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