Work2009

Robust Airfoil Design with Respect to Boundary Layer Transition

Liangyu Zhao · W. N. Dawes · Geoffrey Thomas Parks · Jerome Jarrett · Shuxing Yang

10 citations0/0 files storedAIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference (SDM)

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Probabilistic and Robust Engineering Design Computational Fluid Dynamics and Aerodynamics Advanced Multi-Objective Optimization Algorithms

Abstract

In order to disign an airfoil of which maximum lift coefficient (CLmax) is not sensitive to location of forced top boundary layer transition. Taking maximizing mean value of CLmax and minimizing standard deviation as biobjective, leading edge radius, manximum thick-ness and its location, maximum camber and its location as deterministic design variables, location of forced top boundary layer transition as stochastic variable, XFOIL as deter-ministic CFD solver, non-intrusive polynomial chaos as substitute of Monte Carlo method, we completed a robust airfoil design problem. Results demonstrate performance of initial airfoil is enhanced through reducing standard deviation of CLmax. Besides, we also know maximum thickness has the most dominating effect on mean value of CLmax, location of maximum thickness has the most dominating effect on standard deviation of CLmax, maxi-mum camber has a little effect on both mean value and standard deviation, and maximum camber is the only element of which increase can lead increase of mean value and standard deviation at the same time. Nomenclature AOA angle of attack

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References

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