background: engineering background & motivation
| Precise estimations of maximum
lift and stall angle of a wing are an important issue for the aerodynamic
design of aircraft.
While the conventional CFD technology has enabled precise numerical analysis
of attached flows at relatively low angles of attack, |
Shih, C et al. AIAA J. Vol.30, No.5 |
it is still difficult to simulate
massively-separated unsteady turbulent flows at high angles of attack
near stall conditions.
Therefore, it is important and necessary to develop a CFD technology for the
prediction of such unsteady flows at high Reynolds numbers within the reasonable
computational cost.
In the workshop sponsored by the National Aerospace Laboratory of Japan in
2000, CFD predictions of the stall
characteristics of three types of wing sections were discussed; NACA63-018,
NACA63-012, and NACA64A006.
The stall characteristics of the NACA63-018 and the NACA63-012 were relatively well
predicted by the conventional RANS computations.
However, prediction of stall characteristic of the NACA64A006 airfoil
at high Reynolds numbers was not successful at all.
Therefore, we focus on the CFD prediction of the stalling characteristics of
the NACA64A006 airfoil.
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