Vortex-Generating Shock Control Bumps for Robust Drag Reduction at Transonic Speeds

What is it about?

Drag reduction for aircraft wings are crucial for future greener air transport with reduced emission. Shock control bumps are passive devices that can effectively reduce the wave drag at transonic speeds through careful design. The robustness of the bump design is hindered by the potential flow separation down stream of the bump at the higher transonic range. An integration of vortex generators with the shock control bump is proposed and investigated in this work to address the robustness problem due to flow separation in shock control.

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