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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
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Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0

Description: Report presenting testing of the performance of a ventrally mounted inlet having a variable-angle vertical-wedge compression surface determined at several Mach numbers for angles of attack, angles of yaw, and wedge angle. A solid wedge and wedges with two different porosities were tested. Results regarding the inlet flow-field survey, comparison of inlet configurations, performance of the inlet, effect of free-stream Mach number at angle of attack of 2 degrees, effect of angles of attack and ya… more
Date: August 3, 1956
Creator: Allen, John L. & Piercy, Thomas G.
Partner: UNT Libraries Government Documents Department
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Flight measurements of the low-speed characteristics of a 35 degree swept-wing airplane with area suction boundary-layer control on the flaps

Description: Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics o… more
Date: February 3, 1956
Creator: Anderson, Seth B. & Quigley, Hervey C.
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Longitudinal Stability and Control Characteristics of the Grumman F8F-1 Airplane, TED No. NACA 2379

Description: A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compres… more
Date: September 3, 1948
Creator: Assadourian, Arthur & Reeder, John P.
Partner: UNT Libraries Government Documents Department
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Flight Test of a Solid-Fuel Ram Jet With the Internal Surface of the Combustor Air Cooled

Description: Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. Having an internally cooled combustor averted combustor burn-out during the flight test. Results regarding acceleration, altitude, air specific impulse, and fuel specific impulse are provided.
Date: July 3, 1956
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department
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Flight Test of a Solid-Fuel Ramjet With the Internal Surface of the Combustor Air Cooled

Description: Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. The internally cooled combustor averted combustor burn-out during the flight test. Results regarding the net thrust coefficient, gross thrust coefficient, time history of the air specific impulse, and total fuel load are provided.
Date: July 3, 1956
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department
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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
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Performance of J33-A-21 and J33-A-23 Turbojet-Engine Compressors with Water Injection

Description: "As part of the performance investigation of compressors for the J33 turbojet engine, the A-21 model and the A-23 model with a 17- and a 34-blade impeller were operated with water injection at their respective design equivalent speeds of 11,500 and 11,750 rpm. Inlet conditions of pressure of 14 inches of mercury absolute and of ambient temperature correspond to those of the investigation of these models without water injection. The water-air ratio by weight ranged from 0.05 to 0.06. By the use … more
Date: August 3, 1949
Creator: Beede, William L. & Withee, Joseph R., Jr.
Partner: UNT Libraries Government Documents Department
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Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections

Description: Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord. Results regardi… more
Date: July 3, 1950
Creator: Berggren, Robert E. & Graham, Donald J.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Knock-Limited Performance of a Triptane Blend, a Toluene Blend, and 28-R Fuel in an R-1830-75 Engine

Description: "Knock-limited performance data were obtained for three fuels on an R-1830-75 engine in a B-24D airplane at engine speeds of 1800, 2250, and 2600 rpm, a spark advance of 25 degrees B.T.C., and carburetor-air temperatures of 85 F for 1800 and 2250 rpm and 100 F for 2600 rpm. The test fuels were a blend of 80 percent 28-R plus 20 percent triptane (leaded to 4.5 ml TEL/gal), a blend of 80 percent 28-R plus 15 percent toluene (leaded to 4.5 ml TEL / gal), and 28-R fuel. The knock-limited manifold p… more
Date: September 3, 1946
Creator: Blackman, Calvin C.
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of operational characteristics of J47 turbojet engine

Description: Report presenting an investigation in the altitude wind tunnel to determine the operational characteristics of a J47 turbojet engine over a wide range of simulated flight conditions at a range of altitudes. Operational characteristics investigated include operating range, starting, altitude and airspeed compensation of the fuel regulator, and acceleration.
Date: August 3, 1950
Creator: Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department
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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
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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
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Low-speed longitudinal stability and lateral-control characteristics of a model of a 40 degree swept-wing fighter-type airplane at a Reynolds number of 9 x 10(exp 6)

Description: Report presenting an investigation on a model of a 40 degree swept-wing fighter airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight testing. The effects of high-lift and stall control devices, horizontal-tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated.
Date: February 3, 1956
Creator: Bollech, Thomas V. & Kelly, H. Neale
Partner: UNT Libraries Government Documents Department
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A comparison of the experimental and theoretical loading over triangular wings at supersonic speeds

Description: Report presenting the results of an experimental investigation of the pressure distribution over two triangular wings at supersonic speeds. The two wings which were tested had identical plan forms, 45 degrees of sweepback of the leading edge, and an aspect ratio of 4.0, but different airfoil sections. Results regarding the pressure distribution at zero lift, flow characteristics and pressure distribution at angles of attack, normal-force coefficients, and application of results to other triangu… more
Date: January 3, 1951
Creator: Boyd, John W. & Phelps, E. Ray
Partner: UNT Libraries Government Documents Department
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Interferometer With Large Working Field Utilizing Schlieren Optics

Description: Report describing the optical system of a new-type interferometer utilizing schileren optics. Using this instrument, former limits to the working-field size imposed by the practical size of conventional topics are removed. Testing using the interferometer occurred in the 18- by 18-inch supersonic tunnel.
Date: January 3, 1951
Creator: Buchele, Donald R. & Day, Pierce B.
Partner: UNT Libraries Government Documents Department
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The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

Description: "The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the true stress, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Rayleigh-Ritz method of finding upper limits" (p. 213).
Date: May 3, 1946
Creator: Budiansky, Bernard & Hu, Pai C.
Partner: UNT Libraries Government Documents Department
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Correlation of laboratory smoke test with carbon deposition in turbojet combustors

Description: Report presenting a correlation of carbon deposition of 19 fuels in a turbojet combustor as a function of the boiling point and of the flame height at the sooting point of the fuels in a simple wick lamp for a particular combustor operating at a single set of conditions. Two similar investigations with different combustors, operating conditions, and nine different fuels yielded similar correlations on the same graph.
Date: February 3, 1950
Creator: Busch, Arthur M.
Partner: UNT Libraries Government Documents Department
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Effect of fuel properties on liner temperatures in a single tubular turbojet combustor

Description: Report presenting the effect of fuel properties on combustion-liner temperatures in a single tubular combustor at combustor-inlet conditions representative of those encountered in turbojet-powered high-flight-speed aircraft. Testing was conducted with three liquid jet-type fuels that varied in voltaility and aromatic content. The variations in fuel properties were found to produce only moderate and not always consistent changes in average liner temperature.
Date: June 3, 1957
Creator: Butze, Helmut F.
Partner: UNT Libraries Government Documents Department
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Investigation of a 1/4-Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Influence of Trailing-Edge Flap Span and Deflection on the Longitudinal Characteristics

Description: Report presenting development tests on a model of the Republic F-105 airplane at a Mach number of 0.20. The purpose of the current investigation is to obtain the longitudinal force and moment characteristics of the model equipped with trailing-edge flaps of various spans and deflections. Results regarding the longitudinal stability characteristics and effect of the horizontal tail are provided.
Date: September 3, 1954
Creator: Cancro, Patrick A. & Kelly, H. Neale
Partner: UNT Libraries Government Documents Department
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Investigation of a 1/4-Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel : Influence of Trailing-Edge Flap Span and Deflection on the Longitudinal Characteristics

Description: Memorandum presenting development tests on a scale model of the Republic F-105 airplane in the 19-foot pressure tunnel. The second phase, which is presented in this report, was made at a Reynolds number of 9.0 x 10(exp 6) and a Mach number of 0.20. The purpose of the tests was to obtain the longitudinal force and moment characteristics of the model equipped with trailing-edge flaps of various spans and deflections.
Date: September 3, 1954
Creator: Cancro, Patrick A. & Kelly, H. Neale
Partner: UNT Libraries Government Documents Department
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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
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Investigation of a Ram-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower

Description: Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.
Date: June 3, 1953
Creator: Carpenter, Paul J. & Radin, Edward J.
Partner: UNT Libraries Government Documents Department
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