한국전산유체공학회:학술대회논문집
- 2011.05a
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- Pages.414-419
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- 2011
Unsteady Aerodynamic characteristics at High Angle of Attack around Two Dimensional NACA0012 Airfoil
고 받음각 2차원 NACA0012 에어포일 주위의 비정상 공기역학적 특성
- Published : 2011.05.26
Abstract
Missile am fighter aircraft have been challenged by low restoring nose-down pitching moment at high angle of attach. The consequence of weak nose-down pitching moment can be resulting in a deep stall condition. Especially, the pressure oscillation has a huge effect on noise generation, structure damage, aerodynamic performance and safety, because the flow has strong unsteadiness at high angle of attack. In this paper, the unsteady aerodynamics coefficients were analyzed at high angle of attack up to 60 degrees around two dimensional NACA0012 airfoil. The two dimensional unsteady compressible Navier-Stokes equation with a LES turbulent model was calculated by OHOC (Optimized High-Order Compact) scheme. The flow conditions are Mach number of 0.3 and Reynolds number of
Keywords
- High Angle of Attack;
- Unsteady Aerodynamic Characteristics;
- Optimized High-Order Compact Scheme;
- LES turblent model