Parallel optimization of flapping airfoils in a biplane configuration for maximum thrust

Date

2004-05-27

Author

Tuncer, İsmail Hakkı

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Flapping airfoils in a biplane configuration are optimized for a maximum thrust production. A parallel Navier-Stokes solver on overset grids and a gradient based parallel optimization method are employed. The periodic flapping motion of airfoils in a plane configuration is described in a combined pitch and plunge. The pitch and plunge amplitudes and the phase shift between them are optimized for a range of flapping frequencies. It is shown that at low flapping frequencies, flapping airfoils in a biplane configuration produce more thrust than a single flapping airfoil. However, at high flapping frequencies the pitch amplitude tends to go to zero, which promotes an early leading edge vortex formation and limits the thrust production.

Subject Keywords

Optimization problems, Unsteady flows, Domain decomposition

URI

https://hdl.handle.net/11511/53208

Conference Name

6th International Conference on Parallel Computational Fluid Dynamics

Collections

Department of Aerospace Engineering, Conference / Seminar

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Parallel computation of flows around flapping airfoils in biplane configuration Tuncer, İsmail Hakkı; Kaya, Muhammed Çağrı (2002-05-22) Unsteady, laminar flows over flapping airfoils in biplane configuration are computed on overset grids. The overset grid solutions are obtained in parallel in a cluster environment. It is shown that airfoils in biplane configuration and oscillating in pitch and plunge with a proper phase shift between them enhance the thrust production significantly.
Path optimization of flapping airfoils based on unsteady viscous flow solutions Kaya, Mustafa; Tuncer, İsmail Hakkı; Department of Aerospace Engineering (2008) The flapping path of a single airfoil and dual airfoils in a biplane configuration is optimized for maximum thrust and/or propulsive efficiency. Unsteady, low speed viscous flows are computed using a Navier-Stokes solver in a parallel computing environment. A gradient based algorithm and Response Surface Methodology (RSM) are employed for optimization. The evaluation of gradient vector components and the design of experiments for RSM, which require unsteady solutions, are also carried out in parallel. Paral...
Optimization of aeroelastic flapping motion of thin airfoils in a biplane configuration for maximum thrust Kaya, Mustafa; Tuncer, İsmail Hakkı; Jones, Kevin D.; Platzer, Max F. (2007-01-01) An aeroelastic flapping motion of thin airfoils in a biplane configuration is optimized for maximum thrust. Airfoils are attached to swing arms by an elastic joint, which is model led by a torsional spring. A spring-mass system is employed for the aeroelastic coupling. The stiffness coefficient and the mass moment of inertia of the airfoil are optimized for maximum thrust. A gradient based optimization method is employed in a parallel computing environment. Unsteady, low speed flows are computed in parallel...
Optimization of Flapping Motion Parameters for Two Airfoils in a Biplane Configuration Kaya, Mustafa; Tuncer, İsmail Hakkı; Jones, Kevin D.; Platzer, Max F. (American Institute of Aeronautics and Astronautics (AIAA), 2009-03-01) Flapping motion parameters of airfoils in a biplane configuration are optimized for maximum thrust and/or propulsive efficiency. Unsteady, viscous flowfields over airfoils flapping in a combined plunge and pitch are computed with a parallel flow solver on moving and deforming overset grids. The amplitudes of the sinusoidal pitch and plunge motions and the phase shift between them are optimized for a range of flapping frequencies. A gradient-based optimization algorithm is implemented in a parallel computing...
Path optimization of dual airfoils flapping in a biplane configuration with RSM in a parallel computing environment Kaya, Mustafa; Tuncer, İsmail Hakkı (2011-01-01) The path of dual airfoils in a biplane configuration undergoing a combined, non-sinusoidal pitching and plunging motion is optimized for maximum thrust and/or propulsive efficiency. The non-sinusoidal, periodic flapping motion is described using Non-Uniform Rational B-Splines (NURBS). The Response Surface Methodology (RSM) is employed for the optimization of NURBS parameters in a parallel computing environment. A gradient based optimization algorithm, steepest ascent method is started from the optimum point...

Citation Formats

İ. H. Tuncer, “Parallel optimization of flapping airfoils in a biplane configuration for maximum thrust,” presented at the 6th International Conference on Parallel Computational Fluid Dynamics, Las Palmas Gran Canaria, SPAIN, 2004, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53208.