Experimental investigation of flow patterns in radial-outflow vortexes using a rotating-peripheral-wall water vortex tube
Flow distributions in radial outflow vortices using rotating peripheral wall water vortex tube
Travers, A.↗
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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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Visual observations of flow through a radial-bladed centrifugal impeller
Visual observations to find flow distribution and coefficients through radial bladed centrifugal pump impeller
Miller, M. J.↗
Calibration of 30 deg included-angle cone for determining local flow conditions in Mach number range of 1.51 to 3.51
Wind tunnel calibration of 30 deg included angle cone for determination of local values of Mach number, total pressure, and flow distribution
Vahl, W. A.↗
Flow phenomena and separation over highly swept delta wings with trailing-edge flaps at Mach 6.
Hypersonic flow distribution and separation types over highly swept delta wings with trailing edge flaps at Mach 6
Keyes, J. W.↗
Visualization of noise from cold supersonic jets.
Acoustic radiation and flow distributions from cold supersonic jets by shadowgraph visualization, noting sound wave sources
Lowson, M. V.↗
A flow experiment on a curved-porous-wall gas-core reactor geometry
Curved porous wall gas core reactor flow distribution experiment
Lanzo, C. D.↗
Flow field computations for blunt bodies in planetary environments
Numerical analysis on flow distribution around hypersonic blunt body in planetary atmosphere
Byron, S.↗
Flow phenomena and separation over delta wings with trailing-edge flaps at Mach 6.
Hypersonic flow distribution and separation types over highly swept delta wings with trailing edge flaps at Mach 6
Keyes, J. W.↗
The bottom 500 ft. of thunderstorm associated winds
Thunderstorm bottom wind profile model, analyzing flow distribution, isotach, isogon and isotherm characteristics
Goldman, J. L.↗
Study of a Supersonic Diffuser for a Centrifugal Compressor
Flow distribution and performance of supersonic vane diffusers for centrifugal compressors
Papon, A.↗
Experimental evaluation of a honeycomb rotor shroud configuration to improve the stall margin of a 0.5 hub-tip ratio single-stage compressor. Volume 2 - Data supplement
Flow distribution data for solid and honeycomb rotor shrouds to improve stall margin of 0.5 hub tip ratio single stage compressor
Oscarson, R. P.↗
Flow field resulting from forward-facing nozzles exhausting near a large cylindrical body at free-stream Mach numbers of 3.0, 4.5, and 6.0
Measurement of flow distribution caused by forward facing nozzles exhausting near large cylindrical body at hypersonic speed
Martin, J. A.↗
Penetration and spreading of transverse jets of hydrogen in a Mach 2.72 airstream
Schlieren photography of flow distribution for transverse hydrogen jets from flat plate into Mach 2.72 airstream
Billig, F. S.↗
A computational method for unified solutions to the inviscid flow field about blunt bodies
Finite difference method for unified solutions to inviscid supersonic flow distribution about blunt bodies
Aungier, R. H.↗
Time-dependent solutions of nonequilibrium airflow past a blunt body
Multicomponent nonequilibrium air flow past axisymmetric blunt body, calculating flow distribution at various attack angles with time dependent technique
Li, C. P.↗
Design and fabrication of brayton cycle solar heat receiver
A detail design and fabrication of a solar heat receiver using lithium fluoride as the heat storage material was completed. A gas flow analysis was performed to achieve uniform flow distribution within overall pressure drop limitations. Structural analyses and allowable design criteria were developed for anticipated environments such as launch, pressure containment, and thermal cycling. A complete heat receiver assembly was fabricated almost entirely from the refractory alloy, niobium-1% zirconium.
Mendelson, I.↗
Exploratory study of the effects of injection configurations and inlet flow conditions on the characteristics of flow in spherical chambers
Flow visualization studies were conducted to evaluate techniques for injecting simulated-fuel and simulated-propellant gases into a spherical cavity for application to open-cycle gaseous-core nuclear rockets. Preliminary studies were conducted with six simulated-fuel injectors and eight simulated-propellant injection configurations. Additional tests were conducted with the best configuration to determine the effect of weight-flow ratio, gas density ratio, injector location, and flow distribution on the simulated-fuel containment characteristics.
Johnson, B. V.↗
Surface pressure and inviscid flow field properties of the McDonnell-Douglas delta-wing orbiter for nominal Mach number of 8, Volume 1
The results of a wind tunnel test program to determine the surface pressures and flow distribution on the McDonnell Douglas Orbiter configuration are presented. Tests were conducted in hypersonic wind tunnel at Mach 8. The freestream unit Reynolds number was 3.7 time one million per foot. Angle of attack was varied from 10 degrees to 60 degrees in 10 degree increments.
Warmbrod, J. D.↗