Computational Aerodynamics Analysis of a Light Aircraft | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 6, Volume 15, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013, May 2013, Page 1-8 PDF (912.52 K) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.21882 | ||||
 View on SCiNiTO | ||||
| Author | ||||
| M. M. Abdulla | ||||
| Researcher, Aeronautical Research Center, Sudan. | ||||
| Abstract | ||||
| Abstract: This work aims to study and simulate the flow field around light a/c using numerical solution based on solving Reynolds Averaged Navier-Stokes equations coupled with K-ω SST turbulence model. Solution strategy began by analyzing wing alone then analyzing the whole a/c configuration. This strategy allows studying the wing flow field carefully and analyzing the vortices which occur over the wing and capture their effective regions at critical design conditions like stall condition. These regions were captured by plotting pressure contours and flow pathlines. The aerodynamic behavior of this aircraft was investigated at different angles of attack and side slip angles. The x, y and z forces and moments were calculated at flight speed of 50m/s and at sea level conditions. Lift and drag curves for different angles of attack were plotted. The maximum lift coefficient for this a/c was 1.67 which occurred at angle of attack 16o , the maximum lift to drag ratio (L/D) found to be 14 which occurred at α=3o, and the zero lift drag coefficient was 0.0342. Also the yawing moment coefficient was plotted for different side slip angles as well as rolling moment. The longitudinal stability derivatives with respect to angle of attack, speed variation (u), pitch rate (q) and time rate of change of angle of attack were calculated using obtained CFD results. Regarding lateral stability only side slip derivatives were calculated. | ||||
| Keywords | ||||
| Aerodynamics analysis; CFD; static stability | ||||
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