Computational Analysis of Propulsion Performance of Modified Pitching Motion Airfoils in Laminar Flow

Table 1

Details of grid and time steps independence study.

Validation	Cells	Time steps/cycle	𝐶𝑇mean	𝐶𝑃mean	η
Case 1: 𝑅=0.5𝑐, 𝜃=20°, and 𝑘=3
Time	96,000	1200	0.693	4.736	0.146
	96,000	2400	0.694	4.742	0.146
	96,000	4800	0.697	4.738	0.147
Space	48,000	2400	0.697	4.595	0.152
	96,000	2400	0.694	4.742	0.146
	192,000	4800	0.703	4.763	0.147
Case 2: 𝑅=1.5𝑐, 𝜃=10°, and 𝑘=2
Time	96,000	1200	0.227	1.134	0.2
	96,000	2400	0.226	1.135	0.199
	96,000	4800	0.227	1.144	0.198
Space	48,000	2400	0.231	1.167	0.198
	96,000	2400	0.226	1.135	0.199
	192,000	4800	0.230	1.166	0.197