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The suction control of flow separation of a NACA0012 airfoil is studied numerically for Reynolds number Re=104, angle of attack α = 2 ° , 4°, 6°, and 8°, and Re=105, α = 4 ° . The suppression effects of suction are studied considering many parameters such as suction coefficient, location, angle, hole width, and porosity. The variations in energy consumption and lift–drag ratio during the control process are used for evaluating the control effects.

The deflectable nose missile has a longer range by deflecting its nose to improve its aerodynamic feature. Based on detached eddy simulation (DES), the supersonic flow fields of a missile with deflectable nose are simulated numerically and its aerodynamic force coefficients are calculated under the condition of the deflection angles vary from 0° to 8°, angles of attack, 0°–8°, and mach numbers, 2 to 5. Coupling these aerodynamic coefficients with the plumb plane ballistic equations, the extended flight range has been calculated. Furthermore, the genetic algorithm (GA) is employed for the solution of maximum range of the deflected missile.