NREL's S820 Airfoil (s820-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S820 Airfoil (s820-nr) Reynolds number: 100,000 Max Cl/Cd: 36.96 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s820-nr-100000-n5.txt Download as CSV file: xf-s820-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S820 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3477 0.13481 0.12989 -0.0583 1.0000 0.0440
-12.750 -0.3544 0.13237 0.12754 -0.0580 1.0000 0.0446
-12.500 -0.3660 0.12729 0.12254 -0.0650 0.9941 0.0466
-12.250 -0.3635 0.12145 0.11672 -0.0710 0.9880 0.0468
-11.750 -0.2168 0.09253 0.08783 -0.0900 0.9515 0.0193
-11.500 -0.2144 0.08817 0.08347 -0.0922 0.9478 0.0189
-11.250 -0.3323 0.09190 0.08702 -0.0878 0.9716 0.0194
-11.000 -0.3293 0.08719 0.08231 -0.0910 0.9649 0.0189
-10.750 -0.3300 0.08125 0.07631 -0.0965 0.9596 0.0184
-10.500 -0.3380 0.07543 0.07041 -0.1013 0.9515 0.0182
-10.250 -0.3457 0.07004 0.06488 -0.1057 0.9450 0.0177
-10.000 -0.3565 0.06579 0.06047 -0.1080 0.9356 0.0174
-9.750 -0.3670 0.06172 0.05621 -0.1096 0.9275 0.0171
-9.500 -0.3767 0.05850 0.05279 -0.1095 0.9184 0.0167
-9.250 -0.3887 0.05572 0.04979 -0.1078 0.9091 0.0163
-9.000 -0.3974 0.05302 0.04682 -0.1056 0.9022 0.0158
-8.750 -0.4066 0.05025 0.04371 -0.1023 0.8941 0.0152
-8.250 -0.4049 0.04541 0.03799 -0.0968 0.8823 0.0142
-8.000 -0.3975 0.04311 0.03542 -0.0949 0.8773 0.0141
-7.750 -0.3853 0.04077 0.03277 -0.0936 0.8739 0.0141
-7.500 -0.3744 0.03885 0.03057 -0.0916 0.8691 0.0140
-7.250 -0.3608 0.03688 0.02825 -0.0898 0.8644 0.0140
-7.000 -0.3410 0.03499 0.02600 -0.0887 0.8612 0.0142
-6.750 -0.3178 0.03298 0.02377 -0.0885 0.8589 0.0148
-6.500 -0.3008 0.03194 0.02266 -0.0874 0.8548 0.0159
-6.250 -0.2809 0.03091 0.02146 -0.0863 0.8509 0.0178
-6.000 -0.2535 0.02955 0.01989 -0.0860 0.8482 0.0186
-5.750 -0.2235 0.02818 0.01836 -0.0861 0.8460 0.0190
-5.500 -0.1947 0.02687 0.01697 -0.0861 0.8442 0.0198
-5.250 -0.1816 0.02611 0.01623 -0.0838 0.8398 0.0204
-5.000 -0.1698 0.02551 0.01562 -0.0815 0.8357 0.0214
-4.750 -0.1547 0.02490 0.01494 -0.0796 0.8325 0.0227
-4.500 -0.1364 0.02429 0.01420 -0.0782 0.8300 0.0253
-4.250 -0.1285 0.02397 0.01380 -0.0751 0.8251 0.0295
-4.000 -0.1167 0.02370 0.01344 -0.0726 0.8207 0.0342
-3.750 -0.1023 0.02308 0.01281 -0.0706 0.8177 0.0494
-3.500 -0.1121 0.02036 0.01174 -0.0662 0.8146 0.3665
-3.250 -0.1222 0.02129 0.01385 -0.0576 0.8079 0.6457
-3.000 -0.1072 0.02398 0.01666 -0.0503 0.8048 0.7147
-2.750 -0.0830 0.02443 0.01689 -0.0488 0.8026 0.7281
-2.500 -0.0553 0.02432 0.01658 -0.0491 0.8009 0.7309
-2.250 -0.0409 0.02441 0.01653 -0.0474 0.7969 0.7346
-2.000 -0.0287 0.02441 0.01638 -0.0458 0.7919 0.7397
-1.750 -0.0037 0.02438 0.01620 -0.0456 0.7892 0.7420
-1.500 0.0237 0.02433 0.01602 -0.0459 0.7873 0.7443
-1.250 0.0523 0.02428 0.01583 -0.0465 0.7859 0.7471
-1.000 0.0546 0.02471 0.01622 -0.0431 0.7791 0.7514
-0.750 0.0772 0.02471 0.01609 -0.0431 0.7758 0.7551
-0.500 0.1037 0.02475 0.01606 -0.0431 0.7737 0.7572
-0.250 0.1322 0.02476 0.01600 -0.0436 0.7721 0.7597
0.000 0.1629 0.02471 0.01587 -0.0445 0.7707 0.7625
0.250 0.1566 0.02548 0.01663 -0.0399 0.7619 0.7670
0.500 0.1843 0.02551 0.01660 -0.0405 0.7596 0.7702
0.750 0.2140 0.02552 0.01658 -0.0411 0.7579 0.7725
1.000 0.2448 0.02552 0.01655 -0.0419 0.7565 0.7752
1.500 0.2647 0.02647 0.01749 -0.0377 0.7447 0.7835
1.750 0.2964 0.02645 0.01747 -0.0386 0.7431 0.7860
2.000 0.3294 0.02639 0.01743 -0.0397 0.7418 0.7885
2.250 0.3203 0.02744 0.01852 -0.0348 0.7314 0.7933
2.500 0.3517 0.02741 0.01850 -0.0358 0.7293 0.7972
2.750 0.3853 0.02730 0.01842 -0.0369 0.7278 0.8004
3.250 0.4128 0.02829 0.01952 -0.0337 0.7153 0.8082
3.500 0.4477 0.02809 0.01936 -0.0350 0.7136 0.8120
4.000 0.4810 0.02883 0.02025 -0.0324 0.7008 0.8205
4.250 0.5082 0.02882 0.02034 -0.0326 0.6967 0.8252
4.500 0.5218 0.02928 0.02087 -0.0310 0.6882 0.8302
4.750 0.5576 0.02876 0.02046 -0.0319 0.6855 0.8340
5.250 0.6066 0.02845 0.02037 -0.0309 0.6717 0.8441
5.750 0.6589 0.02759 0.01979 -0.0298 0.6571 0.8554
6.000 0.6709 0.02782 0.02014 -0.0276 0.6452 0.8621
6.500 0.7260 0.02646 0.01908 -0.0263 0.6285 0.8754
7.000 0.7561 0.02647 0.01942 -0.0226 0.6010 0.8947
7.250 0.7732 0.02637 0.01948 -0.0209 0.5844 0.9068
7.500 0.7833 0.02695 0.02023 -0.0191 0.5617 0.9237
7.750 0.8082 0.02676 0.02020 -0.0190 0.5354 0.9452
8.000 0.8481 0.02539 0.01890 -0.0199 0.4978 1.0000
8.250 0.8889 0.02405 0.01722 -0.0201 0.4343 1.0000
8.500 0.9044 0.02463 0.01741 -0.0187 0.3732 1.0000
8.750 0.9122 0.02582 0.01830 -0.0170 0.3226 1.0000
9.000 0.9192 0.02715 0.01941 -0.0153 0.2805 1.0000
9.250 0.9268 0.02851 0.02057 -0.0139 0.2439 1.0000
9.500 0.9357 0.02984 0.02175 -0.0126 0.2139 1.0000
9.750 0.9457 0.03114 0.02295 -0.0114 0.1884 1.0000
10.000 0.9554 0.03248 0.02418 -0.0103 0.1672 1.0000
10.250 0.9667 0.03375 0.02542 -0.0093 0.1490 1.0000
10.500 0.9776 0.03507 0.02672 -0.0083 0.1338 1.0000
10.750 0.9884 0.03642 0.02810 -0.0074 0.1205 1.0000
11.000 0.9989 0.03781 0.02949 -0.0065 0.1091 1.0000
11.250 1.0084 0.03931 0.03099 -0.0056 0.0984 1.0000
11.500 1.0183 0.04081 0.03253 -0.0047 0.0885 1.0000
11.750 1.0288 0.04231 0.03412 -0.0040 0.0791 1.0000
12.000 1.0372 0.04400 0.03585 -0.0031 0.0715 1.0000
12.250 1.0449 0.04577 0.03768 -0.0024 0.0639 1.0000
12.500 1.0536 0.04755 0.03958 -0.0016 0.0567 1.0000
12.750 1.0577 0.04970 0.04174 -0.0009 0.0509 1.0000
13.000 1.0663 0.05158 0.04383 -0.0003 0.0449 1.0000
13.250 1.0688 0.05399 0.04625 0.0002 0.0408 1.0000
13.500 1.0757 0.05617 0.04864 0.0009 0.0364 1.0000
13.750 1.0786 0.05868 0.05125 0.0013 0.0330 1.0000
14.000 1.0798 0.06149 0.05415 0.0017 0.0304 1.0000
14.250 1.0832 0.06420 0.05708 0.0020 0.0274 1.0000
14.500 1.0841 0.06718 0.06020 0.0021 0.0255 1.0000
14.750 1.0819 0.07057 0.06366 0.0019 0.0240 1.0000
15.000 1.0814 0.07398 0.06729 0.0019 0.0226 1.0000
15.250 1.0783 0.07784 0.07142 0.0014 0.0206 1.0000
15.500 1.0746 0.08177 0.07553 0.0006 0.0195 1.0000
15.750 1.0693 0.08603 0.07993 -0.0005 0.0186 1.0000
16.000 1.0623 0.09061 0.08462 -0.0019 0.0178 1.0000
16.250 1.0551 0.09543 0.08958 -0.0033 0.0173 1.0000
16.500 1.0442 0.10126 0.09572 -0.0056 0.0168 1.0000
16.750 1.0315 0.10767 0.10241 -0.0085 0.0163 1.0000
17.000 1.0170 0.11467 0.10966 -0.0120 0.0160 1.0000
17.250 1.0021 0.12212 0.11733 -0.0162 0.0158 1.0000
17.500 0.9857 0.13031 0.12572 -0.0210 0.0159 1.0000
17.750 0.9670 0.13958 0.13514 -0.0266 0.0160 1.0000
18.000 0.9451 0.15032 0.14604 -0.0332 0.0163 1.0000
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