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Table 3 Comparison of the lift and drag coefficients between the different spatial resolutions at α=5 deg and α=10 deg

From: Aerodynamic analysis of a generic wing featuring an elasto-flexible lifting surface

CL at α=5 deg0.519 ±0.0270.5160.515
CD at α=5 deg0.032 ±0.0030.0290.029
CL at α=10 deg0.906 ±0.0260.8980.897
CD at α=10 deg0.066 ±0.0050.0630.062