MUMBAI, India, April 17 -- Intellectual Property India has published a patent application (202641042772 A) filed by G Ashwin Prabhu; Dr. S. Ramasubramanian; Ms. A. Shaziah; Mr. G. Abdul Azeez; Mr. A. Mohammed Wafeeq; Mr. Md Raihan Ihtisham; Mr. V. Vinoth; Mr. Vigneshwaran V; and Mr. Mohammed Afthab, Chennai, Tamil Nadu, on April 2, for 'aircraft wing modeling with aerodynamic considerations using catia.'
Inventor(s) include Dr. S. Ramasubramanian; Ms. A. Shaziah; Mr. G. Abdul Azeez; Mr. A. Mohammed Wafeeq; Mr. Md Raihan Ihtisham; Mr. V. Vinoth; Mr. Vigneshwaran V; and Mr. Mohammed Afthab.
The application for the patent was published on April 17, under issue no. 16/2026.
According to the abstract released by the Intellectual Property India: "This project presents a comprehensive aerodynamic investigation and comparative analysis of the NACA 2418 and NACA 4412 airfoils, with the objective of enhancing wing efficiency through precise geometric modeling and performance evaluation using CATIA (Computer-Aided Three-dimensional Interactive Application). The study emphasizes the relationship between airfoil geometry, specifically camber and thickness distribution, and its direct influence on aerodynamic characteristics such as lift generation, drag behavior, and overall flight efficiency. A parametric modeling approach is adopted to accurately construct the airfoil profiles and develop corresponding three-dimensional wing sections within CATIA. The aerodynamic performance is assessed based on fundamental coefficients, including lift coefficient (Cl), drag coefficient (Cd), and aerodynamic efficiency ratio (Cl/Cd), under subsonic flow conditions. NACA 2418, with a camber of 2% and a relatively high thickness of 18%, is examined for its superior structural integrity and load-bearing capability, making it suitable for low-speed and high-weight aircraft configurations. Conversely, NACA 4412, featuring a higher camber of 4% and moderate thickness of 12%, demonstrates enhanced lift characteristics and improved aerodynamic efficiency, making it more favorable for performance-oriented wing designs. The study incorporates aerodynamic principles to evaluate pressure distribution, boundary layer behavior, and flow separation over the airfoil surfaces. The comparative analysis highlights the trade-off between structural strength and aerodynamic performance, providing a basis for selecting an optimal airfoil configuration. The outcomes contribute to the field of aerodynamic design by establishing a systematic approach to airfoil selection and wing optimization, thereby supporting the development of efficient, high-performance aircraft wings."
Disclaimer: Curated by HT Syndication.
