Aeroelastic Analysis of a Distributed Electric Propulsion Wing
Aeroelastic Analysis of a Distributed Electric Propulsion Wing
- New search for: S. J. Massey
- New search for: B. K. Stanford
- New search for: C. D. Wieseman
- New search for: J. Heeg
- New search for: S. J. Massey
- New search for: B. K. Stanford
- New search for: C. D. Wieseman
- New search for: J. Heeg
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.
Document information
Aeroelastic Analysis of a Distributed Electric Propulsion Wing
2017
20 pages
Report
No indication
English
Computer Software , Algebra, Analysis, Geometry, & Mathematical Logic , Aircraft , Test Facilities & Equipment , Aeroelasticity , Computational grids , Design analysis , Divergence , Dynamic pressure , Lifting bodies , Electric propulsion , Wing nacelle configurations , Wings , Computational fluid dynamics , Finite element method , Grid refinement (mathematics) , Linear evolution equations , Nastran , Navier-stokes equation , Pitching moments , Reynolds averaging , Structural analysis