Test Case 4
This case is again for the same airfoil discussed in the previous test case. The boundarylayer calculations employing quasi-steady and unsteady flow assumptions are performed for
reduced frequencies of 0.0001 (Fig. 10.8), 0.01 (Fig. 10.9), 0.1 (Fig. 10.10), 0.25 (Fig. 10.11)
and 0.5 (Fig. 10.12), for a chord Reynolds number Rc of 6  106 with 1  5 ,    12 and
 T S  30 . In all cases, the results indicate not only the strong effect of the viscosity on the
solutions, but also the effect of quasi-steady and unsteady flow assumption on the solutions.
Fig 10.8 Variation of lift coefficient cl with (a) angle of attack a and (b) cycle,   0.0001
Fig 10.9 Variation of lift coefficient cl with (a) angle of attack a and (b) cycle,   0.01
6/28/2016 3:12 AM
1
Fig 10.10 Variation of lift coefficient cl with (a) angle of attack a and (b) cycle,   0.1
Fig 10.11 Variation of lift coefficient cl with (a) angle of attack a and (b) cycle,   0.25
Fig 10.12 Variation of lift coefficient cl with (a) angle of attack a and (b) cycle,   0.5
6/28/2016 3:12 AM
2