NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa) Reynolds number: 100,000 Max Cl/Cd: 28.19 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0012h-sa-100000.txt Download as CSV file: xf-naca0012h-sa-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6685 0.12966 0.12380 0.0086 1.0000 0.1851
-11.250 -0.8496 0.07654 0.07049 -0.0260 1.0000 0.1249
-11.000 -0.8854 0.06914 0.06297 -0.0278 1.0000 0.1243
-10.750 -0.9237 0.06287 0.05648 -0.0267 1.0000 0.1239
-10.500 -0.9566 0.05672 0.04993 -0.0249 1.0000 0.1242
-10.250 -0.9812 0.05138 0.04402 -0.0221 1.0000 0.1252
-10.000 -0.9533 0.05026 0.04317 -0.0221 1.0000 0.1282
-9.750 -0.9364 0.04886 0.04175 -0.0211 1.0000 0.1310
-9.500 -0.9339 0.04570 0.03829 -0.0194 1.0000 0.1335
-9.250 -0.9334 0.04231 0.03444 -0.0171 1.0000 0.1366
-9.000 -0.9309 0.03917 0.03072 -0.0147 1.0000 0.1398
-8.750 -0.9087 0.03784 0.02953 -0.0141 1.0000 0.1432
-8.500 -0.8890 0.03661 0.02824 -0.0131 1.0000 0.1471
-8.250 -0.8757 0.03471 0.02596 -0.0113 1.0000 0.1518
-8.000 -0.8597 0.03283 0.02385 -0.0098 1.0000 0.1560
-7.750 -0.8377 0.03190 0.02298 -0.0089 1.0000 0.1604
-7.500 -0.8188 0.03070 0.02158 -0.0075 1.0000 0.1659
-7.250 -0.8006 0.02923 0.01988 -0.0061 1.0000 0.1712
-7.000 -0.7786 0.02840 0.01911 -0.0051 1.0000 0.1764
-6.750 -0.7588 0.02743 0.01794 -0.0037 1.0000 0.1830
-6.500 -0.7376 0.02634 0.01683 -0.0025 1.0000 0.1889
-6.250 -0.7160 0.02561 0.01608 -0.0014 1.0000 0.1955
-6.000 -0.6955 0.02468 0.01495 0.0000 1.0000 0.2029
-5.750 -0.6731 0.02398 0.01438 0.0010 1.0000 0.2098
-5.500 -0.6523 0.02330 0.01347 0.0024 1.0000 0.2183
-5.250 -0.6297 0.02254 0.01289 0.0033 1.0000 0.2260
-5.000 -0.6085 0.02195 0.01212 0.0046 1.0000 0.2355
-4.750 -0.5860 0.02126 0.01161 0.0056 1.0000 0.2442
-4.500 -0.5643 0.02066 0.01094 0.0067 1.0000 0.2546
-4.250 -0.5422 0.02012 0.01047 0.0078 1.0000 0.2652
-4.000 -0.5200 0.01951 0.00993 0.0088 1.0000 0.2763
-3.750 -0.4980 0.01897 0.00939 0.0099 1.0000 0.2891
-3.500 -0.4758 0.01846 0.00890 0.0109 1.0000 0.3030
-3.250 -0.4534 0.01783 0.00845 0.0118 1.0000 0.3178
-3.000 -0.4311 0.01726 0.00804 0.0127 1.0000 0.3344
-2.750 -0.4089 0.01676 0.00771 0.0137 1.0000 0.3535
-2.500 -0.3871 0.01627 0.00749 0.0146 1.0000 0.3757
-2.250 -0.3652 0.01584 0.00730 0.0155 1.0000 0.4052
-2.000 -0.3437 0.01535 0.00721 0.0165 1.0000 0.4469
-1.750 -0.3232 0.01480 0.00724 0.0178 1.0000 0.5250
-1.500 -0.3051 0.01432 0.00750 0.0202 1.0000 0.6563
-1.250 -0.2876 0.01430 0.00795 0.0234 1.0000 0.7651
-1.000 -0.2691 0.01457 0.00844 0.0264 1.0000 0.8381
-0.750 -0.2431 0.01501 0.00897 0.0278 1.0000 0.8947
-0.500 -0.1883 0.01562 0.00957 0.0235 0.9955 0.9389
-0.250 -0.0958 0.01620 0.01010 0.0122 0.9853 0.9618
0.000 0.0000 0.01642 0.01029 0.0000 0.9754 0.9754
0.250 0.0958 0.01620 0.01010 -0.0122 0.9618 0.9853
0.500 0.1883 0.01562 0.00957 -0.0235 0.9389 0.9955
0.750 0.2431 0.01501 0.00897 -0.0278 0.8947 1.0000
1.000 0.2691 0.01457 0.00844 -0.0264 0.8381 1.0000
1.250 0.2876 0.01430 0.00795 -0.0234 0.7652 1.0000
1.500 0.3050 0.01432 0.00750 -0.0202 0.6563 1.0000
1.750 0.3232 0.01480 0.00724 -0.0178 0.5251 1.0000
2.000 0.3436 0.01535 0.00721 -0.0165 0.4470 1.0000
2.250 0.3651 0.01584 0.00730 -0.0155 0.4053 1.0000
2.500 0.3871 0.01626 0.00748 -0.0146 0.3757 1.0000
2.750 0.4089 0.01676 0.00771 -0.0137 0.3535 1.0000
3.000 0.4310 0.01726 0.00804 -0.0127 0.3344 1.0000
3.250 0.4533 0.01783 0.00845 -0.0118 0.3178 1.0000
3.500 0.4757 0.01846 0.00890 -0.0109 0.3031 1.0000
3.750 0.4979 0.01897 0.00938 -0.0099 0.2891 1.0000
4.000 0.5199 0.01951 0.00993 -0.0088 0.2763 1.0000
4.250 0.5421 0.02012 0.01046 -0.0078 0.2653 1.0000
4.500 0.5642 0.02066 0.01094 -0.0067 0.2546 1.0000
4.750 0.5859 0.02126 0.01161 -0.0055 0.2442 1.0000
5.000 0.6084 0.02195 0.01212 -0.0046 0.2356 1.0000
5.250 0.6296 0.02254 0.01288 -0.0033 0.2260 1.0000
5.500 0.6522 0.02330 0.01347 -0.0023 0.2183 1.0000
5.750 0.6730 0.02398 0.01438 -0.0009 0.2098 1.0000
6.000 0.6954 0.02467 0.01495 0.0001 0.2029 1.0000
6.250 0.7160 0.02561 0.01608 0.0014 0.1955 1.0000
6.500 0.7375 0.02634 0.01683 0.0026 0.1889 1.0000
6.750 0.7587 0.02743 0.01793 0.0037 0.1830 1.0000
7.000 0.7785 0.02840 0.01911 0.0051 0.1764 1.0000
7.250 0.8006 0.02923 0.01988 0.0061 0.1712 1.0000
7.500 0.8188 0.03070 0.02158 0.0075 0.1659 1.0000
7.750 0.8377 0.03190 0.02297 0.0089 0.1604 1.0000
8.000 0.8597 0.03283 0.02384 0.0098 0.1560 1.0000
8.250 0.8758 0.03471 0.02596 0.0113 0.1518 1.0000
8.500 0.8891 0.03661 0.02824 0.0131 0.1471 1.0000
8.750 0.9087 0.03784 0.02952 0.0141 0.1432 1.0000
9.000 0.9310 0.03917 0.03072 0.0147 0.1398 1.0000
9.250 0.9335 0.04232 0.03444 0.0171 0.1366 1.0000
9.500 0.9341 0.04570 0.03830 0.0193 0.1335 1.0000
9.750 0.9366 0.04886 0.04175 0.0211 0.1309 1.0000
10.000 0.9538 0.05024 0.04313 0.0220 0.1282 1.0000
10.250 0.9813 0.05140 0.04404 0.0221 0.1252 1.0000
10.500 0.9567 0.05675 0.04997 0.0248 0.1242 1.0000
10.750 0.9239 0.06292 0.05653 0.0266 0.1239 1.0000
11.000 0.8855 0.06922 0.06305 0.0276 0.1243 1.0000
11.250 0.8500 0.07663 0.07059 0.0258 0.1249 1.0000
11.500 0.6684 0.12975 0.12390 -0.0090 0.1851 1.0000
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Polar data table (+)
Polar graphs
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