Transient CFD simulation of a NACA airfoil at Mach 0.6, following the flow as the angle of attack increases from attached flow to full stall.
Sector
Aerospace research
Client
University research group
Flow type
Transient, compressible, separated
Project Snapshot
Challenge
At Mach 0.6, compressibility and separation interact: local supersonic pockets and shock-induced separation can trigger stall earlier than low-speed data suggests. Steady simulations at fixed angles miss how separation actually develops over time.
Approach
A transient compressible simulation with the angle of attack increased progressively, a turbulence model suited to adverse pressure gradients and separation, and near-wall mesh resolution to capture the boundary layer.
Key Findings
- Separation began near the trailing edge and moved upstream as incidence increased, rather than appearing suddenly.
- Suction-side pressure recovery weakened well before maximum lift, giving an early indicator of stall.
- The dynamic response differed from steady-state predictions, showing the value of transient analysis near stall.
Deliverables
An animated flow-field visualization, surface-pressure evolution and a clear picture of the stall sequence for research use. For background, see our article on the stall process in aerodynamics.
Working on a similar problem?
Explore our CFD consulting services or send us your aerodynamic simulation or research question. Learn more about our computational fluid dynamics consulting in Australia.