NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S801 Airfoil (s801-nr) Reynolds number: 100,000 Max Cl/Cd: 52.2 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s801-nr-100000-n5.txt Download as CSV file: xf-s801-nr-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3492 0.11921 0.11412 -0.0531 1.0000 0.0361
-11.000 -0.3483 0.11671 0.11168 -0.0521 1.0000 0.0353
-10.750 -0.3517 0.11398 0.10902 -0.0513 1.0000 0.0346
-10.500 -0.3590 0.11126 0.10638 -0.0504 1.0000 0.0340
-10.250 -0.3501 0.10564 0.10077 -0.0554 0.9959 0.0339
-10.000 -0.3416 0.10002 0.09516 -0.0605 0.9907 0.0338
-9.750 -0.3353 0.09386 0.08901 -0.0666 0.9849 0.0345
-9.500 -0.3310 0.08784 0.08300 -0.0719 0.9766 0.0341
-9.250 -0.3308 0.08093 0.07611 -0.0781 0.9669 0.0337
-9.000 -0.3399 0.07087 0.06605 -0.0880 0.9545 0.0327
-8.750 -0.3702 0.06018 0.05514 -0.0985 0.9371 0.0315
-8.500 -0.3870 0.05226 0.04678 -0.1046 0.9226 0.0310
-8.250 -0.3883 0.04651 0.04049 -0.1075 0.9122 0.0307
-8.000 -0.3735 0.04224 0.03574 -0.1100 0.9058 0.0309
-7.750 -0.3580 0.03901 0.03209 -0.1110 0.8978 0.0312
-7.500 -0.3357 0.03607 0.02874 -0.1125 0.8920 0.0317
-7.250 -0.3075 0.03368 0.02598 -0.1144 0.8881 0.0331
-7.000 -0.2878 0.03182 0.02373 -0.1142 0.8802 0.0347
-6.750 -0.2588 0.02966 0.02108 -0.1154 0.8760 0.0359
-6.500 -0.2269 0.02776 0.01876 -0.1167 0.8727 0.0366
-6.250 -0.2054 0.02641 0.01734 -0.1161 0.8658 0.0375
-6.000 -0.1759 0.02518 0.01601 -0.1169 0.8615 0.0388
-5.750 -0.1431 0.02413 0.01482 -0.1182 0.8583 0.0414
-5.500 -0.1203 0.02341 0.01395 -0.1175 0.8518 0.0441
-5.250 -0.0932 0.02245 0.01294 -0.1177 0.8472 0.0463
-5.000 -0.0628 0.02159 0.01205 -0.1187 0.8438 0.0492
-4.750 -0.0371 0.02097 0.01132 -0.1186 0.8393 0.0530
-4.500 -0.0134 0.02040 0.01074 -0.1183 0.8341 0.0594
-4.250 0.0152 0.01974 0.01010 -0.1189 0.8303 0.0720
-4.000 0.0463 0.01898 0.00943 -0.1199 0.8273 0.1008
-3.750 0.0680 0.01849 0.00919 -0.1194 0.8220 0.1548
-3.500 0.0922 0.01776 0.00898 -0.1196 0.8175 0.2633
-3.250 0.1176 0.01677 0.00885 -0.1201 0.8142 0.4473
-3.000 0.1376 0.01674 0.00942 -0.1174 0.8115 0.5849
-2.750 0.1538 0.01724 0.00998 -0.1144 0.8066 0.6530
-2.500 0.1780 0.01761 0.01022 -0.1134 0.8024 0.6951
-2.250 0.2049 0.01791 0.01036 -0.1128 0.7991 0.7231
-2.000 0.2307 0.01818 0.01052 -0.1117 0.7964 0.7426
-1.750 0.2494 0.01853 0.01079 -0.1096 0.7925 0.7589
-1.500 0.2671 0.01885 0.01105 -0.1074 0.7882 0.7733
-1.250 0.2895 0.01905 0.01116 -0.1060 0.7848 0.7870
-1.000 0.3151 0.01918 0.01119 -0.1053 0.7821 0.8002
-0.750 0.3401 0.01924 0.01118 -0.1042 0.7799 0.8112
-0.500 0.3499 0.01960 0.01153 -0.1009 0.7745 0.8212
-0.250 0.3706 0.01977 0.01166 -0.0996 0.7707 0.8317
0.000 0.3939 0.01983 0.01166 -0.0985 0.7677 0.8403
0.250 0.4221 0.01984 0.01160 -0.0986 0.7655 0.8477
0.500 0.4407 0.02004 0.01178 -0.0971 0.7616 0.8544
0.750 0.4584 0.02033 0.01206 -0.0957 0.7566 0.8609
1.000 0.4817 0.02041 0.01212 -0.0950 0.7533 0.8658
1.250 0.5116 0.02043 0.01210 -0.0955 0.7508 0.8706
1.500 0.5456 0.02043 0.01205 -0.0970 0.7488 0.8746
1.750 0.5515 0.02094 0.01263 -0.0935 0.7418 0.8796
2.000 0.5774 0.02108 0.01276 -0.0935 0.7381 0.8836
2.250 0.6099 0.02110 0.01277 -0.0946 0.7354 0.8870
2.500 0.6451 0.02105 0.01271 -0.0961 0.7332 0.8898
2.750 0.6499 0.02167 0.01342 -0.0927 0.7253 0.8947
3.000 0.6793 0.02173 0.01350 -0.0932 0.7215 0.8979
3.250 0.7149 0.02164 0.01342 -0.0947 0.7188 0.9007
3.500 0.7283 0.02211 0.01398 -0.0926 0.7116 0.9052
3.750 0.7551 0.02214 0.01406 -0.0926 0.7065 0.9086
4.000 0.7934 0.02187 0.01382 -0.0943 0.7031 0.9110
4.250 0.8061 0.02232 0.01436 -0.0921 0.6945 0.9162
4.500 0.8398 0.02207 0.01418 -0.0930 0.6893 0.9194
4.750 0.8630 0.02208 0.01428 -0.0922 0.6819 0.9239
5.000 0.8927 0.02186 0.01413 -0.0924 0.6742 0.9277
5.250 0.9159 0.02181 0.01420 -0.0915 0.6651 0.9326
5.500 0.9514 0.02129 0.01373 -0.0924 0.6568 0.9368
5.750 0.9672 0.02138 0.01395 -0.0903 0.6452 0.9453
6.000 0.9916 0.02122 0.01391 -0.0896 0.6334 0.9545
6.250 1.0188 0.02100 0.01381 -0.0895 0.6209 0.9685
6.500 1.0388 0.02096 0.01387 -0.0882 0.6064 1.0000
6.750 1.0529 0.02125 0.01427 -0.0862 0.5892 1.0000
7.000 1.0675 0.02157 0.01470 -0.0844 0.5691 1.0000
7.250 1.0830 0.02186 0.01506 -0.0827 0.5444 1.0000
7.500 1.1048 0.02186 0.01502 -0.0816 0.5099 1.0000
7.750 1.1316 0.02168 0.01456 -0.0809 0.4600 1.0000
8.000 1.1450 0.02237 0.01495 -0.0789 0.4079 1.0000
8.250 1.1514 0.02355 0.01584 -0.0762 0.3611 1.0000
8.500 1.1554 0.02497 0.01701 -0.0736 0.3195 1.0000
8.750 1.1596 0.02648 0.01832 -0.0713 0.2821 1.0000
9.000 1.1647 0.02804 0.01970 -0.0693 0.2498 1.0000
9.250 1.1706 0.02963 0.02114 -0.0675 0.2207 1.0000
9.500 1.1777 0.03120 0.02262 -0.0659 0.1962 1.0000
9.750 1.1855 0.03278 0.02410 -0.0645 0.1753 1.0000
10.000 1.1932 0.03441 0.02565 -0.0631 0.1577 1.0000
10.500 1.2108 0.03763 0.02881 -0.0608 0.1302 1.0000
10.750 1.2203 0.03923 0.03045 -0.0597 0.1192 1.0000
11.000 1.2291 0.04092 0.03215 -0.0587 0.1102 1.0000
11.250 1.2368 0.04272 0.03395 -0.0577 0.1026 1.0000
11.500 1.2469 0.04437 0.03568 -0.0568 0.0955 1.0000
11.750 1.2543 0.04626 0.03758 -0.0559 0.0897 1.0000
12.000 1.2639 0.04802 0.03942 -0.0550 0.0844 1.0000
12.250 1.2730 0.04985 0.04135 -0.0543 0.0796 1.0000
12.500 1.2794 0.05193 0.04340 -0.0535 0.0758 1.0000
12.750 1.2905 0.05368 0.04535 -0.0528 0.0716 1.0000
13.000 1.2992 0.05564 0.04741 -0.0522 0.0680 1.0000
13.250 1.3065 0.05777 0.04956 -0.0516 0.0652 1.0000
13.500 1.3164 0.05977 0.05169 -0.0510 0.0624 1.0000
13.750 1.3253 0.06188 0.05397 -0.0505 0.0593 1.0000
14.000 1.3324 0.06413 0.05636 -0.0501 0.0568 1.0000
14.250 1.3388 0.06648 0.05877 -0.0497 0.0547 1.0000
14.500 1.3468 0.06886 0.06126 -0.0493 0.0527 1.0000
14.750 1.3521 0.07154 0.06420 -0.0491 0.0505 1.0000
15.000 1.3559 0.07436 0.06721 -0.0489 0.0484 1.0000
15.250 1.3586 0.07728 0.07027 -0.0490 0.0467 1.0000
15.500 1.3616 0.08017 0.07323 -0.0491 0.0452 1.0000
15.750 1.3643 0.08328 0.07644 -0.0492 0.0437 1.0000
16.000 1.3601 0.08739 0.08091 -0.0498 0.0423 1.0000
16.250 1.3550 0.09168 0.08548 -0.0506 0.0409 1.0000
16.500 1.3497 0.09606 0.09008 -0.0517 0.0397 1.0000
16.750 1.3444 0.10048 0.09469 -0.0531 0.0386 1.0000
17.000 1.3400 0.10478 0.09912 -0.0547 0.0375 1.0000
17.250 1.3386 0.10861 0.10300 -0.0561 0.0365 1.0000
17.500 1.3303 0.11384 0.10839 -0.0583 0.0356 1.0000
17.750 1.3131 0.12103 0.11591 -0.0620 0.0350 1.0000
18.000 1.2940 0.12898 0.12415 -0.0665 0.0346 1.0000
18.250 1.2719 0.13799 0.13344 -0.0721 0.0343 1.0000
18.500 1.2448 0.14877 0.14448 -0.0792 0.0343 1.0000
18.750 1.2076 0.16321 0.15915 -0.0892 0.0348 1.0000
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