Numerical simulation and optimization of junction separation for a verification aircraft postprint

Abstract: The junction flow separation structure can be induced at the junction of aircraft components. Especially for a T-type tail aircraft,the junction separation flow may lead to directional instability under small sideslip angle.The k-ω SST-QCR method is used to analyze the corner separation at the T-type tail junction of a verify aircraft,and to suppress the flow separation caused by the complex interaction of the boundary layer.Results show the separation flow on the leeward side of the vertical tail causes the directional instability.The corner flow separation can be suppressed by using the fairing cone at the junction,so that the aircraft can maintain the directional stability at a small sideslip angle.