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Application of a Momentum Source Model to the RAH-66 Comanche FANTAILA Momentum Source Model has been revised and implemented in the flow solver OVERFLOW-D. In this approach, the fan forces are evaluated from two-dimensional airfoil tables as a function of local Mach number and angle-of-attack and applied as source terms in the discretized Navier-Stokes equations. The model revisions include a new model for forces in the tip region and axial distribution of the source terms. The model revisions improve the results significantly. The Momentum Source Model agrees well with a discrete blade model for all computed collective pitch angles. The two models agree well with experimental data for thrust vs. torque. The Momentum Source Model is a good complement to Discrete Blade Models for ducted fan computations. The lower computational and labor costs make parametric studies, optimization studies and interactional aerodynamics studies feasible for cases beyond what is practical with a Discrete Blade Model today.
Document ID
20040086885
Acquisition Source
Ames Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Nygaard, Tor A. (Eloret Corp. Moffett Field, CA, United States)
Dimanlig, Arsenio C. (Eloret Corp. Moffett Field, CA, United States)
Meadowcroft, Edward T. (Boeing Co. Ridley Park, PA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2004
Subject Category
Aerodynamics
Meeting Information
Meeting: American Helicopter Society 4th Decennial Specialist Conference on Aeromechanics
Location: San Francisco, CA
Country: United States
Start Date: January 21, 2004
End Date: January 23, 2004
Sponsors: American Helicopter Society, Inc.
Funding Number(s)
CONTRACT_GRANT: NAS2-00062
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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