NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa) Reynolds number: 200,000 Max Cl/Cd: 46.56 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0012h-sa-200000-n5.txt Download as CSV file: xf-naca0012h-sa-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0911 0.10452 0.09971 -0.0053 1.0000 0.0463
-16.750 -1.1460 0.09023 0.08513 -0.0143 1.0000 0.0464
-16.500 -1.1812 0.07999 0.07463 -0.0208 1.0000 0.0467
-16.250 -1.2005 0.07312 0.06761 -0.0249 1.0000 0.0471
-16.000 -1.2125 0.06767 0.06206 -0.0279 1.0000 0.0475
-15.750 -1.2238 0.06248 0.05675 -0.0309 1.0000 0.0479
-15.500 -1.2328 0.05782 0.05197 -0.0334 1.0000 0.0484
-15.250 -1.2398 0.05368 0.04770 -0.0354 1.0000 0.0489
-15.000 -1.2448 0.05003 0.04392 -0.0368 1.0000 0.0495
-14.750 -1.2482 0.04681 0.04055 -0.0378 1.0000 0.0503
-14.500 -1.2499 0.04398 0.03756 -0.0382 1.0000 0.0511
-14.250 -1.2502 0.04147 0.03489 -0.0381 1.0000 0.0519
-14.000 -1.2489 0.03926 0.03248 -0.0376 1.0000 0.0529
-13.750 -1.2459 0.03734 0.03041 -0.0367 1.0000 0.0537
-13.500 -1.2411 0.03574 0.02877 -0.0355 1.0000 0.0546
-13.250 -1.2347 0.03436 0.02733 -0.0341 1.0000 0.0555
-13.000 -1.2271 0.03312 0.02600 -0.0325 1.0000 0.0565
-12.750 -1.2184 0.03199 0.02476 -0.0307 1.0000 0.0577
-12.500 -1.2087 0.03093 0.02357 -0.0288 1.0000 0.0590
-12.250 -1.1974 0.02993 0.02241 -0.0270 1.0000 0.0604
-12.000 -1.1845 0.02892 0.02134 -0.0254 1.0000 0.0617
-11.750 -1.1699 0.02805 0.02045 -0.0239 1.0000 0.0630
-11.500 -1.1537 0.02724 0.01958 -0.0226 1.0000 0.0646
-11.250 -1.1363 0.02647 0.01870 -0.0214 1.0000 0.0664
-11.000 -1.1179 0.02571 0.01782 -0.0202 1.0000 0.0683
-10.750 -1.0998 0.02492 0.01697 -0.0190 1.0000 0.0701
-10.500 -1.0812 0.02422 0.01626 -0.0178 1.0000 0.0719
-10.250 -1.0613 0.02359 0.01557 -0.0168 1.0000 0.0740
-10.000 -1.0407 0.02298 0.01487 -0.0157 1.0000 0.0764
-9.750 -1.0198 0.02237 0.01416 -0.0147 1.0000 0.0787
-9.500 -0.9999 0.02173 0.01354 -0.0136 1.0000 0.0811
-9.250 -0.9787 0.02120 0.01298 -0.0126 1.0000 0.0836
-9.000 -0.9570 0.02069 0.01240 -0.0116 1.0000 0.0865
-8.750 -0.9353 0.02017 0.01182 -0.0106 1.0000 0.0893
-8.500 -0.9144 0.01964 0.01132 -0.0095 1.0000 0.0922
-8.250 -0.8926 0.01920 0.01085 -0.0084 1.0000 0.0954
-8.000 -0.8704 0.01878 0.01036 -0.0074 1.0000 0.0988
-7.750 -0.8492 0.01831 0.00990 -0.0062 1.0000 0.1021
-7.500 -0.8278 0.01791 0.00950 -0.0051 1.0000 0.1058
-7.250 -0.8058 0.01754 0.00910 -0.0039 1.0000 0.1098
-7.000 -0.7842 0.01716 0.00871 -0.0027 1.0000 0.1136
-6.750 -0.7628 0.01678 0.00836 -0.0015 1.0000 0.1179
-6.500 -0.7408 0.01647 0.00803 -0.0004 1.0000 0.1225
-6.250 -0.7191 0.01614 0.00769 0.0008 1.0000 0.1269
-6.000 -0.6977 0.01581 0.00741 0.0020 1.0000 0.1319
-5.750 -0.6757 0.01555 0.00712 0.0032 1.0000 0.1372
-5.500 -0.6542 0.01525 0.00685 0.0044 1.0000 0.1422
-5.250 -0.6326 0.01499 0.00662 0.0056 1.0000 0.1481
-4.750 -0.5892 0.01451 0.00619 0.0079 1.0000 0.1602
-4.500 -0.5645 0.01431 0.00600 0.0085 0.9992 0.1675
-4.250 -0.5259 0.01404 0.00579 0.0062 0.9942 0.1763
-4.000 -0.4879 0.01381 0.00559 0.0041 0.9884 0.1860
-3.750 -0.4496 0.01355 0.00541 0.0019 0.9828 0.1964
-3.500 -0.4128 0.01331 0.00522 0.0001 0.9758 0.2067
-3.250 -0.3731 0.01308 0.00503 -0.0023 0.9692 0.2186
-3.000 -0.3389 0.01282 0.00485 -0.0035 0.9594 0.2303
-2.750 -0.3036 0.01257 0.00467 -0.0048 0.9491 0.2427
-2.500 -0.2683 0.01233 0.00450 -0.0061 0.9382 0.2561
-2.250 -0.2366 0.01211 0.00434 -0.0067 0.9241 0.2701
-2.000 -0.2054 0.01188 0.00416 -0.0070 0.9087 0.2853
-1.750 -0.1748 0.01162 0.00397 -0.0073 0.8905 0.3014
-1.500 -0.1454 0.01135 0.00377 -0.0072 0.8686 0.3203
-1.250 -0.1188 0.01103 0.00359 -0.0066 0.8429 0.3483
-1.000 -0.0936 0.01065 0.00344 -0.0057 0.8157 0.4094
-0.750 -0.0704 0.01029 0.00333 -0.0043 0.7816 0.4903
-0.500 -0.0471 0.01005 0.00326 -0.0029 0.7459 0.5591
-0.250 -0.0236 0.00992 0.00322 -0.0015 0.7081 0.6165
0.000 0.0000 0.00987 0.00321 0.0000 0.6649 0.6649
0.250 0.0236 0.00992 0.00322 0.0015 0.6164 0.7082
0.500 0.0471 0.01005 0.00326 0.0029 0.5592 0.7459
0.750 0.0704 0.01029 0.00333 0.0043 0.4903 0.7817
1.000 0.0937 0.01065 0.00344 0.0057 0.4095 0.8156
1.250 0.1188 0.01103 0.00359 0.0066 0.3484 0.8429
1.500 0.1455 0.01135 0.00377 0.0072 0.3203 0.8686
1.750 0.1748 0.01162 0.00397 0.0072 0.3015 0.8905
2.000 0.2054 0.01188 0.00416 0.0070 0.2853 0.9087
2.250 0.2366 0.01211 0.00434 0.0067 0.2701 0.9241
2.500 0.2683 0.01233 0.00450 0.0061 0.2561 0.9383
2.750 0.3036 0.01257 0.00467 0.0048 0.2427 0.9491
3.000 0.3389 0.01282 0.00485 0.0035 0.2304 0.9594
3.250 0.3732 0.01308 0.00503 0.0023 0.2186 0.9692
3.500 0.4128 0.01330 0.00522 -0.0001 0.2067 0.9758
3.750 0.4496 0.01355 0.00541 -0.0019 0.1963 0.9829
4.000 0.4879 0.01381 0.00559 -0.0041 0.1859 0.9885
4.250 0.5259 0.01403 0.00579 -0.0062 0.1763 0.9943
4.500 0.5645 0.01431 0.00600 -0.0085 0.1675 0.9993
4.750 0.5891 0.01451 0.00619 -0.0079 0.1602 1.0000
5.250 0.6325 0.01498 0.00662 -0.0056 0.1481 1.0000
5.500 0.6541 0.01525 0.00685 -0.0044 0.1422 1.0000
5.750 0.6756 0.01554 0.00712 -0.0032 0.1372 1.0000
6.000 0.6976 0.01581 0.00740 -0.0020 0.1319 1.0000
6.250 0.7190 0.01614 0.00769 -0.0008 0.1269 1.0000
6.500 0.7407 0.01647 0.00802 0.0004 0.1225 1.0000
6.750 0.7627 0.01678 0.00836 0.0016 0.1179 1.0000
7.000 0.7841 0.01716 0.00871 0.0028 0.1136 1.0000
7.250 0.8057 0.01754 0.00910 0.0039 0.1098 1.0000
7.500 0.8277 0.01790 0.00950 0.0051 0.1058 1.0000
7.750 0.8492 0.01831 0.00989 0.0062 0.1021 1.0000
8.000 0.8704 0.01878 0.01036 0.0074 0.0988 1.0000
8.250 0.8926 0.01920 0.01084 0.0084 0.0954 1.0000
8.500 0.9144 0.01964 0.01132 0.0095 0.0922 1.0000
8.750 0.9354 0.02017 0.01182 0.0106 0.0893 1.0000
9.000 0.9571 0.02069 0.01240 0.0116 0.0865 1.0000
9.250 0.9788 0.02120 0.01298 0.0126 0.0836 1.0000
9.500 1.0000 0.02173 0.01354 0.0136 0.0810 1.0000
9.750 1.0200 0.02237 0.01416 0.0147 0.0787 1.0000
10.000 1.0409 0.02298 0.01487 0.0157 0.0764 1.0000
10.250 1.0615 0.02359 0.01557 0.0167 0.0740 1.0000
10.500 1.0814 0.02422 0.01626 0.0178 0.0719 1.0000
10.750 1.1001 0.02492 0.01697 0.0189 0.0701 1.0000
11.000 1.1182 0.02571 0.01782 0.0201 0.0683 1.0000
11.250 1.1366 0.02647 0.01870 0.0213 0.0664 1.0000
11.500 1.1541 0.02725 0.01958 0.0225 0.0645 1.0000
11.750 1.1704 0.02805 0.02045 0.0239 0.0630 1.0000
12.000 1.1850 0.02892 0.02135 0.0253 0.0617 1.0000
12.250 1.1980 0.02994 0.02242 0.0269 0.0604 1.0000
12.500 1.2094 0.03093 0.02357 0.0287 0.0590 1.0000
12.750 1.2192 0.03199 0.02476 0.0306 0.0576 1.0000
13.000 1.2279 0.03312 0.02600 0.0323 0.0564 1.0000
13.250 1.2356 0.03436 0.02732 0.0339 0.0554 1.0000
13.500 1.2421 0.03574 0.02877 0.0353 0.0545 1.0000
13.750 1.2469 0.03734 0.03041 0.0365 0.0537 1.0000
14.000 1.2500 0.03926 0.03247 0.0374 0.0528 1.0000
14.250 1.2514 0.04147 0.03488 0.0379 0.0519 1.0000
14.500 1.2513 0.04396 0.03755 0.0380 0.0510 1.0000
14.750 1.2497 0.04679 0.04054 0.0376 0.0502 1.0000
15.000 1.2464 0.05000 0.04389 0.0366 0.0495 1.0000
15.250 1.2416 0.05364 0.04766 0.0352 0.0489 1.0000
15.500 1.2348 0.05776 0.05191 0.0332 0.0484 1.0000
15.750 1.2260 0.06240 0.05667 0.0307 0.0479 1.0000
16.000 1.2149 0.06756 0.06195 0.0277 0.0475 1.0000
16.250 1.2032 0.07295 0.06743 0.0247 0.0470 1.0000
16.500 1.1826 0.08009 0.07473 0.0204 0.0467 1.0000
16.750 1.1474 0.09034 0.08525 0.0139 0.0464 1.0000
17.000 1.0914 0.10488 0.10008 0.0047 0.0462 1.0000
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Polar data table (+)
Polar graphs
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