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Decades of research on Supercritical Airfoil were conducted to boost an aircraft's efficiency at High Subsonic Speed. This research work analyzes the simulation on Supercritical wing SC (2)-0714 with Shock Control Bump of various heights at different angles of attack. A comparative study has been performed on aerodynamic characteristics between the models of variable heights. The foils were initially designed in Dassault’s Solidworks and imported to Ansys Fluent to test at Transonic Flow Regimes. The Obtained Results are validated and prove that the Shock Control Bump with low bump height is effective in delaying the drag at Mach 0.85. It is summarized that such Optimized Airfoil offers the maximum Cl and feasible in the Aviation Industry.

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Aerodynamics Analysis on Effects of Various Shock Control Bump Heights at Transonic Flight Regime

  • 会议论文

  • 发表日期：

    2025年

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  • P. Catherine Victoria,
  • G. Balaji,
  • Ullamgunta Nithin Srinivas,
  • Thummalapalli Danesh,
  • Syed Mazz,
  • G. Santhosh Kumar

摘要

Decades of research on Supercritical Airfoil were conducted to boost an aircraft's efficiency at High Subsonic Speed. This research work analyzes the simulation on Supercritical wing SC (2)-0714 with Shock Control Bump of various heights at different angles of attack. A comparative study has been performed on aerodynamic characteristics between the models of variable heights. The foils were initially designed in Dassault’s Solidworks and imported to Ansys Fluent to test at Transonic Flow Regimes. The Obtained Results are validated and prove that the Shock Control Bump with low bump height is effective in delaying the drag at Mach 0.85. It is summarized that such Optimized Airfoil offers the maximum Cl and feasible in the Aviation Industry.