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Performance measurements, flow visualization, and numerical simulation of a crossflow fan

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Author
Seaton, M. Scot.
Date
2003-03
Advisor
Hobson, Garth V.
Second Reader
Shreeve, Raymond P.
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Abstract
A 12-inch diameter, 1.5-inch span crossflow fan test apparatus was constructed and tested using the existing Turbine Test Rig (TTR) as a power source. Instrumentation was installed and a data acquisition program was developed to measure the performance of the crossflow fan. Performance measurements were taken over a speed range of 1,000 to 7,000 RPM. Results comparable to those measured by Vought Systems Division of LTV Aerospace in 1975 were obtained. At 6,000 RPM, a thrust-to-power ratio of one was determined; however, at 3,000 RPM twice the thrust-to-power ratio was measured. Flow visualization was conducted using dye-injection methods. Performance and flow visualization results were compared to predictions obtained from 2-D numerical simulation conducted using Flo++, a commercial PC-based computational fluid dynamics software package by Softflo. A possible design for a light civil V/STOL aircraft was suggested using a similar crossflow fan apparatus for both lift and propulsion.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
URI
http://hdl.handle.net/10945/1065
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    Investigation of performance improvements including application of inlet guide vanes to a cross-flow fan 

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    Experimental investigation of a six inch diameter, four inch span cross-flow fan 

    Ulvin, Jessica M. (Monterey California. Naval Postgraduate School, 2008-06);
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    Experimental and computational investigation of cross-flow fan propulsion for lightweight VTOL aircraft 

    Hobson, Garth V.; Cheng, W.T.; Seaton, M. Scot; Gannon, Anthony; Platzer, Max F. (ASME, 2004-06);
    Cross-flow fan propulsion has not been seriously considered for aircraft use since an Vought Systems Division (VSD) study for the U.S. Navy in 1975. A recent conceptual design study of light-weight, single seat VTOL ...
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