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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.
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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.
A small displacement-small strain finite element technique utilizing the constant strain triangle and incremental constitutive equations for elasticplastic (media nonhardening and obeying a Coulomb yield condition) was applied to the analysis of gravity flow initiation. This was done in a V-shaped hopper containing a powder under lunar environmental conditions. Three methods of loading were examined. Of the three, the method of computing the initial state of stress in a filled hopper prior to drawdown, by adding material to the hopper layer by layer, was the best. Results of the analysis of a typical hopper problem show that the initial state of stress, the elastic moduli, and the strength parameters have an important influence on material response subsequent to the opening of the hopper outlet.
Results of an experimental and numerical investigation of tangential swept slot injection (sweep angles of 22.5 and 45 deg) into a thick turbulent boundary layer at Mach 6 are presented. Film cooling effectiveness, skin friction, and flow structure downstream of the swept slot injection are investigated. The data are compared to that for unswept slots, and it is found that cooling effectiveness and skin-friction reductions are not significantly affected by sweeping the slot. Predictions of cooling effectiveness and skin friction obtained by a numerical finite-difference technique agree reasonably well with experimental surface variables. As in previous supersonic two-dimensional slot research, reduced mixing was found downstream of the slot lip in the present three-dimensional case.