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Case Study: Transonic aerodynamics of NACA 0012 airfoil using Ansys Fluent

Steady state CFD simulations are performed over NACA 0012 airfoil 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 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, shock stall and drag divergence.

Learning Outcomes

  • Understand high speed external aerodynamics.
  • Describe the effect of mixed flow pattern and associated complications.
  • Analyse Mach number and pressure contours around an airfoil.
  • Explain the phenomenon of shock-stall, critical Mach number, drag divergence Mach number and shock wave attachment Mach number.
  • 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, data and mesh files.
Transonic aerodynamics of NACA 0012 airfoil using Ansys Fluent

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