Country
States
766 Matching Results
Results open in a new window/tab.
An Investigation of the Dynamic and Static Stability Characteristics of a Group of Specialized Store Configurations at Transonic Speeds
Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date:
August 21, 1953
Creator:
Henry, Beverly Z., Jr. & Braden, John A.
System:
The UNT Digital Library
Theoretical Performance of Liquid Hydrogen and Liquid Fluorine as a Rocket Propellant
Report of theoretical values of performance parameters for liquid hydrogen and flourine as a rocket propellant for a wide range of fuel-oxidant and expansion ratios. Parameters computed include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date:
February 6, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Theoretical Performance of Liquid Ammonia and Liquid Fluorine as a Rocket Propellant
"Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity" (p. 1).
Date:
July 3, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Theoretical Performance of Mixtures of Liquid Ammonia and Hydrazine as Fuel With Liquid Fluorine as Oxidant for Rocket Engines
Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine with flourine as oxidant for a variety of parameters. Parameters included are specific impulse, combustion chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date:
July 29, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Theoretical Performance of Liquid Hydrazine and Liquid Fluorine as a Rocket Propellant
"Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity" (p. 1).
Date:
July 3, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Results of a Power-on Flight of a 1/10-Scale Rocket-Propelled Model of the Convair XF2Y-1 Airplane at a Mach Number of 1.53
Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.
Date:
September 28, 1953
Creator:
Bland, William M., Jr. & Nelson, Robert L.
System:
The UNT Digital Library
Development of a Supersonic Area Rule and an Application to the Design of a Wing-Body Combination Having High Lift-to-Drag Ratios
Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.
Date:
August 18, 1953
Creator:
Whitcomb, Richard T. & Fischetti, Thomas L.
System:
The UNT Digital Library
Analytical Studies of the Response to Longitudinal Control of Three Airplane Configurations in Landing Approaches
Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.
Date:
April 9, 1953
Creator:
Bihrle, William, Jr. & Stone, Ralph W., Jr.
System:
The UNT Digital Library
Experimental and theoretical investigation of rotating-stall characteristics of single-stage axial-flow compressor with hub-tip ratio of 0.76
Report presenting the overall performance and rotating stall characteristics of a single-stage compressor with a hub-tip ratio of 0.76 and a symmetrical velocity diagram over a wide range of weight flow for several different design speed percentages. No discontinuities in performance were noted at an operating condition. Results regarding the overall performance, types of rotating stall observed, circumferential extent of stall zones, flow fluctuations incited by rotating stall, rotating-stall hysteresis, and a theoretical analysis are provided.
Date:
November 30, 1953
Creator:
Graham, Robert W. & Prian, Vasily D.
System:
The UNT Digital Library
An Investigation at Transonic Speeds of the Effects of Fences, Drooped Nose, and Vortex Generators on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a 6-Percent-Thick, 45 Degree Sweptback Wing
Report presenting an investigation at transonic speeds to determine the effects of fences, drooped nose, combination fences and drooped nose, and vortex generators on a 45 degree sweptback wing-fuselage combination. The purpose of undertaking this investigation was due to the pitch-up tendency that results from leading-edge vortex-type flow on thin sweptback wings. The data for each component and their interaction with one another is also provided.
Date:
March 31, 1953
Creator:
Hieser, Gerald
System:
The UNT Digital Library
Effect of Drawbar Upstream Location on Air Velocity Distribution at the Inlet Face of Reactor Segment Designed by the General Electric Company
The results of flow tests on a drawbar for the General Electric reactor segment test in the MTR are reported. The drawbar is a T-shaped obstruction located as close to the upstream face of the reactor test segment as possible without serious flow distortion ; the drawbar is required for instrumentation leads and segment insertion and removal in the MTR. The effect of drawbar upstream distance on velocity distribution across the segment face is evaluated for several Reynolds numbers.
Date:
January 1953
Creator:
Nagey, T. F. & Sams, E. W.
System:
The UNT Digital Library
Effect of diffuser design, diffuser-exit velocity profile and fuel distribution on altitude performance of several afterburner configurations
"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 fuel-air ratios at diffuser-inlet total pressures from 2750 to 620 pounds per square foot" (p. 1).
Date:
July 9, 1953
Creator:
Conrad, E. William; Schultz, Frederick W. & Usow, Karl H.
System:
The UNT Digital Library
Investigation of a Ram-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower
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.
System:
The UNT Digital Library
Effects of finite span on the section characteristics of two 45 degree sweptback wings of aspect ratio 6
Report presenting a study of the finite-span effects on the local loading characteristics of two sweptback wings at low speed in order to provide some information about the usefulness of two-dimensional section data and span-loading theory for determining the section characteristics of a swept wing. At low values of lift coefficient, the finite-span effects were restricted to regions of the wing close to the root and tip. Results regarding the local pressure-distribution comparisons, local lift-curve comparisons, and evaluation of surface-loading procedure are provided.
Date:
September 1953
Creator:
Hunton, Lynn W.
System:
The UNT Digital Library
Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects
Note presenting a solution to second order in thickness derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency.
Date:
July 1953
Creator:
Van Dyke, Milton D.
System:
The UNT Digital Library
Linearized potential theory of propeller induction in a compressible flow
Report presenting the potential of the linearized flow for a lifting-line propeller of arbitrary circulation distribution at subsonic advance as derived in cylindrical harmonics. From the potential the induced angle at the lifting line is obtained.
Date:
September 1953
Creator:
Davidson, Robert E.
System:
The UNT Digital Library
Velocity potential and air forces associated with a triangular wing in supersonic flow, with subsonic leading edges, and deforming harmonically according to a general quadratic equation
Report presenting the velocity potential for a triangular wing with subsonic leading edges experiencing harmonic deformations in supersonic flow. The oscillations considered are such that the amplitude of wing distortion can be represented by a general quadratic expression for a surface.
Date:
September 1953
Creator:
Watkins, Charles E. & Berman, Julian H.
System:
The UNT Digital Library
A flight investigation of the effect of steady rolling on the natural frequencies of a body-tail combination
Report presenting flight experiments with a freely falling model to observe the effects of steady rolling on the pitching and yawing motions of a body-tail combination. Steady rolling introduces yawing moments into the pitch oscillations and pitching motions into the yaw oscillations. Results regarding the experimental effects of steady-roll on no-roll natural frequencies, comparison of measured and experimental effects of steady rolling on the no-roll natural frequencies, and effects of roll as applied to the design of missiles are provided.
Date:
August 1953
Creator:
Bergrun, Norman R. & Nickel, Paul A.
System:
The UNT Digital Library
Effect of blade-thickness taper on axial-velocity distribution at the leading edge of an entrance rotor-blade row with axial inlet, and the influence of this distribution on alignment of the rotor blade for zero angle of attack
Report presenting a method for estimating the effect of blade-thickness taper on the inlet axial-velocity distribution of an entrance rotor-blade row with an axial inlet, and the influence of this velocity distribution on the alignment of the rotor blade for zero effective angle of attack. The method is developed for compressible and incompressible nonviscous fluids, and results are presented for incompressible flow into a plane, two dimensional cascade and for compressible flow into an entrance rotor-blade row with tapered blades.
Date:
August 1953
Creator:
Stanitz, John D.
System:
The UNT Digital Library
One-Dimensional, Compressible, Viscous Flow Relations Applicable to Flow in a Ducted Helicopter Blade
Report presenting one-dimensional, steady-state, compressible, viscous flow relations which permit the determination of flow conditions at any radial position in a ducted helicopter blade. The relations are required for estimating the performance of proposed helicopter jet-propulsion systems which involve ducting air or gases through the blade from root to tip.
Date:
December 1953
Creator:
Henry, John R.
System:
The UNT Digital Library
Survey of Portions of the Iron-Nickel-Molybdenum and Cobalt-Iron-Molybdenum Ternary Systems at 1200 Degrees C
Note presenting a survey of the 1200 degrees Celsius isothermal sections of the iron-nickel-molybdenum and the cobalt-iron-molybdenum ternary systems. The phases occurring in the systems were identified by means of x-ray diffraction and by etching methods, and the phase boundaries at 1200 degrees Celsius were determined microscopically, using the disappearing phase method with quenched specimens. Results regarding the specific phases and phase diagrams are provided.
Date:
February 1953
Creator:
Das, Dilip K. & Beck, Paul A.
System:
The UNT Digital Library
The compressible laminar boundary layer with heat transfer and small pressure gradient
Report presenting a perturbation method for the calculation of velocity and temperature profiles and skin-friction and heat-transfer characteristics for two-dimensional, compressible laminar boundary layers with heat transfer and a small arbitrary pressure gradient is presented. The combined effects of heat transfer and pressure gradient on boundary-layer characteristics are demonstrated by applying the results of the analysis to two representative wings.
Date:
October 1953
Creator:
Low, George M.
System:
The UNT Digital Library
Evaluation of Gust Response Characteristics of Some Existing Aircraft With Wing Bending Flexibility Included
Report presenting calculation studies to evaluate the influence that wing bending flexibility has on the structural response to gusts for three twin-engine transports and one four-engine bomber. The manner in which dynamic response factors for acceleration and bending moment vary with different assumed airplane operational factors is shown.
Date:
February 1953
Creator:
Kordes, Eldon E. & Houbolt, John C.
System:
The UNT Digital Library
A Fundamental Investigation of Fretting Corrosion
Note presenting a summary of all phases of an investigation of fretting corrosion that has been conducted over a period of several years. Part I describes a test machine for measuring fretting damage under controlled experimental conditions. Part II presents data for mild steel fretted against itself, with a number of characteristics taken into consideration. Part III suggest a mechanism for the fretting process.
Date:
December 1953
Creator:
Uhlig, H. H.; Feng, I. Ming; Tierney, W. D. & McClellan, A.
System:
The UNT Digital Library