Aerodynamics of supercritical airfoil using Ansys Fluent® Software
Steady state CFD simulations are performed over NACA 0012 and SC(2)-0712 airfoils over a wide range of Mach numbers to understand the concepts of critical Mach number and drag divergence Mach number. The results include the variation of lift and drag coefficients with Mach number, pressure and Mach number contours for flow visualization. The design features of supercritical airfoils are elaborated. The present study will serve as a starting point for mechanical, aeronautical and aerospace engineering students to better understand the fundamental concepts associated with external aerodynamics along with the visualization of shock formation and drag divergence using Ansys Fluent®, the fluid simulation software.
Learning Outcomes
- Understand high speed external aerodynamics
- Describe the effect of mixed flow pattern and associated complications
- Analyze Mach number and pressure contours around an airfoil
- Explain the phenomenon of flat top pressure distribution and design aspects of supercritical airfoil
- Understand the effect of shock formation on pressure distribution
Applicable Courses for Use
- Introduction to Aerodynamics
- Principles of High Speed Flights
- External Aerodynamics
- Compressible Flows
- Advanced Gas Dynamics
Downloadable Content
- Case study pdf file and relevant case, data, and mesh files
Related Resources
- https://www.ansys.com/academic/educators/education-resources/aerodynamic-characteristics-of-multiple-tandem-airfoils-in-ansys-fluent
- https://www.ansys.com/academic/educators/education-resources/flow-around-an-airfoil-with-ansys-fluent
- https://www.ansys.com/academic/educators/education-resources/transonic-aerodynamics-of-naca-0012-airfoil-using-ansys-fluent
