CFD Simulations Using Open-Source SU2 Code

RAE 2822 Transonic Airfoil
*Contributor: Geonwoo Kim (Nov 2025)*  

We consider the classical transonic flow problem over the RAE 2822 super-critical airfoil, widely used as a validation case for compressible turbulent CFD solvers (e.g., NASA GRC V&V archive).

• Geometry: 2-D airfoil section RAE 2822

• Transonic, featuring a shock–boundary-layer interaction on the upper surface of the airfoil.

• Typical free-stream conditions:

  • Mach number = 0.729

  • Angle of attack = 2.31 degree

  • Reynolds number = 6.5 million

Converging-Diverging Verification (CDV) Nozzle
*Contributor: Junsang Yoon (Dec 2025)*  

We consider the classical compressible flow problem through a converging–diverging nozzle, widely used as a verification case for isentropic and shocked nozzle flows in CFD solvers (e.g., NASA GRC V&V archive).

• Geometry: Axisymmetric converging–diverging nozzle

  • Throat area = 1.0 in² at x = 5 in 

• Plenum conditions: 

  • Total pressure = 1.0 psia

  • Total temperature = 100 R 

• Exit pressure cases (defines flow regime): 

  • Pexit/Pt = 0.89: subsonic, isentropic 

  • Pexit/Pt = 0.75: supersonic with a normal shock in diffuser

  • Pexit/Pt = 0.16: fully supersonic, isentropic

Sajben Transonic Diffuser
*Contributor: Seunghyun Choi (Dec 2025)*  

We consider the transonic flow through the Sajben converging–diverging diffuser, a standard validation case for internal shock behavior and comparison with well-documented experimental data (e.g., NASA GRC V&V archive).

• Geometry: 2-D converging–diverging diffuser 

  • Throat height = 0.14435 ft at x = 0 

• Plenum conditions: 

  • Total pressure = 19.58 psia 

  • Total temperature = 500 R 

• Exit pressure cases (controls shock strength): 

  • Pexit​ = 16.05 psia: weak shock