Abstract: The flight regime of modern transport aircraft, is at transonic speeds, in terms of Mach number M∞ = 0.75-0.85 and at very high Reynolds numbers. The transonic flow occurs when the two regimes of subsonic and supersonic flows occur in the same local flow field. It is characterized by the development of a supersonic pocket, delimited by the wall on the one hand and by the sonic line on the upper surface of the wing on the other hand. The appearance of a supersonic pocket on the under-surface of the wing is also possible; all depends on the incidence angle and the geometrical form of the wing. This work is devoted to the evaluation and the validation of the numerical results resulting from transonic calculation of flow around a NACA0012 aerofoil, then around a wing 3d having the same basic airfoil. All calculations are executed by using the turbulence models of two equations k-ε, k-ω and SST k-w.

Key words: Transonic flow, Numerical simulation, Aerofoil NACA0012, Mach wave, unmanned aircraft vehicle (UAV)