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The flow field of airfoil with different Trailing- Edge
geometry have studied. For this research, the two -zone grid,
created by solving elliptic partial diffe- rential equations
and algebraic equs, was used. An locally implicit scheme is
used for the numerical so- lution of the compressible Navier-
Stokes equs. First, the NACA 0012 and RAE2822 airfoil were sel-
ected to demonstrate the scheme program and compared with the
experimental data of AGARD. Then, the RAE2822 airfoil was used
to study a two-dimensional shock bou- ndary-layer interaction
problem. In this study, the Trailing-Edge geometry was cla-
ssified to two types. The first type is slab Trailing- Edge.
For this Type, the slabs were add to Trailing- Edge of NACA
64A 004M airfoil. The second type is Divergent Trailing-
Edge (DTE). For this type, the Trailing-Edge of RAE2822
airfoil was modified by variying surface curvature with
constant Trailing-Edge thickness. Four different Divergent
Trailing-Edge has been designed. In this study, flow over
the airfoil with slab Trailing-Edge and Divergent Trailing-
Edge are investi- gated. The results show that the increased
camber eff- ectiveness of the Divergent Trailing-Edge airfoil
has superior transonic lift and drag characteristics to
RAE2822 airfoil. In addition, It is also found that the
Divergent Trailing-Edge has effects to decouple the upper-
and lower-surface pressure distributions near the Trailing-
Edge.
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