This contribution presents the implementation and the results of non-linear folding wing tip on a transport aircraft wing at gust impact. Unsteady Reynolds averaged Navier-Stokes -simulation are conducted to evaluate the gust alleviation potential. The wing consists of a rigid inner wing, a transition element and a non-linear folding wing tip. The numerical simulations are conducted in cruise flight condition at an altitude of \(h=35\;000\;ft\) , lift coefficient of \(C_L=0.53 \) and a free-stream Mach number of \(Ma_{\infty } = 0.78\) . The gust is characterized by a 1-cosine shape defined within certification specifications CS25. A sensitivity analysis evaluates the effect of the flare angle \(\varLambda =45^\circ \) on the lift coefficient, the lift distribution, pressure distribution at the wing surface as well as the wing root bending moment. At maximum gust impact a root bending moment reduction at maximum gust impact of \(\varDelta C_{wrbm}=8\%\) and a \(\varDelta C_{L,WTP}=26\%\) is achieved. The peak load on the wing is significantly lowered by the folding wing tip and show to possess potential gust load alleviation.