2D and 3D Unsteady Aerodynamic Analysis of a Very Light Aircraft's Wing

Date

2023-7-17

Author

Anılır, Berkan

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The aim of this thesis is to investigate the unsteady aerodynamics of designed Very Light Aircraft (VLA)’s wing starting from its airfoil to whole wing with numerical simulations. In this regard, Unsteady Reynolds-averaged Navier-Stokes (URANS) simulations have been performed for a single 2D SD7062 airfoil, 2D SD7062 airfoil with a 0.30c high cambered single-slotted flap and 3D Very Light Aircraft’s wing. In 2D SD7062 airfoil simulation at cruise Reynolds number of 5×106, the aerodynamic coefficients, laminar separation bubble parameters, time-averaged velocity streamlines and vortex patterns are revealed and discussed in detail. Also, two-dimensional analyses are compared with the three-dimensional analyses at various pre- and post-stall regimes. In 2D SD7062 airfoil with a flap simulations at cruise, takeoff and landing condition, the influence of flap deflection on the aerodynamic coefficients and unsteady flowfiled are observed. The optimum gap size at landing condition with 40° flap deflection is studied to reach the maximum lift coefficient. In 3D wing simulations at cruise condition, the impact of taper ratio, dihedral angle and wing tip shape on the aerodynamics of a Very Light Aircraft’s wing has been investigated. Since the post-stall regimes are also explored, the stall cell formation is observed just above the stall angle as evident in the mean surface streamlines. The stall cell characteristics with respect to different wing design variables and angles of attack are represented and their effects on the sectional lift distributions and total aerodynamic coefficients are discussed.

Subject Keywords

Unsteady flow, Computational fluid dynamics, Very Light Aircraft, SD7062, Wing design

URI

https://hdl.handle.net/11511/104827

Collections

Graduate School of Natural and Applied Sciences, Thesis