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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15251 - 15300 of 17,329
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A theoretical study of stagnation-point ablation.
No Description digital.library.unt.edu/ark:/67531/metadc57245/
The theory of diffusion in strained systems
No Description digital.library.unt.edu/ark:/67531/metadc57442/
Thermal fatigue of ductile materials I : effect of variations in the temperature cycle on the thermal-fatigue of S-816 and inconel 550
No Description digital.library.unt.edu/ark:/67531/metadc56823/
Thermal fatigue of ductile materials II : effect of cyclic thermal stressing on the stress-rupture life and ductility of S-816 and Inconel 550.
No Description digital.library.unt.edu/ark:/67531/metadc56862/
Torque-speed characteristics for high-specific-work turbines
No Description digital.library.unt.edu/ark:/67531/metadc57535/
Transient temperature distribution in a two-component semi-infinite composite slab of arbitrary materials subjected to aerodynamic heating with a discontinuous change in equilibrium temperature or heat-transfer coefficient
No Description digital.library.unt.edu/ark:/67531/metadc57008/
The Turbulent Boundary Layer on a Rough Curvilinear Surface
A number of semiempirical approximate methods exist for determining the characteristics of the turbulent boundary layer on a curvilinear surface. At present, among these methods, the one proposed by L. G. Loitsianskii is given frequent practical application. This method is sufficiently effective and permits, in the case of wing profiles with technically smooth surfaces, calculating the basic characteristics of the boundary layer and the values of the overall drag with an accuracy which suffices for practical purposes. The idea of making use of the basic integral momentum equation ((d delta(sup xx))/dx) + ((V' delta(sup xx))/V) (2 + H) = (tau(sub 0))/(rho V(exp 2)) proves to be fruitful also for the solution of the problems in the determination of the characteristics of the turbulent boundary layer on a rough surface. digital.library.unt.edu/ark:/67531/metadc63908/
Use of short flat vanes for producing efficient wide-angle two-dimensional subsonic diffusers
No Description digital.library.unt.edu/ark:/67531/metadc57055/
Use of the Coanda effect for jet deflection and vertical lift with multiple-flat-plate and curved-plate deflection surfaces
No Description digital.library.unt.edu/ark:/67531/metadc57527/
Use of the Kernel function in a three-dimensional flutter analysis with application to a flutter-tested delta-wing model
No Description digital.library.unt.edu/ark:/67531/metadc57259/
Water-impact theory for aircraft equipped with nontrimming hydro-skis mounted on shock struts
No Description digital.library.unt.edu/ark:/67531/metadc57419/
Wind-tunnel tests of a full-scale helicopter rotor with symmetrical and with cambered blade sections at advance ratios from 0.3 to 0.4
No Description digital.library.unt.edu/ark:/67531/metadc57455/
Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades
Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant properties based on the coolant bulk temperature gave the best agreement with experimental data. The agreement obtained was within 3 percent at the midspan and tip regions of the blade. At the root region of the blade, the agreement was within 3 percent for coolant flows within the turbulent flow regime and within 10 percent for coolant flows in the laminar regime. The calculated and measured cooling-air pressure losses through the blade agreed within 5 percent. Calculated spanwise blade temperatures for assumed turboprop engine operating conditions of 2000 F turbine-inlet gas temperature and flight conditions of 300 knots at a 30,000-foot altitude agreed well with those obtained by the extrapolation of correlated experimental data of a static cascade investigation of these blades. digital.library.unt.edu/ark:/67531/metadc64246/
Comparison of Injectors With a 200-pound-thrust Ammonia-oxygen Engine
Injection techniques for 200-pound thrust ammonia- oxygen rocket engine. digital.library.unt.edu/ark:/67531/metadc52872/
Design and experimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressor rotor designed for 40 pounds per second per unit frontal area
No Description digital.library.unt.edu/ark:/67531/metadc58374/
Thermal reaction of diborane with trimethylborane
No Description digital.library.unt.edu/ark:/67531/metadc64257/
Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane
No Description digital.library.unt.edu/ark:/67531/metadc53282/
Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight
No Description digital.library.unt.edu/ark:/67531/metadc64406/
Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10
Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle. The data also indicate that laminar heating rates over the windward surface of a highly swept flat glider wing at moderate angles of attack can be predicted with reasonable engineering accuracy by flat-plate theory using wedge local flow conditions and basing Reynolds numbers on lengths from the wing leading edge parallel to the surface center line. digital.library.unt.edu/ark:/67531/metadc52943/
Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models
No Description digital.library.unt.edu/ark:/67531/metadc64259/
Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane
No Description digital.library.unt.edu/ark:/67531/metadc64250/
Accidental Radiation Excursion at the Y-12 Plant, June 16, 1958: Final Report
This report describes the circumstances leading to the accident, attempts to reconstruct the nuclear reactivity conditions, and reviews the dosimetric means and results which were used to help determine the exposure of affected employees. digital.library.unt.edu/ark:/67531/metadc173360/
Design and Experimental Investigation of a Single-stage Turbine With a Rotor Entering Relative Mach Number of 2
Design of single-stage turbine for rotor entering at supersonic speed - performance characteristics. digital.library.unt.edu/ark:/67531/metadc52947/
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50
Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7. digital.library.unt.edu/ark:/67531/metadc52983/
The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane
No Description digital.library.unt.edu/ark:/67531/metadc64322/
Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration
No Description digital.library.unt.edu/ark:/67531/metadc64318/
Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18
Aerodynamic performance characteristics and static stability and control of hypersonic glider with arrow planform wings. digital.library.unt.edu/ark:/67531/metadc53064/
Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18
No Description digital.library.unt.edu/ark:/67531/metadc64409/
Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces
Wind tunnel tests of wingless low aspect ratio folding control missile configurations. digital.library.unt.edu/ark:/67531/metadc52945/
Measurements of the buffeting loads on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane
The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane have been measured in the Langley 16-foot transonic tunnel in the Mach number range from 0.40 to 0.90. When the buffeting loads were reduced to a nondimensional aerodynamic coefficient of buffeting intensity, it was found that the maximum buffeting intensity of the horizontal tail was about twice as large as that of the wing. Comparison of power spectra of buffeting loads acting on the horizontal tail of the airplaneand of the model indicated that the model horizontal tail, which was of conventional force-test-model design, responded in an entirely different mode than did the airplane.This result implied that if quantitative extrapolation of model data to flight conditions were desired a dynamically scaled model of the rearward portion of the fuselage and empennage would be required. A study of the sources of horizontal-tail buffeting of the model indicated that the wing wake contributed a large part of the total buffeting load. At one condition it was found that removal of the wing wake would reduce the buffeting loads on the horizontal tail to about one-third of the original value. digital.library.unt.edu/ark:/67531/metadc62852/
Stability investigation of a blunt cone and a blunt cylinder with a square base at Mach numbers from 0.64 to 2.14
No Description digital.library.unt.edu/ark:/67531/metadc64415/
A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance
Effects of manual attack-display noise filtering on pilot tracking performance. digital.library.unt.edu/ark:/67531/metadc52833/
Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external- compression inlet
No Description digital.library.unt.edu/ark:/67531/metadc53222/
Effect of spike-tip and cowl-lip blunting on inlet performance of a Mach 3.0 external-compression inlet
No Description digital.library.unt.edu/ark:/67531/metadc64349/
Experimental investigation of effect of spike- tip and cowl-lip blunting on the internal performance of a two-cone cylindrical-cowl inlet at mach number 4.95
No Description digital.library.unt.edu/ark:/67531/metadc53218/
Experimental Study of Ballistic-Missile Base Heating with Operating Rocket
A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor. Temperature as high as 1200 F was measured in the base region because of the ignition of burnable rocket gases. combustibles that are dumped into the base by accessories seriously aggravate the base-burning temperature rise. digital.library.unt.edu/ark:/67531/metadc52877/
Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet from Mach 2.1 to 3.0
Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg. When the inlet was unstarted, an erroneous signal was obtained from the normal-shock control through most of the starting cycle that prevented the inlet from starting. Therefore, it was necessary to over-ride the normal-shock control signal and not allow the control to position the terminal shock until the spike was positioned. digital.library.unt.edu/ark:/67531/metadc52979/
Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination
No Description digital.library.unt.edu/ark:/67531/metadc64337/
APPR-1 Research and Development Program. Design Analysis for Flow and Temperature Measurement Program, Task No. 5
From objectives: "To establish, by literature search, analysis and design, the engineering and fabrication requirements for modifying reactor components and developing and installing the necessary instrumentation to carry out a fuel temperature and flow measurement experimental program." digital.library.unt.edu/ark:/67531/metadc100964/
Heat Transfer Measured in Free Flight on a Slightly Blunted 25 deg Cone-Cylinder-Flare Configuration at Mach Numbers up to 9.89
Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds. digital.library.unt.edu/ark:/67531/metadc52942/
Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices
No Description digital.library.unt.edu/ark:/67531/metadc64423/
Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5
No Description digital.library.unt.edu/ark:/67531/metadc64332/
Some notes on the probable damage to an intercontinental-ballistic-missile warhead following puncture of the heat shield
No Description digital.library.unt.edu/ark:/67531/metadc53283/
Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine
No Description digital.library.unt.edu/ark:/67531/metadc64263/
Off-Design Performance of Divergent Ejectors
Off-design performance of divergent ejectors. digital.library.unt.edu/ark:/67531/metadc52845/
Off-design performance of divergent ejectors
No Description digital.library.unt.edu/ark:/67531/metadc64402/
Rocket-model investigation to determine the lift and pitching effectiveness of small pulse rockets exhausted from the fuselage over the surface of an adjacent wing at Mach numbers from 0.9 to 1.8
No Description digital.library.unt.edu/ark:/67531/metadc64417/
Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination
No Description digital.library.unt.edu/ark:/67531/metadc64240/
Use of highly reactive chemical additives to improve afterburner performance at altitude
Liquid hydrogen and aluminum trimethyl as highly reactive chemical additives in turbojet afterburner to promote fuel combustion process. digital.library.unt.edu/ark:/67531/metadc52986/
Use of highly reactive chemical additives to improve afterburner performance at altitude
No Description digital.library.unt.edu/ark:/67531/metadc64354/