Aeroelastic Analysis of Wind Tunnel Test Data of a Flexible Wing with a Variable Camber Continuous Trailing Edge Flap (VCCTEF)
Authors:
- 2 January 2015
- conference paper
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 8 references indexed in Scilit:
- The design, construction, and tests of a concept aeroelastic wind tunnel model of a high-lift variable camber continuous trailing edge flap (HL-VCCTEF) wing configuration2015
- Experimental Investigation of a Flexible Wing with a Variable Camber Continuous Trailing Edge Flap Design2014
- Static Aeroelastic Analysis with an Inviscid Cartesian Method2014
- Static Aeroelastic and Longitudinal Trim Model of Flexible Wing Aircraft Using Finite-Element Vortex-Lattice Coupled Solution2014
- Coupled Vortex-Lattice Flight Dynamic Model with Aeroelastic Finite-Element Model of Flexible Wing Transport Aircraft with Variable Camber Continuous Trailing Edge Flap for Drag Reduction2013
- Elastically Shaped Wing Optimization and Aircraft Concept for Improved Cruise Efficiency2013
- A Mission Adaptive Variable Camber Flap Control System to Optimize High Lift and Cruise Lift to Drag Ratios of Future N+3 Transport Aircraft2013
- Introduction to Structural Dynamics and Aeroelasticity2002