### Abstract

A numerical method is developed to solve the solutions of the Euler/Navier-Stokes equations for investigating the flowfileds of the flapping wings. It uses a third-order modified Osher-Chakravarthy (MOC) upwind finite-volume scheme for the convective terms and a second-order central finite-volume scheme for the viscous terms. A Diagonal Dominant Alternating Direction Implicit scheme (DDADI) coupling with an implicit residual smoothing is used for the time integration to achieving fast convergence of the proposed numerical method. The Baldwin-Lomax algebraic turbulent model is applied for calculating the turbulence flows at high Reynolds numbers. Quantitative and understanding simulations as a function of the plunging frequency, mean angle of attack, plunging amplitude and pitching angle are calculated. It is found that the mean thrust output and propulsion efficiency are independent of the mean angle of attack but dependent of the reduce frequency. The mean lift is linear shift while increasing the mean angle of attack.

Original language | English |
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Title of host publication | 33rd AIAA Fluid Dynamics Conference and Exhibit |

Publication status | Published - 2003 Dec 1 |

Event | 33rd AIAA Fluid Dynamics Conference and Exhibit 2003 - Orlando, FL, United States Duration: 2003 Jun 23 → 2003 Jun 26 |

### Publication series

Name | 33rd AIAA Fluid Dynamics Conference and Exhibit |
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### Other

Other | 33rd AIAA Fluid Dynamics Conference and Exhibit 2003 |
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Country | United States |

City | Orlando, FL |

Period | 03-06-23 → 03-06-26 |

### Fingerprint

### All Science Journal Classification (ASJC) codes

- Fluid Flow and Transfer Processes
- Energy Engineering and Power Technology
- Aerospace Engineering
- Mechanical Engineering

### Cite this

*33rd AIAA Fluid Dynamics Conference and Exhibit*(33rd AIAA Fluid Dynamics Conference and Exhibit).

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*33rd AIAA Fluid Dynamics Conference and Exhibit.*33rd AIAA Fluid Dynamics Conference and Exhibit, 33rd AIAA Fluid Dynamics Conference and Exhibit 2003, Orlando, FL, United States, 03-06-23.

**Numerical study of flapping wing.** / Lin, San-Yih; Hu, Jeu Jiun.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

TY - GEN

T1 - Numerical study of flapping wing

AU - Lin, San-Yih

AU - Hu, Jeu Jiun

PY - 2003/12/1

Y1 - 2003/12/1

N2 - A numerical method is developed to solve the solutions of the Euler/Navier-Stokes equations for investigating the flowfileds of the flapping wings. It uses a third-order modified Osher-Chakravarthy (MOC) upwind finite-volume scheme for the convective terms and a second-order central finite-volume scheme for the viscous terms. A Diagonal Dominant Alternating Direction Implicit scheme (DDADI) coupling with an implicit residual smoothing is used for the time integration to achieving fast convergence of the proposed numerical method. The Baldwin-Lomax algebraic turbulent model is applied for calculating the turbulence flows at high Reynolds numbers. Quantitative and understanding simulations as a function of the plunging frequency, mean angle of attack, plunging amplitude and pitching angle are calculated. It is found that the mean thrust output and propulsion efficiency are independent of the mean angle of attack but dependent of the reduce frequency. The mean lift is linear shift while increasing the mean angle of attack.

AB - A numerical method is developed to solve the solutions of the Euler/Navier-Stokes equations for investigating the flowfileds of the flapping wings. It uses a third-order modified Osher-Chakravarthy (MOC) upwind finite-volume scheme for the convective terms and a second-order central finite-volume scheme for the viscous terms. A Diagonal Dominant Alternating Direction Implicit scheme (DDADI) coupling with an implicit residual smoothing is used for the time integration to achieving fast convergence of the proposed numerical method. The Baldwin-Lomax algebraic turbulent model is applied for calculating the turbulence flows at high Reynolds numbers. Quantitative and understanding simulations as a function of the plunging frequency, mean angle of attack, plunging amplitude and pitching angle are calculated. It is found that the mean thrust output and propulsion efficiency are independent of the mean angle of attack but dependent of the reduce frequency. The mean lift is linear shift while increasing the mean angle of attack.

UR - http://www.scopus.com/inward/record.url?scp=84894606753&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84894606753&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9781624100956

T3 - 33rd AIAA Fluid Dynamics Conference and Exhibit

BT - 33rd AIAA Fluid Dynamics Conference and Exhibit

ER -