NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa) Reynolds number: 50,000 Max Cl/Cd: 20.27 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0012h-sa-50000.txt Download as CSV file: xf-naca0012h-sa-50000.csv |
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
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Polar data table (+)
Polar graphs
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