XFOIL Version 6.96 Calculated polar for: NACA0012H for VAWT from Sandia report SAND80-211 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.6866 0.07867 0.07048 -0.0053 1.0000 0.2535 -8.250 -0.6936 0.07253 0.06428 -0.0070 1.0000 0.2482 -8.000 -0.7170 0.06534 0.05697 -0.0089 1.0000 0.2437 -7.750 -0.7364 0.05906 0.05044 -0.0094 1.0000 0.2424 -7.500 -0.7413 0.05454 0.04568 -0.0088 1.0000 0.2448 -7.250 -0.7436 0.05032 0.04111 -0.0078 1.0000 0.2478 -7.000 -0.7445 0.04637 0.03665 -0.0064 1.0000 0.2511 -6.750 -0.7257 0.04429 0.03463 -0.0053 1.0000 0.2577 -6.500 -0.7136 0.04188 0.03197 -0.0038 1.0000 0.2645 -6.250 -0.7032 0.03923 0.02891 -0.0023 1.0000 0.2708 -6.000 -0.6828 0.03762 0.02737 -0.0011 1.0000 0.2793 -5.750 -0.6693 0.03549 0.02486 0.0005 1.0000 0.2878 -5.500 -0.6484 0.03396 0.02337 0.0017 1.0000 0.2972 -5.250 -0.6305 0.03226 0.02150 0.0030 1.0000 0.3075 -5.000 -0.6110 0.03079 0.01986 0.0043 1.0000 0.3189 -4.750 -0.5895 0.02944 0.01859 0.0054 1.0000 0.3307 -4.500 -0.5684 0.02816 0.01728 0.0066 1.0000 0.3438 -4.250 -0.5470 0.02698 0.01607 0.0077 1.0000 0.3580 -4.000 -0.5253 0.02594 0.01505 0.0088 1.0000 0.3741 -3.750 -0.5030 0.02497 0.01414 0.0099 1.0000 0.3915 -3.500 -0.4807 0.02408 0.01339 0.0111 1.0000 0.4112 -3.250 -0.4582 0.02327 0.01272 0.0123 1.0000 0.4336 -3.000 -0.4358 0.02250 0.01207 0.0134 1.0000 0.4603 -2.750 -0.4132 0.02180 0.01161 0.0146 1.0000 0.4917 -2.500 -0.3912 0.02112 0.01122 0.0161 1.0000 0.5309 -2.250 -0.3710 0.02048 0.01098 0.0181 1.0000 0.5834 -2.000 -0.3528 0.01992 0.01102 0.0213 1.0000 0.6589 -1.750 -0.3335 0.01987 0.01158 0.0262 1.0000 0.7702 -1.500 -0.2748 0.02109 0.01287 0.0259 1.0000 0.8881 -1.250 -0.0928 0.02235 0.01366 0.0015 1.0000 0.9662 -1.000 0.0170 0.02163 0.01273 -0.0146 1.0000 1.0000 -0.750 0.0167 0.02127 0.01239 -0.0117 1.0000 1.0000 -0.500 0.0138 0.02103 0.01217 -0.0083 1.0000 1.0000 -0.250 0.0079 0.02089 0.01205 -0.0043 1.0000 1.0000 0.000 0.0000 0.02085 0.01201 0.0000 1.0000 1.0000 0.250 -0.0079 0.02089 0.01204 0.0043 1.0000 1.0000 0.500 -0.0138 0.02103 0.01216 0.0083 1.0000 1.0000 0.750 -0.0167 0.02127 0.01238 0.0117 1.0000 1.0000 1.000 -0.0170 0.02162 0.01273 0.0146 1.0000 1.0000 1.250 0.0928 0.02235 0.01365 -0.0015 0.9663 1.0000 1.500 0.2746 0.02109 0.01287 -0.0259 0.8882 1.0000 1.750 0.3335 0.01987 0.01158 -0.0262 0.7703 1.0000 2.000 0.3527 0.01992 0.01102 -0.0213 0.6590 1.0000 2.250 0.3710 0.02048 0.01098 -0.0181 0.5835 1.0000 2.500 0.3911 0.02112 0.01122 -0.0160 0.5310 1.0000 2.750 0.4131 0.02180 0.01160 -0.0146 0.4917 1.0000 3.000 0.4357 0.02250 0.01207 -0.0134 0.4603 1.0000 3.250 0.4581 0.02326 0.01272 -0.0122 0.4336 1.0000 3.500 0.4806 0.02408 0.01339 -0.0111 0.4113 1.0000 3.750 0.5030 0.02496 0.01414 -0.0099 0.3915 1.0000 4.000 0.5252 0.02594 0.01505 -0.0088 0.3742 1.0000 4.250 0.5469 0.02698 0.01607 -0.0077 0.3580 1.0000 4.500 0.5683 0.02816 0.01728 -0.0066 0.3438 1.0000 4.750 0.5894 0.02944 0.01858 -0.0054 0.3307 1.0000 5.000 0.6109 0.03079 0.01986 -0.0043 0.3189 1.0000 5.250 0.6304 0.03226 0.02149 -0.0030 0.3075 1.0000 5.500 0.6484 0.03396 0.02337 -0.0017 0.2972 1.0000 5.750 0.6693 0.03549 0.02485 -0.0005 0.2878 1.0000 6.000 0.6828 0.03762 0.02737 0.0011 0.2793 1.0000 6.250 0.7031 0.03923 0.02892 0.0023 0.2708 1.0000 6.500 0.7135 0.04188 0.03197 0.0038 0.2645 1.0000 6.750 0.7257 0.04429 0.03462 0.0053 0.2577 1.0000 7.000 0.7446 0.04637 0.03665 0.0064 0.2511 1.0000 7.250 0.7436 0.05032 0.04111 0.0078 0.2478 1.0000 7.500 0.7414 0.05454 0.04568 0.0088 0.2448 1.0000 7.750 0.7366 0.05906 0.05045 0.0094 0.2424 1.0000 8.000 0.7173 0.06535 0.05697 0.0089 0.2437 1.0000 8.250 0.6939 0.07255 0.06430 0.0070 0.2482 1.0000 8.500 0.6869 0.07870 0.07051 0.0052 0.2535 1.0000