Optimized Off-Design Performance of Flexible Wings with Continuous Trailing-Edge Flaps

Speaker: David Rodriguez, Applied Modeling and Simulation Branch, NASA Ames Research Center
February 17, 2015

Presentation

Abstract

This work assesses the potential aerodynamic performance benefits of a variable-camber, continuous-trailing-edge flap system on a generic transport aircraft at off-design conditions. A process to optimize transport wings while addressing static aeroelastic effects is presented. To establish a proper baseline, a transport wing is first aerodynamically optimized at a mid-cruise flight condition using an inviscid, aeroelastic analysis tool. The optimized wing is then analyzed at off-design cruise conditions. The optimization is repeated at these off-design conditions to determine how much performance is lost by the wing optimized solely for the mid-cruise condition. The full-span flap system is then adapted to maximize performance of the mid-cruise-optimized wing at these off-design conditions. The measured improvement is quantified by a comparison with wings designed specifically for the off-design conditions. To evaluate the effects of aeroelasticity on the effectiveness of the flap system, this entire process is performed on both a conventionally stiff wing and a modern, more flexible wing. The results indicate that the flap system allows for recovery of near-optimal performance throughout cruise and is found to be advantageous even for wings with increased flexibility. Moreover, the flaps appear to provide a means for active wave drag reduction during flight.

Biography

David Rodriguez joined the Science & Technology Corporation in late 2012 and is working in the Applied Modeling and Simulation Branch at NASA Ames. He is currently applying multidisciplinary analysis techniques to model and eventually design very flexible wings using the Cart3D Euler flow solver. He received a Bachelor's of Engineering from Georgia Tech in 1991 and a Ph.D. from Stanford University in 2001 under the advisement of Professor Ilan Kroo. His dissertation focused on applying multidisciplinary optimization methods to design boundary layer ingesting inlets for a blended-wing-body configuration.

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