Surge

Description: A compilation of the six technical papers presented at the NACA Conference on Engine Stall and Surge on February 3, 1955 at the Lewis Flight Propulsion Laboratory. A list of conference attendees is also provided.
Date: February 3, 1955
Partner: UNT Libraries Government Documents Department

Drag Near Zero Lift of a 1/7-Scale Model of the Convair B-58 External Store as Measured in Free Flight Between Mach Numbers of 0.8 and 2.45

Description: "The zero-lift drag of a 1/7-scale model of the Convair B-58 external store was obtained at mach numbers between 0.8 and 2.45 at corresponding Reynolds numbers per foot of 3.5 x 10 to the 6th power and 15.3 X 10 to the 6th power. The experimental drag data are compared with calculated values at both subsonic and supersonic speeds and show good agreement. In addition to the drag data, some static stability derivatives and damping factors were also obtained and are presented with the predicted values of these derivatives for completeness and for comparison" (p. 1).
Date: August 3, 1955
Creator: Hopko, Russell N.
Partner: UNT Libraries Government Documents Department

Measured Effective Thermal Conductivity of Uranium Oxide Powder in Various Gases and Gas Mixtures

Description: Memorandum presenting an investigation of the effective thermal conductivities of powders, which included uranium oxide UO(sub 2) powder with a density of 59.5 percent of the density of the solid uranium oxide at a range of temperatures. Helium, argon, and nitrogen gases and mixtures of helium-argon and xenon-krypton gases were introduced into the powder void, and the experimental effective thermal conductivities of the gas-powder mixtures were determined.
Date: March 3, 1955
Creator: Boegli, J. S. & Deissler, R. G.
Partner: UNT Libraries Government Documents Department

Investigation of 300 Area slug pickling operation

Description: The recent modernization program for the 300 area metal preparation process has included installation of automatic spray pickling machines. Operative problems have accompanied start-up of the new machine including too rapid reoxidation of slugs leaving the pickle operation. Numerous slugs have had to be repickled with consequent interruption to canning operations. Investigations were conducted in cooperation with Coatings and Corrosion Unit, Fuel Technology Sub-Section and Process Improvement Unit, Metal Preparation Section, to obtain basis information about slug oxide removal and reoxidation. Findings and conclusions from the investigation are presented in this document.
Date: August 3, 1955
Creator: Corlett, R. F.
Partner: UNT Libraries Government Documents Department