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TECHNICAL PAPERS

Aerodynamic Design and Performance of Aspirated Airfoils

[+] Author and Article Information
Ali Merchant

Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Turbomach 125(1), 141-148 (Jan 23, 2003) (8 pages) doi:10.1115/1.1519834 History: Received October 11, 2001; Online January 23, 2003
Copyright © 2003 by ASME
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References

Figures

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Effect of suction on boundary layer growth
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Controlled diffusion cascade at a highly loaded condition with no suction
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Decrease in momentum thickness with suction at design loading conditions
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Decrease in momentum thickness with suction at high loading conditions
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Effect of aspiration on the loss variation with incidence at design and high loading conditions
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Aspirated blade section with supersonic precompression—(a) surface mach, (b) pressure contours
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Diverging trailing edge concept
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High-speed stage contours of Mach number—(a) rotor 95% span, (b) stator 10% span
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High-speed stage contours of axial speed—(a) rotor exit, (b) stator exit
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High-speed stage mass averaged exit profiles—(a) rotor exit, (b) stator exit
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Low-reaction stage stator mid-span Mach contours
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Low-reaction stage stator exit axial speed contours
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Low-reaction stage mass averaged stator exit profiles
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3-D viscous solution mid-span Mach contours
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3-D viscous solution exit axial speed contours
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3-D viscous solution EGV exit profiles

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