Numerical prediction of aerodynamic stability derivatives of a projectile

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2021-9-07

Author

Yayla, Koray

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Prediction of aircraft aerodynamic stability derivatives is crucial for evaluating its flight dynamic characteristics. By using the open source SU2 software, steady and unsteady Reynolds-Averaged Navier-Stokes analyzes are performed in order to determine the aerodynamic stability derivatives of a missile like projectile from literature. The employed prediction methods that are based on forced oscillatory motion and differential method are particularly emphasized for roll damping and pitch damping derivatives. Also, constant roll rate analyzes are performed with the options of rigid mesh motion and rotating reference frame. Differences between them are evaluated by comparing the results obtained from these different approaches with each other and experimental data. The effects of the Spalart Allmaras and Shear Stress Transport turbulence models on steady and unsteady simulations are examined in terms of accuracy and computational cost. The effects of oscillation method parameters such as reduced frequency, time step size, and oscillation amplitude are also investigated. The numerical prediction of the aerodynamic stability derivatives shows good agreement with the experimental data.

Subject Keywords

Stability derivatives, Damping derivatives, Computational fluid dynamics, Forced oscillation method, Differential method, Rigid mesh motion, Rotating reference frame

URI

https://hdl.handle.net/11511/93161

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Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

K. Yayla, “Numerical prediction of aerodynamic stability derivatives of a projectile,” M.S. - Master of Science, Middle East Technical University, 2021.