M Mohamed’s scientific contributions

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Publications (1)


Figure 1. Computation domain dimensions.
Figure 2. Domain grid topology.
Figure 3. The coefficient of lift of NACA 6409 section wing in ground effect at various ground clearances with different turbulence models. (Djavareshkian et al. 2011).
Figure 4. Wing geometrical parameters; sweep, twist, taper, and anhedral. and Reynolds number = 3.4 × 10E + 5, these characteristics were compared with experimental data and previous simulation using the same turbulence model Spallart Allmaras. The results showed good agreement with experimental data and perfect agreement with (Djavareshkian et al. 2011) similar simulation. In order to preserve mesh independency an investigation of elements number effect on the results was carried out as shown in Figure 5, which represents a variation within 0.3% to 0.7% between Numerical and experimental coefficient of lift and 15% to 17%
Figure 6. Drag coefficient, lift coefficient, and aerodynamic efficiency at different twist angles.

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Effect of wing geometrical parameters on the aerodynamic performance of wing in ground marine craft
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July 2020

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M Mohamed

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The aerodynamic performance of a 3-D NACA 6409 wing in ground effect was examined numerically with different wing configurations. The influence of changing twist angles, anhedral angles, taper ratios, and sweep angles on the aerodynamic performance was examined and compared with based model. Structured mesh domains were built, and RANS turbulence model Spalart-Allmaras was solved with a commercial solver. Base model numerical results show good agreement with available experimental data. The results show that wash-in twist has a positive effect on wing aerodynamic performance near ground proximity, as well as anhedral angles. Although swept wings have a negative effect on aerodynamic efficiencies compared with non-swept wings, an optimum swept twisted wing configuration was proposed to achieve higher aerodynamic efficiency, while applying wing sweep. Tapered wings produced a slight increase in aerodynamic efficiency in a narrow range of taper ratios. Speed variation has no drastic or abrupt effect on results.

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