MUMBAI, India, Sept. 14 -- Intellectual Property India has published a patent application (202541020618 A) filed by Anupama P A on March 07, 2025, for Docile Shock Control For Supercritical Airfoil.
Inventor includes Anupama P A.
The application for the patent was published on September 11, 2026, under issue no. 37/2026.
Abstract: The transition from subsonic to supersonic flow over an airfoil in the transonic regime results in substantial pressure disturbances, which give rise to shock waves and boundary layer separation. These phenomena significantly affect the aerodynamic performance of the airfoil by increasing drag and creating vortices, thus reducing lift and efficiency. To address these performance losses, flow control techniques are often implemented to manage and modify the flow characteristics around the airfoil. This study focuses on the RAE 2822 supercritical airfoil, a commonly used airfoil in transonic and supersonic flow regimes. The research explores the integration of passive flow control elements, such as two-dimensional surface bumps and cavity contours, designed using the Hick's-Henne shape function, into the baseline airfoil design. These roughness elements are strategically placed at three different locations on the airfoil to investigate their effects on aerodynamic performance. The analysis involves evaluating key aerodynamic parameters, including the lift coefficient (CL), drag coefficient (CD), and pressure coefficient (CP) distributions, to assess the influence of the roughness elements on flow characteristics. The study is conducted at two distinct Reynolds numbers-Re=3.1 xI 0"6 for transonic conditions and provide valuable insights into the potential of passive flow control techniques to improve airfoil perfonnance by delaying flow separation, reducing drag, and enhancing overall aerodynamic efficiency, particularly in challenging transonic and supersonic flow regimes.
Disclaimer: Curated by HT Syndication.
