NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S826 Airfoil (s826-nr) Reynolds number: 200,000 Max Cl/Cd: 82.99 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s826-nr-200000.txt Download as CSV file: xf-s826-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S826 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3583 0.11465 0.11128 -0.0402 1.0000 0.0395
-9.750 -0.3654 0.11094 0.10764 -0.0416 1.0000 0.0408
-9.500 -0.3768 0.10703 0.10380 -0.0439 1.0000 0.0416
-8.000 -0.4143 0.08187 0.07893 -0.0530 0.9943 0.0442
-7.750 -0.3999 0.07791 0.07496 -0.0571 0.9886 0.0456
-7.500 -0.3229 0.05264 0.04949 -0.0878 0.9587 0.0527
-7.250 -0.3209 0.04837 0.04463 -0.0989 0.9462 0.0536
-7.000 -0.3635 0.05786 0.05386 -0.0990 0.9551 0.0533
-6.750 -0.3458 0.05003 0.04586 -0.1048 0.9486 0.0553
-6.500 -0.3140 0.04600 0.04184 -0.1088 0.9459 0.0579
-6.250 -0.2438 0.02698 0.02258 -0.1139 0.9226 0.0693
-6.000 -0.2095 0.02327 0.01876 -0.1177 0.9200 0.0739
-5.750 -0.1965 0.02832 0.02202 -0.1199 0.9329 0.0241
-5.500 -0.1671 0.02565 0.01909 -0.1207 0.9256 0.0233
-5.250 -0.1295 0.02341 0.01661 -0.1224 0.9220 0.0234
-5.000 -0.0891 0.02174 0.01475 -0.1245 0.9196 0.0245
-4.750 -0.0600 0.02016 0.01323 -0.1252 0.9111 0.0283
-4.500 -0.0172 0.01870 0.01179 -0.1287 0.9078 0.0366
-4.250 0.0314 0.01713 0.01022 -0.1336 0.9057 0.0560
-4.000 0.0727 0.01560 0.00882 -0.1377 0.8976 0.1040
-3.750 0.1246 0.01428 0.00850 -0.1440 0.8948 0.4468
-3.500 0.1604 0.01464 0.00878 -0.1446 0.8892 0.4745
-3.250 0.1916 0.01503 0.00920 -0.1441 0.8814 0.4922
-3.000 0.2339 0.01508 0.00917 -0.1462 0.8778 0.5055
-2.750 0.2662 0.01518 0.00927 -0.1464 0.8674 0.5139
-2.500 0.3085 0.01513 0.00914 -0.1487 0.8607 0.5232
-2.250 0.3485 0.01503 0.00894 -0.1509 0.8511 0.5305
-2.000 0.3891 0.01472 0.00847 -0.1537 0.8400 0.5353
-1.750 0.4284 0.01446 0.00808 -0.1561 0.8288 0.5372
-1.500 0.4660 0.01429 0.00778 -0.1581 0.8174 0.5396
-1.250 0.5008 0.01418 0.00752 -0.1597 0.8052 0.5425
-1.000 0.5328 0.01409 0.00728 -0.1608 0.7923 0.5457
-0.750 0.5650 0.01401 0.00703 -0.1621 0.7804 0.5489
-0.500 0.5947 0.01399 0.00694 -0.1626 0.7699 0.5509
-0.250 0.6253 0.01402 0.00688 -0.1632 0.7608 0.5534
0.000 0.6527 0.01407 0.00691 -0.1633 0.7507 0.5564
0.250 0.6829 0.01413 0.00687 -0.1640 0.7424 0.5600
0.500 0.7129 0.01416 0.00680 -0.1648 0.7338 0.5637
0.750 0.7410 0.01422 0.00685 -0.1650 0.7263 0.5661
1.000 0.7691 0.01430 0.00693 -0.1652 0.7192 0.5689
1.250 0.7980 0.01442 0.00704 -0.1656 0.7129 0.5725
1.500 0.8264 0.01452 0.00712 -0.1659 0.7058 0.5768
1.750 0.8571 0.01463 0.00717 -0.1667 0.7006 0.5803
2.000 0.8827 0.01474 0.00738 -0.1665 0.6941 0.5833
2.250 0.9116 0.01487 0.00754 -0.1668 0.6886 0.5870
2.500 0.9404 0.01503 0.00770 -0.1673 0.6832 0.5915
2.750 0.9672 0.01515 0.00788 -0.1673 0.6767 0.5956
3.000 0.9966 0.01530 0.00805 -0.1677 0.6714 0.5996
3.250 1.0219 0.01545 0.00831 -0.1674 0.6646 0.6042
3.500 1.0510 0.01557 0.00841 -0.1678 0.6581 0.6091
3.750 1.0759 0.01569 0.00864 -0.1672 0.6502 0.6129
4.000 1.1039 0.01577 0.00874 -0.1672 0.6421 0.6179
4.250 1.1286 0.01589 0.00894 -0.1667 0.6330 0.6238
4.500 1.1561 0.01597 0.00907 -0.1666 0.6252 0.6287
4.750 1.1800 0.01607 0.00930 -0.1658 0.6160 0.6347
5.000 1.2058 0.01617 0.00946 -0.1655 0.6072 0.6404
5.250 1.2312 0.01624 0.00962 -0.1649 0.5980 0.6461
5.750 1.2793 0.01641 0.01002 -0.1634 0.5781 0.6590
6.000 1.3038 0.01648 0.01014 -0.1627 0.5667 0.6671
6.250 1.3244 0.01652 0.01035 -0.1612 0.5537 0.6740
6.500 1.3456 0.01660 0.01054 -0.1598 0.5397 0.6830
6.750 1.3652 0.01665 0.01074 -0.1581 0.5241 0.6907
7.000 1.3843 0.01675 0.01093 -0.1563 0.5062 0.7000
7.250 1.4001 0.01687 0.01119 -0.1539 0.4831 0.7097
7.500 1.4138 0.01705 0.01147 -0.1511 0.4533 0.7197
7.750 1.4222 0.01744 0.01179 -0.1474 0.4051 0.7312
8.000 1.4191 0.01836 0.01238 -0.1418 0.3431 0.7436
8.250 1.4136 0.01971 0.01345 -0.1363 0.2875 0.7575
8.500 1.4102 0.02115 0.01467 -0.1313 0.2392 0.7736
8.750 1.4075 0.02263 0.01598 -0.1268 0.2005 0.7943
9.000 1.4062 0.02402 0.01731 -0.1225 0.1692 0.8261
9.250 1.3994 0.02502 0.01839 -0.1172 0.1481 1.0000
9.500 1.4024 0.02677 0.02000 -0.1144 0.1259 1.0000
9.750 1.4047 0.02858 0.02171 -0.1117 0.1082 1.0000
10.000 1.4069 0.03045 0.02352 -0.1091 0.0940 1.0000
10.250 1.4098 0.03236 0.02540 -0.1068 0.0819 1.0000
10.500 1.4128 0.03435 0.02741 -0.1047 0.0714 1.0000
10.750 1.4137 0.03661 0.02968 -0.1026 0.0628 1.0000
11.000 1.4128 0.03912 0.03217 -0.1007 0.0551 1.0000
11.250 1.4174 0.04128 0.03443 -0.0992 0.0475 1.0000
11.500 1.4148 0.04424 0.03742 -0.0975 0.0415 1.0000
11.750 1.4151 0.04699 0.04019 -0.0963 0.0356 1.0000
12.000 1.4154 0.04992 0.04324 -0.0950 0.0306 1.0000
12.250 1.4131 0.05318 0.04649 -0.0941 0.0270 1.0000
12.500 1.4152 0.05609 0.04955 -0.0932 0.0235 1.0000
12.750 1.4162 0.05911 0.05261 -0.0927 0.0209 1.0000
13.000 1.4144 0.06270 0.05628 -0.0918 0.0189 1.0000
13.250 1.4175 0.06568 0.05942 -0.0914 0.0170 1.0000
13.500 1.4181 0.06895 0.06275 -0.0914 0.0155 1.0000
13.750 1.4174 0.07261 0.06652 -0.0910 0.0141 1.0000
14.000 1.4194 0.07593 0.07003 -0.0909 0.0130 1.0000
14.250 1.4207 0.07943 0.07368 -0.0909 0.0122 1.0000
14.500 1.4212 0.08304 0.07740 -0.0910 0.0116 1.0000
14.750 1.4216 0.08676 0.08119 -0.0911 0.0111 1.0000
15.000 1.4224 0.09084 0.08542 -0.0906 0.0108 1.0000
15.250 1.4171 0.09563 0.09050 -0.0915 0.0105 1.0000
15.500 1.4108 0.10071 0.09585 -0.0927 0.0104 1.0000
15.750 1.4030 0.10612 0.10152 -0.0943 0.0103 1.0000
16.000 1.3929 0.11204 0.10771 -0.0964 0.0102 1.0000
16.250 1.3808 0.11848 0.11441 -0.0991 0.0101 1.0000
16.500 1.3685 0.12515 0.12132 -0.1023 0.0101 1.0000
16.750 1.3543 0.13245 0.12887 -0.1063 0.0101 1.0000
17.000 1.3409 0.13982 0.13645 -0.1106 0.0102 1.0000
17.250 1.3266 0.14774 0.14457 -0.1156 0.0103 1.0000
17.500 1.3105 0.15658 0.15363 -0.1216 0.0103 1.0000
17.750 1.2969 0.16517 0.16238 -0.1276 0.0105 1.0000
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