You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15281 - 15290 of 17,421
  |   |  
Thermal fatigue of ductile materials II : effect of cyclic thermal stressing on the stress-rupture life and ductility of S-816 and Inconel 550.

Thermal fatigue of ductile materials II : effect of cyclic thermal stressing on the stress-rupture life and ductility of S-816 and Inconel 550.

Date: September 1, 1958
Creator: Clauss, Francis J & Freeman, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Torque-speed characteristics for high-specific-work turbines

Torque-speed characteristics for high-specific-work turbines

Date: September 1, 1958
Creator: Stewart, Warner L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: September 1, 1958
Creator: Trimpi, Robert L & Jones, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Turbulent Boundary Layer on a Rough Curvilinear Surface

The Turbulent Boundary Layer on a Rough Curvilinear Surface

Date: September 1, 1958
Creator: Droblenkov, V. F.
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Use of short flat vanes for producing efficient wide-angle two-dimensional subsonic diffusers

Use of short flat vanes for producing efficient wide-angle two-dimensional subsonic diffusers

Date: September 1, 1958
Creator: Cochran, D L & Kline, S J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of the Coanda effect for jet deflection and vertical lift with multiple-flat-plate and curved-plate deflection surfaces

Use of the Coanda effect for jet deflection and vertical lift with multiple-flat-plate and curved-plate deflection surfaces

Date: September 1, 1958
Creator: Von Glahn, Uwe H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of the Kernel function in a three-dimensional flutter analysis with application to a flutter-tested delta-wing model

Use of the Kernel function in a three-dimensional flutter analysis with application to a flutter-tested delta-wing model

Date: September 1, 1958
Creator: Woolston, Donald S & Sewall, John L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Water-impact theory for aircraft equipped with nontrimming hydro-skis mounted on shock struts

Water-impact theory for aircraft equipped with nontrimming hydro-skis mounted on shock struts

Date: September 1, 1958
Creator: Schnitzer, Emanuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: September 1, 1958
Creator: Mccloud, John L , III & Mccullough, George B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Date: September 4, 1958
Creator: Stepka, Francis S
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department