SEARCH · Engineering Papers
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Program analyzes the consequences of a loss-of-flow accident in the primary cooling system of a heterogeneous light-water moderated and cooled nuclear reactor. It produces a temperature matrix 36 x 41 /x,y/ which includes fuel surface temperatures relative to the time the pump power was lost.
Static pressure and flow field for flat plate model with short trailing-edge flap
Outer casing blowing and bleeding and undistorted inlet flow for improved performance of high aspect ratio transonic rotor
Complete radial equilibrium flow computer program
Turbulence model for statistical analysis of fluid dynamics of eddies in chemically reacting flow
Electron beam fluorescence probe and afterglow investigation for hypersonic He flow visualization, observing qualitative structure
Laminar flow swirling motion in circular duct, studying separation and reversal
Uniform flow and wall boundary layer growth measurement in conical nozzle of reflected shock tunnel operating at high enthalpy conditions
High enthalpy shock tube and nozzle gas flows for incident shock Mach numbers analyzed for laminar boundary layers and boundary layer transitions
Short chamber inlet configuration for eddy elimination in coaxial flow reactor of gaseous core nuclear rockets
Analysis of supersonic conical flow and solutions for subsonic region on compression side of delta wing
Acoustic radiation from underexpanded supersonic main jet flow from nozzle impinged upon by annular jet
Multiphase two dimensional mixing and combustion of flow fields suspended in gaseous medium for propulsion systems problems, obtaining governing equations
Turbulent base pressure on conical afterbodies in supersonic axisymmetric flow, including initial direction effect
Changes in acoustic properties of perforated plates resulting from interaction of flows normal and tangential to plate surface
Turbulent base pressure on conical afterbodies in supersonic axisymmetric flow, including initial direction effect
Multiphase two dimensional mixing and combustion of flow fields suspended in gaseous medium for propulsion systems problems, obtaining governing equations
The results of an analytical study to determine the effect of changes in the amount, velocity, injection location, injection angle, and temperature of coolant flow on blade row performance are presented. The results show that the change in output of a cooled turbine blade row relative to the specific output of the uncooled blade row can be positive, negative, or zero. Comparisons between the analytical results and experimental results for four different cases of coolant discharge, all at a coolant temperature ratio of unity, show good agreement for three cases and rather poor agreement for the other. To further test the validity of the method, more experimental data is needed, particularly at different coolant temperature ratios.