NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S801 Airfoil (s801-nr) Reynolds number: 1,000,000 Max Cl/Cd: 147.26 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s801-nr-1000000.txt Download as CSV file: xf-s801-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S801 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5581 0.04220 0.03991 -0.1105 0.9874 0.0111
-11.250 -0.5526 0.03728 0.03472 -0.1179 0.9841 0.0113
-11.000 -0.5602 0.03316 0.03035 -0.1205 0.9727 0.0114
-10.750 -0.5620 0.03124 0.02826 -0.1195 0.9522 0.0115
-10.500 -0.5558 0.02487 0.02126 -0.1246 0.9388 0.0118
-10.250 -0.5145 0.02277 0.01899 -0.1304 0.9332 0.0123
-10.000 -0.4723 0.02152 0.01759 -0.1353 0.9217 0.0126
-9.750 -0.4357 0.02065 0.01656 -0.1385 0.9039 0.0131
-9.500 -0.4125 0.01973 0.01541 -0.1388 0.8817 0.0134
-9.250 -0.3931 0.01886 0.01432 -0.1381 0.8624 0.0138
-9.000 -0.3734 0.01811 0.01336 -0.1373 0.8466 0.0142
-8.750 -0.3521 0.01760 0.01269 -0.1366 0.8334 0.0145
-8.500 -0.3288 0.01748 0.01242 -0.1361 0.8222 0.0149
-8.000 -0.2899 0.01469 0.00929 -0.1345 0.8029 0.0157
-7.750 -0.2670 0.01410 0.00861 -0.1340 0.7948 0.0161
-7.500 -0.2427 0.01362 0.00808 -0.1337 0.7873 0.0165
-7.250 -0.2185 0.01317 0.00754 -0.1334 0.7804 0.0170
-7.000 -0.1935 0.01272 0.00703 -0.1332 0.7743 0.0176
-6.750 -0.1682 0.01235 0.00659 -0.1330 0.7682 0.0181
-6.500 -0.1424 0.01207 0.00624 -0.1328 0.7628 0.0187
-6.250 -0.1162 0.01173 0.00585 -0.1327 0.7575 0.0189
-6.000 -0.0912 0.01116 0.00520 -0.1325 0.7526 0.0193
-5.750 -0.0661 0.01056 0.00452 -0.1324 0.7481 0.0201
-5.500 -0.0393 0.01019 0.00412 -0.1326 0.7442 0.0209
-5.250 -0.0120 0.00991 0.00381 -0.1327 0.7401 0.0216
-5.000 0.0153 0.00969 0.00354 -0.1328 0.7364 0.0225
-4.750 0.0431 0.00952 0.00331 -0.1329 0.7327 0.0234
-4.500 0.0711 0.00930 0.00308 -0.1332 0.7296 0.0241
-4.250 0.0991 0.00901 0.00276 -0.1334 0.7264 0.0260
-4.000 0.1272 0.00884 0.00256 -0.1336 0.7230 0.0281
-3.750 0.1555 0.00868 0.00238 -0.1338 0.7199 0.0326
-3.500 0.1838 0.00832 0.00220 -0.1343 0.7169 0.0737
-3.250 0.2124 0.00798 0.00206 -0.1349 0.7145 0.1280
-3.000 0.2411 0.00769 0.00195 -0.1354 0.7119 0.1837
-2.750 0.2701 0.00737 0.00186 -0.1361 0.7094 0.2515
-2.500 0.2993 0.00703 0.00177 -0.1368 0.7070 0.3367
-2.250 0.3290 0.00665 0.00169 -0.1377 0.7045 0.4422
-2.000 0.3591 0.00628 0.00163 -0.1387 0.7017 0.5605
-1.750 0.3882 0.00611 0.00173 -0.1391 0.6998 0.6539
-1.500 0.4171 0.00614 0.00179 -0.1393 0.6977 0.6785
-1.250 0.4460 0.00621 0.00186 -0.1395 0.6956 0.6963
-1.000 0.4748 0.00629 0.00194 -0.1397 0.6934 0.7093
-0.750 0.5036 0.00637 0.00199 -0.1399 0.6912 0.7158
-0.500 0.5327 0.00646 0.00204 -0.1401 0.6889 0.7225
-0.250 0.5616 0.00657 0.00213 -0.1404 0.6863 0.7278
0.000 0.5900 0.00661 0.00219 -0.1405 0.6842 0.7326
0.250 0.6187 0.00666 0.00223 -0.1407 0.6815 0.7370
0.500 0.6468 0.00669 0.00227 -0.1407 0.6785 0.7413
0.750 0.6748 0.00675 0.00233 -0.1408 0.6755 0.7451
1.000 0.7033 0.00686 0.00240 -0.1409 0.6715 0.7491
1.250 0.7313 0.00690 0.00244 -0.1410 0.6679 0.7527
1.500 0.7589 0.00690 0.00247 -0.1409 0.6638 0.7563
1.750 0.7862 0.00694 0.00252 -0.1408 0.6594 0.7596
2.000 0.8140 0.00703 0.00259 -0.1408 0.6546 0.7626
2.250 0.8415 0.00704 0.00263 -0.1408 0.6502 0.7654
2.500 0.8691 0.00708 0.00266 -0.1408 0.6449 0.7678
2.750 0.8966 0.00715 0.00270 -0.1408 0.6395 0.7697
3.000 0.9240 0.00712 0.00273 -0.1408 0.6345 0.7714
3.250 0.9511 0.00715 0.00277 -0.1407 0.6288 0.7728
3.500 0.9780 0.00721 0.00283 -0.1406 0.6230 0.7743
3.750 1.0051 0.00723 0.00288 -0.1405 0.6154 0.7758
4.000 1.0315 0.00730 0.00294 -0.1403 0.6079 0.7773
4.250 1.0582 0.00734 0.00301 -0.1401 0.5983 0.7787
4.500 1.0841 0.00741 0.00308 -0.1398 0.5858 0.7803
4.750 1.1089 0.00753 0.00315 -0.1393 0.5682 0.7819
5.000 1.1313 0.00774 0.00328 -0.1383 0.5389 0.7832
5.250 1.1469 0.00829 0.00354 -0.1360 0.4822 0.7844
5.500 1.1608 0.00894 0.00393 -0.1335 0.4265 0.7861
5.750 1.1749 0.00961 0.00435 -0.1310 0.3738 0.7878
6.000 1.1881 0.01029 0.00479 -0.1285 0.3246 0.7896
6.250 1.2011 0.01094 0.00523 -0.1259 0.2804 0.7913
6.500 1.2122 0.01153 0.00564 -0.1229 0.2434 0.7930
6.750 1.2240 0.01208 0.00605 -0.1200 0.2136 0.7948
7.000 1.2369 0.01263 0.00647 -0.1175 0.1880 0.7966
7.250 1.2501 0.01317 0.00691 -0.1150 0.1651 0.7983
7.500 1.2632 0.01374 0.00737 -0.1126 0.1452 0.8000
7.750 1.2766 0.01427 0.00784 -0.1102 0.1283 0.8023
8.000 1.2904 0.01481 0.00833 -0.1080 0.1145 0.8043
8.250 1.3044 0.01535 0.00884 -0.1059 0.1028 0.8063
8.500 1.3186 0.01590 0.00937 -0.1038 0.0926 0.8084
8.750 1.3327 0.01648 0.00992 -0.1018 0.0835 0.8106
9.000 1.3458 0.01712 0.01054 -0.0998 0.0752 0.8128
9.250 1.3597 0.01776 0.01116 -0.0979 0.0689 0.8148
9.500 1.3729 0.01841 0.01183 -0.0959 0.0631 0.8174
9.750 1.3862 0.01910 0.01253 -0.0941 0.0583 0.8199
10.000 1.3982 0.01989 0.01333 -0.0921 0.0531 0.8226
10.250 1.4126 0.02058 0.01406 -0.0906 0.0503 0.8255
10.500 1.4243 0.02146 0.01494 -0.0888 0.0468 0.8286
10.750 1.4363 0.02235 0.01587 -0.0871 0.0435 0.8318
11.000 1.4504 0.02310 0.01667 -0.0857 0.0411 0.8353
11.250 1.4617 0.02409 0.01767 -0.0840 0.0385 0.8390
11.500 1.4719 0.02519 0.01881 -0.0824 0.0357 0.8429
11.750 1.4863 0.02601 0.01969 -0.0812 0.0343 0.8470
12.000 1.4983 0.02700 0.02074 -0.0799 0.0326 0.8517
12.250 1.5087 0.02817 0.02194 -0.0784 0.0308 0.8572
12.500 1.5168 0.02954 0.02336 -0.0768 0.0289 0.8633
12.750 1.5299 0.03051 0.02442 -0.0757 0.0282 0.8711
13.000 1.5416 0.03159 0.02559 -0.0746 0.0272 0.8812
13.250 1.5518 0.03273 0.02683 -0.0732 0.0260 0.8983
13.500 1.5588 0.03391 0.02815 -0.0716 0.0248 1.0000
13.750 1.5655 0.03565 0.02993 -0.0704 0.0234 1.0000
14.000 1.5777 0.03690 0.03123 -0.0696 0.0226 1.0000
14.250 1.5889 0.03825 0.03265 -0.0688 0.0218 1.0000
14.500 1.5990 0.03974 0.03418 -0.0680 0.0208 1.0000
14.750 1.6075 0.04140 0.03586 -0.0672 0.0198 1.0000
15.000 1.6127 0.04341 0.03791 -0.0663 0.0186 1.0000
15.250 1.6215 0.04511 0.03968 -0.0656 0.0179 1.0000
15.500 1.6311 0.04675 0.04139 -0.0651 0.0172 1.0000
15.750 1.6395 0.04855 0.04325 -0.0645 0.0163 1.0000
16.000 1.6452 0.05066 0.04539 -0.0640 0.0153 1.0000
16.250 1.6488 0.05306 0.04785 -0.0634 0.0143 1.0000
16.500 1.6569 0.05499 0.04985 -0.0631 0.0135 1.0000
16.750 1.6620 0.05730 0.05221 -0.0627 0.0126 1.0000
17.000 1.6644 0.05999 0.05495 -0.0624 0.0116 1.0000
17.250 1.6677 0.06262 0.05766 -0.0623 0.0107 1.0000
17.500 1.6699 0.06544 0.06054 -0.0622 0.0099 1.0000
17.750 1.6687 0.06877 0.06393 -0.0623 0.0090 1.0000
18.000 1.6681 0.07212 0.06738 -0.0625 0.0084 1.0000
18.250 1.6681 0.07544 0.07080 -0.0628 0.0079 1.0000
18.500 1.6656 0.07920 0.07464 -0.0634 0.0074 1.0000
18.750 1.6604 0.08346 0.07899 -0.0641 0.0070 1.0000
19.000 1.6512 0.08848 0.08412 -0.0653 0.0066 1.0000
19.250 1.6465 0.09291 0.08867 -0.0665 0.0064 1.0000
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