UNT Libraries Government Documents Department - 173 Matching Results

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Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data

Description: Report presenting a theoretical method for calculating heat transfer in the laminar boundary layer on yawed infinite cylinders in compressible flow. The method can be applied to a cylinder of arbitrary cross section and arbitrary chordwise wall-temperature distribution. The variation in local heat transfer around the surface of the cylinder was found to have little functional dependence on yaw angle or wall temperature.
Date: August 9, 1955
Creator: Beckwith, Ivan E.
Item Type: Refine your search to only Report
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Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin

Description: Report presenting testing of two 2024-T3 aluminum-alloy multiweb wing structures (MW-2 and MW-3), similar to airplane or missile wings, at a Mach number of 2 under simulated supersonic flight conditions. Results regarding experimentally determined test conditions, model temperatures, strain-gage results, and model failures are provided. The report indicates that much of the stress data does not agree with expected results, but there is too much uncertainty regarding the reduction of strain data… more
Date: August 9, 1955
Creator: Griffith, George E.; Miltonberger, Georgene H. & Rosecrans, Richard
Item Type: Refine your search to only Report
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Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes

Description: Report presenting the gross weight and uranium investment of nuclear-powered, direct-air, shieldless, ram-jet missiles for a range of altitudes and Mach numbers. Results regarding the effect of reactor operating conditions and flight conditions on ramjet performance and effect of assumptions on ramjet performance are provided.
Date: November 9, 1955
Creator: Sams, Eldon W. & Rom, Frank E.
Item Type: Refine your search to only Report
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Aircraft-Fuel-Tank Design for Liquid Hydrogen

Description: "Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than… more
Date: August 9, 1955
Creator: Reynolds, T. W.
Item Type: Refine your search to only Report
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High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor

Description: Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet te… more
Date: December 9, 1954
Creator: Butze, Helmut F.
Item Type: Refine your search to only Report
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Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance

Description: Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date: July 9, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Item Type: Refine your search to only Report
open access

Effect of diffuser design, diffuser-exit velocity profile and fuel distribution on altitude performance of several afterburner configurations

Description: "An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner f… more
Date: July 9, 1953
Creator: Conrad, E. William; Schultz, Frederick W. & Usow, Karl H.
Item Type: Refine your search to only Report
open access

Correlation Between Hydrogen Pressure and Protective Action of Additives in the Molten Sodium Hydroxide - Nickel System

Description: Memorandum presenting an investigation of the effect of various metallic additives on the molten sodium hydroxide - nickel system. The hydrogen evolved from such systems was measured and the evolution was correlated with the effect of the metal on mass transfer. Results regarding a check with standard tests, purging, presence of two valences for chromium, reaction time of the additive, and pressure within nickel crucibles are provided.
Date: February 9, 1956
Creator: May, Charles E.
Item Type: Refine your search to only Report
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Effectiveness of Inhibitors for Mass Transfer and Corrosion in Sodium Hydroxide - Nickel Systems

Description: Memorandum presenting static crucible tests with additions of the reducing agents sodium chromite Na(sub 3)CrO(sub 4) and manganese dioxide MnO(sub 2) indicate that salts soluble in sodium hydroxide may be added to inhibit mass transfer in nickel. The metals manganese, vanadium, and molybdenum were also investigated in static crucibles and found to be ineffective.
Date: February 9, 1956
Creator: Forestieri, Americo F. & Lad, Robert A.
Item Type: Refine your search to only Report
open access

Free-Spinning Characteristics of a 1/21-Scale Model of the Douglas AD-2W Airplane: TED No. NACA DE329

Description: Report presenting an investigation to determine the spin and recovery characteristics of a model of the Douglas AD-2W airplane, which has a large radome installation. Results indicated that the plane has satisfactory erect and inverted spin-recovery characteristics. Information about erect spins, inverted spins, and recommended recovery technique is provided.
Date: June 9, 1948
Creator: White, Richard P.
Item Type: Refine your search to only Report
open access

Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 1: nacelle with offset air inlet

Description: Report presenting aerodynamic and icing investigations on a model of a turbojet-engine nacelle in order to provide icing protection for the engine, protective screen, and accessory housing by the introduction of hot gases into the inlet-air stream. Adequate ice protection was afforded when the minimum kinetic temperature in the protective screen was greater than 32 degrees Fahrenheit.
Date: July 9, 1948
Creator: Callaghan, Edmund E.; Ruggeri, Robert S. & Krebs, Richard P.
Item Type: Refine your search to only Report
open access

Effect of Taper Ratio on the Low-Speed Rolling Stability Derivatives of Swept and Unswept Wings of Aspect Ratio 2.61

Description: Report discussing testing on a series of tapered swept wings under conditions simulating rolling flight. The lift, longitudinal-force, and pitching-moment characteristics for three swept wings are provided. The results indicated that a decrease in taper ratio on a swept wing caused a small decrease in damping in roll at low and moderate lift coefficients.
Date: November 9, 1948
Creator: Brewer, Jack D. & Fisher, Lewis R.
Item Type: Refine your search to only Report
open access

Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 2: effects of slots upon an inlet enclosing 61.5 percent of the maximum circumference of the forebody

Description: Report presenting tests at Mach numbers between 1.36 and 2.01 of a twin-scoop duct inlet that had slots in the walls of the duct contiguous to the forebody and immediately behind the inlet. The mass flow and total-pressure recovery through the diffusor were measured during tests in which the slot length was constant and the slot width and ramp angle were varied. Results regarding mass flow and total-pressure recovery are provided.
Date: June 9, 1948
Creator: Davis, Wallace F. & Goldstein, David L.
Item Type: Refine your search to only Report
open access

Tests of the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers

Description: Memorandum presenting an investigation on NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils at a range of Mach numbers and low Reynolds numbers, which indicated that the effect of increasing the trailing-edge angle was inappreciable on the Mach number for the normal-force break, to decrease the normal-force-curve slope, to reduce the effects of compressibility, and to decrease the minimum drag coefficient and to increase maximum normal-force to drag ratio.
Date: July 9, 1948
Creator: Lindsey, W. F. & Humphreys, Milton D.
Item Type: Refine your search to only Report
open access

Gas-turbine-engine operation with variable-area fuel nozzles

Description: Report presenting an examination of the characteristics of variable-area and fixed-area atomizing nozzles in relation to use in aircraft gas-turbine engines. A variable-area fuel nozzle and a fuel-distribution control that were used int eh experimental operation of a turbojet engine are described. Results regarding nozzle characteristics and fuel distribution, effect of atomization on engine operating characteristics, and fuel-system characteristics during engine operation are provided.
Date: July 9, 1948
Creator: Gold, Harold & Straight, David M.
Item Type: Refine your search to only Report
open access

Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer 2: Effect of an Oblique Shock Wave Immediately Ahead of the Inlet

Description: Memorandum presenting an investigation of a model with a ramp that produced an oblique shock wave in front of an annular duct inlet, which was tested at Mach numbers between 1.36 and 2.01 to determine the effect of reducing the entrance Mach number on the total-pressure recovery after diffusion. The results showed that the maximum total-pressure recovery of the model investigated was considerably improved through the addition of a ramp.
Date: August 9, 1948
Creator: Brajnikoff, George B.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Combinations at High Subsonic Speeds: Sweep Series

Description: Report presenting an investigation in the high-speed tunnel to determine the effect of sweep on the static lateral stability characteristics of wing-fuselage combinations with wings of aspect ratio 4 and taper ratio 0.6 at high subsonic speeds. Results regarding rolling-moment characteristics and lateral-force and yawing-moment characteristics are also provided.
Date: September 9, 1952
Creator: Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
open access

Free-spinning tunnel investigation of the 1/21-scale model of the Chance Vought F7U-3 airplane: TED No. NACA DE 362

Description: Report presenting an investigation of a 1/21-scale model of the Chance Vought F7U-3 airplane in the 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics for combat loading in the clean condition. Results regarding erect spins, inverted spins, spin-recovery parachutes, and recommended recovery technique are provided.
Date: November 9, 1951
Creator: Klinar, Walter J. & Healy, Frederick M.
Item Type: Refine your search to only Report
open access

Experimental investigation of typical constant- and variable-area exhaust nozzles and effects on axial-flow turbojet-engine performance

Description: Report presenting testing of several turbojet engines with both constant- and variable-area nozzles to extend full-scale nozzle performance to higher exhaust-nozzle pressure ratios and to investigate the effects of constant- and variable-area nozzles on turbojet-engine operation. Results regarding the different types of nozzles are provided.
Date: July 9, 1951
Creator: Wallner, Lewis E. & Wintler, John T.
Item Type: Refine your search to only Report
open access

Rolling Effectiveness of All-Movable Wings at Small Angles of Incidence at Mach Numbers From 0.6 to 1.6

Description: "Experimental data have been obtained of the rolling effectiveness of several all-movable wing configurations by means of rocket-propelled test vehicles in free flight. The results are compared with some available methods of estimation. These results validate the use of the simple equation derived by a strip integration and originally presented in NACA RM L50G14b over a wide range of application as a means of estimating the rolling effectiveness of all-movable wings" (p. 1).
Date: October 9, 1951
Creator: Strass, H. Kurt & Marley, Edward T.
Item Type: Refine your search to only Report
open access

Jet effects on pressures and drags of bodies

Description: From Introduction: "The propulsive jet that discharges from the base of a missile body or nacelle may, by interaction with external stream, cause important drag and stability changes. This paper presents some results of recent investigations by the Lewis and Langley laboratories of the jet effect on body end pressures and drag at zero lift."
Date: November 9, 1951
Creator: Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
open access

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane tapered wing of aspect ratio 3.1 with 3-percent-thick rounded-nose section

Description: Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.
Date: July 9, 1952
Creator: Heitmeyer, John C.
Item Type: Refine your search to only Report
open access

Effects of twist and camber, fences, and horizontal-tail height on the low-speed longitudinal stability characteristics of a wing-fuselage combination with a 45 degree sweptback wing of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)

Description: Report presenting an investigation of the separate and combined effects of twist and camber, fences, and horizontal-tail height on the static longitudinal stability of a 45 degree sweptback wing-fuselage combination of aspect ratio 8 at Mach number 0.19. Two different wings were investigated, one untwisted and one with twist and cambered. Results regarding wing-fuselage configuration and wing-fuselage configurations with horizontal tail are provided.
Date: December 9, 1952
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
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