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Aeroelastic Analysis of a Distributed Electric Propulsion WingAn aeroelastic analysis of a prototype distributed electric propulsion wing is presented. Results using MSC Nastran (Registered Trademark) doublet lattice aerodynamics are compared to those based on FUN3D Reynolds Averaged Navier- Stokes aerodynamics. Four levels of grid refinement were examined for the FUN3D solutions and solutions were seen to be well converged. It was found that no oscillatory instability existed, only that of divergence, which occurred in the first bending mode at a dynamic pressure of over three times the flutter clearance condition.
Document ID
20170001034
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Massey, Steven J. (NASA Langley Research Center Hampton, VA, United States)
Stanford, Bret K. (NASA Langley Research Center Hampton, VA, United States)
Wieseman, Carol D. (NASA Langley Research Center Hampton, VA, United States)
Heeg, Jennifer (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
January 31, 2017
Publication Date
January 9, 2017
Subject Category
Numerical Analysis
Aircraft Design, Testing And Performance
Computer Programming And Software
Report/Patent Number
NF1676L-24611
Report Number: NF1676L-24611
Meeting Information
Meeting: AIAA SciTech 2017
Location: Grapevine, TX
Country: United States
Start Date: January 9, 2017
End Date: January 13, 2017
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 432938.11.01.07.43.40.08
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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