An 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.
Aeroelastic Analysis of a Distributed Electric Propulsion Wing
AIAA SciTech 2017 ; 2017 ; Grapevine, TX, United States
2017-01-09
Aufsatz (Konferenz)
Keine Angabe
Englisch
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