Pressure and flow field study at Mach number 8 of flow separation on a flat plate with deflected trailing edge flap
Static pressure and flow field for flat plate model with short trailing-edge flap
Johnson, C. B.↗
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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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Experimental evaluation of outer casing blowing or bleeding of single stage axial flow compressor. Part 2 - Performance of plain casing insert configuration with undistorted inlet flow and boundary layer trip
Outer casing blowing and bleeding and undistorted inlet flow for improved performance of high aspect ratio transonic rotor
Koch, C. C.↗
Axial flow compressor design computer programs incorporating full radial equilibrium. Part 1 - Flow path and radial distribution of energy specified /program 2/
Complete radial equilibrium flow computer program
Carmody, R. H.↗
A simplified statistical description of turbulent chemically reacting flows /couette flow/
Turbulence model for statistical analysis of fluid dynamics of eddies in chemically reacting flow
Chung, P. M.↗
Electron beam flow visualization in hypersonic helium flow.
Electron beam fluorescence probe and afterglow investigation for hypersonic He flow visualization, observing qualitative structure
Henderson, A., Jr.↗
Separation and flow reversal in swirling flows in circular ducts.
Laminar flow swirling motion in circular duct, studying separation and reversal
Fejer, A. A.↗
Experimental study of high-enthalpy shock- tunnel flow. II - Nozzle-flow characteristics.
Uniform flow and wall boundary layer growth measurement in conical nozzle of reflected shock tunnel operating at high enthalpy conditions
Dunn, M. G.↗
Experimental study of high-enthalpy shock- tunnel flow. I - Shock-tube flow and nozzle starting time.
High enthalpy shock tube and nozzle gas flows for incident shock Mach numbers analyzed for laminar boundary layers and boundary layer transitions
Dunn, M. G.↗
Exploratory experimental study of the effects of inlet conditions on the flow and containment characteristics of coaxial flows
Short chamber inlet configuration for eddy elimination in coaxial flow reactor of gaseous core nuclear rockets
Johnson, B. V.↗
Subsonic flow and supersonic cross-flow near the center portion of a wing Final technical report
Analysis of supersonic conical flow and solutions for subsonic region on compression side of delta wing
Chiang, C. W.↗
Noise from underexpanded axisymmetric jet flows using radial jet flow impingement
Acoustic radiation from underexpanded supersonic main jet flow from nozzle impinged upon by annular jet
Dosanjh, D. S.↗
Some aspects of two phase flows with mixing and combustion in bounded and unbounded flows
Multiphase two dimensional mixing and combustion of flow fields suspended in gaseous medium for propulsion systems problems, obtaining governing equations
Edelman, R. B.↗
The influence of initial flow direction on the turbulent base pressure in supersonic axisymmetric flow
Turbulent base pressure on conical afterbodies in supersonic axisymmetric flow, including initial direction effect
Hall, C. R., Jr.↗
Flow resistance of perforated plates in tangential flow
Changes in acoustic properties of perforated plates resulting from interaction of flows normal and tangential to plate surface
Budoff, M.↗
Influence of initial flow direction on the turbulent base pressure in supersonic axisymmetric flow
Turbulent base pressure on conical afterbodies in supersonic axisymmetric flow, including initial direction effect
Hall, C. R., Jr.↗
Some aspects of two-phase flows with mixing and combustion in bounded and unbounded flows
Multiphase two dimensional mixing and combustion of flow fields suspended in gaseous medium for propulsion systems problems, obtaining governing equations
Edelman, R. B.↗
An analytical study of the effect of coolant flow variables on the kinetic energy output of a cooled turbine blade flow
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.
Prust, H. W., Jr.↗
Gravity flow of powder in a lunar environment. Part 2: Analysis of flow initiation
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.
Pariseau, W. G.↗