You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15251 - 15300 of 17,421
  |   |  
On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas
The equations of shells are taken in the form of the general technical theory of shallow shells and shells of medium length. The aerodynamic forces acting on a shell are taken into account only as forces of excess pressure according to the formula proposed by A.A. Iliushin in reference 3. digital.library.unt.edu/ark:/67531/metadc64007/
Ordinates and theoretical pressure-distribution data for NACA 6- and 6A-series airfoil sections with thicknesses from 2 to 21 and from 2 to 15 percent chord, respectively
No Description digital.library.unt.edu/ark:/67531/metadc57141/
A phenomenological theory for the transient creep of metals at elevated temperatures
No Description digital.library.unt.edu/ark:/67531/metadc57260/
Preliminary heat-transfer studies on two bodies of revolution at angle of attack at a Mach number of 3.12
No Description digital.library.unt.edu/ark:/67531/metadc57532/
Procedure for calculating flutter at high supersonic speed including camber deflections, and comparison with experimental results
No Description digital.library.unt.edu/ark:/67531/metadc57367/
Propellant vaporization as a criterion for rocket-engine design : calculations of chamber length to vaporize various propellants
No Description digital.library.unt.edu/ark:/67531/metadc56386/
The rate of fatigue-crack propagation in two aluminum alloys
No Description digital.library.unt.edu/ark:/67531/metadc57256/
Rate of reaction of gaseous fluorine with water vapor at 35 C
No Description digital.library.unt.edu/ark:/67531/metadc57516/
Relationship of metal surfaces to heat-aging properties of adhesive bonds
No Description digital.library.unt.edu/ark:/67531/metadc57118/
Relative motion in the terminal phase of interception of a satellite or a ballistic missile
No Description digital.library.unt.edu/ark:/67531/metadc57277/
Second-order slender-body theory : axisymmetric flow
No Description digital.library.unt.edu/ark:/67531/metadc57032/
Selected Values of the Physical Properties of Various Materials
Report issued by the Argonne National Laboratory discussing selected physical properties of various solids, liquids, and gases of interest in nuclear reactor heat transfer and fluid flow analysis. In most cases, values for thermal conductivity specific heat, density, viscosity, and Prandtl numbers are given as functions of temperature. This report includes tables, and illustrations. digital.library.unt.edu/ark:/67531/metadc67189/
Similar solutions for the compressible boundary layer on a yawed cylinder with transpiration cooling
No Description digital.library.unt.edu/ark:/67531/metadc57205/
Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5
No Description digital.library.unt.edu/ark:/67531/metadc57502/
Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5
No Description digital.library.unt.edu/ark:/67531/metadc53339/
Slip-flow heat transfer from cylinders in subsonic airstreams
No Description digital.library.unt.edu/ark:/67531/metadc57486/
Some numerical solutions of similarity equations for three-dimensional laminar incompressible boundary-layer flows
No Description digital.library.unt.edu/ark:/67531/metadc57493/
Some observations relating to recovery of internal friction during fatigue of aluminum
No Description digital.library.unt.edu/ark:/67531/metadc57497/
Some static longitudinal stability characteristics of an overlapped-type tandem-rotor helicopter at low airspeeds
No Description digital.library.unt.edu/ark:/67531/metadc57251/
Static longitudinal and lateral stability characteristics at low speed of 60 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6
No Description digital.library.unt.edu/ark:/67531/metadc57268/
Study of hydrogen embrittlement of iron by internal-friction methods
No Description digital.library.unt.edu/ark:/67531/metadc57324/
A study of several theoretical methods for computing the zero-lift wave drag of a family of open-nosed bodies of revolution in the Mach number range of 2.0 to 4.0
No Description digital.library.unt.edu/ark:/67531/metadc57465/
Supersonic wave interference affecting stability
No Description digital.library.unt.edu/ark:/67531/metadc57472/
Tables and graphs of normal-shock parameters at hypersonic Mach numbers and selected altitudes
No Description digital.library.unt.edu/ark:/67531/metadc57249/
Tests of ring-stiffened circular cylinders subjected to a transverse shear load
Thirty-four circular cylinders stiffened by heavy rings were loaded to failure in combined bending and shear with a transverse shear load. The results are presented in the form of an interaction curve which is applicable to the design of ring-stiffened cylinders that fail as a result of local buckling. (author). digital.library.unt.edu/ark:/67531/metadc57404/
Theoretical and experimental analysis of the reduction of rotor blade vibration in turbomachinery through the use of modified stator vane spacing
No Description digital.library.unt.edu/ark:/67531/metadc57510/
Theoretical distribution of laminar-boundary-layer thickness, boundary-layer Reynolds number and stability limit, and roughness Reynolds number for a sphere and disk in incompressible flow
No Description digital.library.unt.edu/ark:/67531/metadc57236/
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/