Zobrazeno 1 - 10
of 11
pro vyhledávání: '"Alvin E. Buggele"'
Publikováno v:
Optics and Lasers in Engineering. 27:543-570
Flow diagnostics based on molecular Rayleigh scattering are discussed along with the results of a feasibility study to non-intrusively measure flow properties in a small supersonic wind tunnel. The technique uses an injection seeded, frequency double
Autor:
Arthur J. Decker, Alvin E. Buggele
Publikováno v:
AIAA Journal. 34:421-423
Artificial neural networks were used successfully to sequence operations in a small, recently modernized, supersonic wind tunnel at NASA-Lewis Research Center. The neural nets generated correct estimates of shadowgraph patterns, pressure sensor readi
Autor:
Alvin E. Buggele, Richard G. Seasholtz
Publikováno v:
SPIE Proceedings.
Filtered Rayleigh Scattering and shadowgraph flow visualization were used to characterize the penetration of helium or moist air injected transversely at several pressures to a Mach 3 flow in the NASA Lewis 3.81 inch by 10 inch continuous flow supers
Autor:
Richard G. Seasholtz, Alvin E. Buggele
Publikováno v:
SPIE Proceedings.
Filtered Rayleigh scattering using iodine absorption cells is an effective technique for obtaining density, temperature, and velocity measurements in high speed confined flows. By tuning a single frequency laser to a strong iodine absorption line, st
Publikováno v:
SPIE Proceedings.
Results of a feasibility study to apply laser Rayleigh scattering to non-intrusively measure flow properties in a small supersonic wind tunnel are presented. The technique uses an injection seeded, frequency doubled Nd:YAG laser tuned to an absorptio
Publikováno v:
17th Aerospace Ground Testing Conference.
The Engine Components Instrumentation Development Facility at NASA Lewis is a unique aeronautics facility dedicated to the development of innovative instrumentation for turbine engine component testing. Containing two separate wind tunnels, the facil
Publikováno v:
AIAA Journal. 20:1146-1148
Rapid double-pulse holography was employed to obtain detailed, two-dimensional images of the shock forming during simulated flutter in a transonic flowfield. The experiment comprised a linear cascade of airfoils externally oscillated in torsion and v
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