NREL's S812 Airfoil (s812-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S812 Airfoil (s812-nr) Reynolds number: 200,000 Max Cl/Cd: 56.22 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s812-nr-200000.txt Download as CSV file: xf-s812-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S812 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4338 0.09771 0.09436 -0.0718 1.0000 0.0497
-13.500 -0.4568 0.09273 0.08933 -0.0727 1.0000 0.0495
-13.250 -0.4814 0.08793 0.08449 -0.0732 1.0000 0.0493
-13.000 -0.5075 0.08332 0.07981 -0.0732 1.0000 0.0491
-12.750 -0.5333 0.07903 0.07545 -0.0727 1.0000 0.0490
-12.500 -0.5588 0.07524 0.07161 -0.0716 1.0000 0.0489
-11.250 -0.7096 0.06423 0.05952 -0.0730 0.9771 0.0486
-11.000 -0.7270 0.06596 0.06070 -0.0737 0.9323 0.0508
-10.750 -0.7173 0.05749 0.05196 -0.0766 0.9095 0.0527
-10.500 -0.6748 0.05193 0.04639 -0.0817 0.8929 0.0556
-10.250 -0.6519 0.04917 0.04330 -0.0840 0.8683 0.0595
-10.000 -0.6607 0.05244 0.04593 -0.0802 0.8416 0.0637
-9.750 -0.6351 0.04444 0.03788 -0.0825 0.8316 0.0680
-9.500 -0.6161 0.04224 0.03551 -0.0824 0.8209 0.0723
-9.250 -0.6259 0.04516 0.03793 -0.0776 0.8090 0.0780
-9.000 -0.4594 0.03436 0.02638 -0.0880 0.8101 0.0412
-8.750 -0.3519 0.03339 0.02532 -0.0918 0.8068 0.0418
-8.500 -0.2938 0.03391 0.02585 -0.0918 0.8001 0.0430
-8.250 -0.2582 0.03424 0.02615 -0.0910 0.7936 0.0446
-8.000 -0.2342 0.03418 0.02605 -0.0902 0.7879 0.0470
-7.750 -0.2132 0.03402 0.02585 -0.0893 0.7823 0.0492
-7.500 -0.1945 0.03377 0.02553 -0.0882 0.7776 0.0506
-7.250 -0.1814 0.03329 0.02504 -0.0867 0.7733 0.0520
-7.000 -0.1779 0.03219 0.02397 -0.0849 0.7687 0.0545
-6.750 -0.1760 0.03091 0.02267 -0.0833 0.7644 0.0567
-6.500 -0.1733 0.02966 0.02134 -0.0818 0.7607 0.0598
-6.250 -0.1717 0.02835 0.01995 -0.0802 0.7572 0.0624
-6.000 -0.1704 0.02702 0.01856 -0.0785 0.7536 0.0647
-5.750 -0.1763 0.02532 0.01679 -0.0762 0.7502 0.0693
-5.500 -0.1755 0.02399 0.01538 -0.0743 0.7471 0.0755
-5.250 0.0719 0.05138 0.04473 -0.0739 0.7451 0.5687
-5.000 0.1070 0.05021 0.04346 -0.0752 0.7428 0.5711
-4.750 0.1331 0.04930 0.04253 -0.0757 0.7402 0.5721
-4.500 0.1574 0.04852 0.04170 -0.0761 0.7374 0.5733
-4.250 0.1778 0.04778 0.04092 -0.0761 0.7348 0.5747
-4.000 0.1966 0.04710 0.04019 -0.0760 0.7325 0.5765
-3.750 0.1451 0.04682 0.03994 -0.0695 0.7301 0.5844
-3.500 0.1508 0.04565 0.03872 -0.0684 0.7281 0.5845
-3.250 0.1707 0.04462 0.03769 -0.0684 0.7262 0.5843
-3.000 0.2168 0.04265 0.03568 -0.0717 0.7244 0.5727
-2.750 0.2457 0.04238 0.03541 -0.0722 0.7222 0.5752
-2.500 0.0992 0.03376 0.02684 -0.0601 0.7186 0.5569
-2.250 0.0489 0.02804 0.02097 -0.0584 0.7158 0.5698
-2.000 0.0756 0.02806 0.02095 -0.0584 0.7142 0.5704
-1.750 0.1021 0.02810 0.02096 -0.0584 0.7127 0.5711
-1.500 0.1253 0.02814 0.02104 -0.0581 0.7110 0.5721
-1.250 0.1470 0.02814 0.02107 -0.0576 0.7090 0.5734
-1.000 0.1685 0.02809 0.02104 -0.0572 0.7066 0.5752
-0.750 0.1735 0.02545 0.01821 -0.0590 0.7041 0.5852
-0.500 0.1989 0.02557 0.01835 -0.0588 0.7023 0.5861
-0.250 0.2243 0.02570 0.01851 -0.0587 0.7006 0.5871
0.000 0.2500 0.02582 0.01864 -0.0588 0.6991 0.5883
0.250 0.2761 0.02591 0.01872 -0.0590 0.6977 0.5899
0.500 0.2987 0.02592 0.01876 -0.0589 0.6957 0.5922
0.750 0.3161 0.02547 0.01830 -0.0594 0.6930 0.5977
1.000 0.3366 0.02531 0.01814 -0.0596 0.6908 0.6012
1.250 0.3586 0.02559 0.01851 -0.0590 0.6885 0.6024
1.500 0.3830 0.02579 0.01875 -0.0588 0.6863 0.6038
1.750 0.4088 0.02594 0.01894 -0.0590 0.6845 0.6056
2.000 0.4359 0.02600 0.01902 -0.0595 0.6830 0.6080
2.250 0.4650 0.02590 0.01889 -0.0608 0.6814 0.6116
2.500 0.4772 0.02615 0.01917 -0.0603 0.6776 0.6159
2.750 0.4909 0.02670 0.01985 -0.0586 0.6738 0.6174
3.000 0.5127 0.02704 0.02029 -0.0579 0.6710 0.6191
3.250 0.5401 0.02718 0.02049 -0.0581 0.6688 0.6211
3.500 0.5719 0.02716 0.02050 -0.0592 0.6671 0.6237
3.750 0.6060 0.02707 0.02041 -0.0609 0.6655 0.6270
4.000 0.5978 0.02824 0.02167 -0.0574 0.6572 0.6309
4.250 0.6246 0.02825 0.02178 -0.0574 0.6543 0.6324
4.500 0.6589 0.02805 0.02165 -0.0585 0.6522 0.6342
4.750 0.6973 0.02775 0.02141 -0.0601 0.6505 0.6362
5.000 0.6839 0.02921 0.02303 -0.0549 0.6410 0.6385
5.250 0.7242 0.02862 0.02249 -0.0569 0.6381 0.6419
5.500 0.7802 0.02736 0.02118 -0.0615 0.6357 0.6462
5.750 0.7830 0.02799 0.02197 -0.0580 0.6271 0.6478
6.000 0.8295 0.02677 0.02082 -0.0603 0.6225 0.6498
6.250 0.8841 0.02527 0.01933 -0.0637 0.6183 0.6521
6.500 0.8954 0.02532 0.01954 -0.0613 0.6089 0.6545
6.750 0.9478 0.02387 0.01805 -0.0648 0.6037 0.6580
7.000 0.9650 0.02368 0.01797 -0.0635 0.5940 0.6615
7.250 1.0035 0.02247 0.01683 -0.0645 0.5861 0.6636
7.500 1.0259 0.02181 0.01630 -0.0632 0.5755 0.6658
7.750 1.0449 0.02132 0.01594 -0.0615 0.5644 0.6681
8.000 1.0665 0.02072 0.01546 -0.0603 0.5527 0.6708
8.250 1.0835 0.02026 0.01512 -0.0584 0.5382 0.6739
8.500 1.0965 0.01995 0.01489 -0.0560 0.5191 0.6770
8.750 1.1001 0.01969 0.01473 -0.0515 0.4947 0.6789
9.000 1.1019 0.01960 0.01452 -0.0469 0.4503 0.6811
9.250 1.0916 0.02040 0.01491 -0.0410 0.3911 0.6833
9.500 1.0737 0.02199 0.01618 -0.0351 0.3426 0.6855
9.750 1.0554 0.02400 0.01795 -0.0301 0.3004 0.6880
10.000 1.0386 0.02640 0.02011 -0.0264 0.2622 0.6905
10.250 1.0245 0.02897 0.02246 -0.0235 0.2252 0.6925
10.500 1.0119 0.03157 0.02490 -0.0209 0.1923 0.6942
10.750 1.0023 0.03415 0.02732 -0.0189 0.1628 0.6960
11.000 0.9964 0.03658 0.02962 -0.0172 0.1387 0.6980
11.250 0.9928 0.03894 0.03186 -0.0159 0.1200 0.7001
11.500 0.9921 0.04119 0.03401 -0.0148 0.1056 0.7026
11.750 0.9952 0.04321 0.03599 -0.0140 0.0941 0.7052
12.000 1.0002 0.04513 0.03789 -0.0134 0.0846 0.7076
12.250 1.0028 0.04716 0.03987 -0.0126 0.0769 0.7096
12.500 1.0121 0.04873 0.04154 -0.0123 0.0695 0.7118
12.750 1.0173 0.05070 0.04350 -0.0118 0.0636 0.7141
13.000 1.0267 0.05239 0.04528 -0.0116 0.0581 0.7167
13.250 1.0322 0.05448 0.04735 -0.0113 0.0532 0.7194
13.500 1.0418 0.05634 0.04931 -0.0115 0.0481 0.7225
13.750 1.0461 0.05850 0.05146 -0.0109 0.0436 0.7247
14.000 1.0537 0.06050 0.05363 -0.0108 0.0393 0.7274
14.250 1.0589 0.06274 0.05581 -0.0104 0.0354 0.7300
14.500 1.0667 0.06493 0.05818 -0.0103 0.0318 0.7330
14.750 1.0731 0.06728 0.06054 -0.0106 0.0292 0.7360
15.000 1.0835 0.06920 0.06249 -0.0102 0.0269 0.7386
15.250 1.0901 0.07155 0.06505 -0.0103 0.0252 0.7413
15.500 1.0986 0.07376 0.06742 -0.0103 0.0240 0.7445
15.750 1.1062 0.07611 0.06985 -0.0106 0.0228 0.7481
16.000 1.1164 0.07831 0.07208 -0.0108 0.0218 0.7520
16.250 1.1261 0.08091 0.07486 -0.0104 0.0210 0.7551
16.500 1.1268 0.08430 0.07852 -0.0109 0.0207 0.7585
16.750 1.1251 0.08813 0.08262 -0.0116 0.0203 0.7620
17.000 1.1217 0.09233 0.08707 -0.0127 0.0200 0.7656
17.250 1.1148 0.09700 0.09201 -0.0141 0.0197 0.7687
17.500 1.1055 0.10206 0.09733 -0.0158 0.0195 0.7716
17.750 1.0946 0.10754 0.10306 -0.0180 0.0193 0.7748
18.000 1.0805 0.11373 0.10952 -0.0207 0.0192 0.7780
18.250 1.0650 0.12047 0.11649 -0.0242 0.0191 0.7814
18.500 1.0454 0.12821 0.12450 -0.0285 0.0192 0.7839
18.750 1.0224 0.13703 0.13358 -0.0337 0.0194 0.7861
19.000 0.9950 0.14742 0.14422 -0.0402 0.0197 0.7878
19.250 0.9653 0.15914 0.15615 -0.0478 0.0203 0.7890
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