NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S831 Airfoil (s831-nr) Reynolds number: 500,000 Max Cl/Cd: 113.91 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s831-nr-500000.txt Download as CSV file: xf-s831-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S831 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 0.1271 0.09697 0.09374 -0.1548 0.8260 0.0148
-12.500 0.1268 0.09350 0.09024 -0.1569 0.8230 0.0150
-12.250 0.1277 0.09001 0.08673 -0.1587 0.8200 0.0151
-12.000 0.1299 0.08660 0.08333 -0.1601 0.8167 0.0152
-11.750 0.1324 0.08314 0.07986 -0.1615 0.8135 0.0152
-11.500 0.1348 0.07958 0.07628 -0.1629 0.8106 0.0152
-11.250 0.1368 0.07570 0.07236 -0.1632 0.8079 0.0155
-11.000 0.1428 0.07294 0.06960 -0.1636 0.8051 0.0158
-10.750 0.1469 0.07003 0.06670 -0.1643 0.8020 0.0161
-10.500 0.1054 0.07485 0.07143 -0.1803 0.8140 0.0154
-10.250 0.1078 0.07199 0.06854 -0.1810 0.8102 0.0156
-10.000 0.1100 0.06898 0.06548 -0.1823 0.8066 0.0158
-9.750 0.1052 0.06462 0.06115 -0.1849 0.8025 0.0158
-9.500 0.0955 0.06032 0.05683 -0.1874 0.7983 0.0158
-9.250 0.0880 0.05724 0.05368 -0.1884 0.7946 0.0160
-9.000 0.0746 0.05404 0.05042 -0.1888 0.7908 0.0160
-8.750 0.0610 0.05140 0.04775 -0.1879 0.7868 0.0160
-8.500 0.0492 0.04944 0.04573 -0.1861 0.7829 0.0162
-8.250 0.0399 0.04756 0.04374 -0.1842 0.7796 0.0163
-8.000 0.0373 0.04549 0.04157 -0.1827 0.7764 0.0166
-7.750 0.0373 0.04340 0.03940 -0.1812 0.7733 0.0169
-7.500 0.0407 0.04128 0.03714 -0.1798 0.7705 0.0172
-7.250 0.0472 0.03912 0.03483 -0.1784 0.7679 0.0179
-7.000 0.0572 0.03690 0.03240 -0.1771 0.7656 0.0188
-6.750 0.0736 0.03599 0.03105 -0.1748 0.7633 0.0200
-6.500 0.0755 0.03175 0.02660 -0.1730 0.7609 0.0206
-6.250 0.0911 0.02985 0.02466 -0.1726 0.7587 0.0211
-6.000 0.1087 0.02834 0.02306 -0.1721 0.7564 0.0218
-5.750 0.1282 0.02686 0.02143 -0.1716 0.7543 0.0228
-5.500 0.1503 0.02549 0.01983 -0.1710 0.7523 0.0246
-5.250 0.1752 0.02543 0.01932 -0.1699 0.7504 0.0266
-5.000 0.1964 0.01926 0.01280 -0.1684 0.7488 0.0164
-4.750 0.2215 0.01658 0.00974 -0.1664 0.7471 0.0114
-4.500 0.2438 0.01552 0.00862 -0.1656 0.7453 0.0112
-4.250 0.2656 0.01471 0.00775 -0.1647 0.7434 0.0112
-4.000 0.2879 0.01410 0.00708 -0.1641 0.7416 0.0112
-3.750 0.3094 0.01331 0.00624 -0.1636 0.7398 0.0119
-3.500 0.3348 0.01290 0.00579 -0.1637 0.7383 0.0131
-3.250 0.3615 0.01250 0.00534 -0.1641 0.7368 0.0180
-3.000 0.3896 0.01223 0.00509 -0.1648 0.7353 0.0358
-2.750 0.4154 0.01207 0.00500 -0.1650 0.7337 0.0525
-2.500 0.4407 0.01184 0.00483 -0.1652 0.7319 0.0770
-2.250 0.4646 0.00992 0.00456 -0.1671 0.7301 0.6201
-2.000 0.4920 0.01015 0.00479 -0.1671 0.7286 0.6522
-1.750 0.5196 0.01037 0.00498 -0.1672 0.7270 0.6678
-1.500 0.5480 0.01058 0.00512 -0.1676 0.7256 0.6795
-1.250 0.5757 0.01073 0.00529 -0.1677 0.7243 0.6866
-1.000 0.6053 0.01092 0.00539 -0.1684 0.7231 0.6947
-0.750 0.6334 0.01108 0.00556 -0.1686 0.7219 0.7004
-0.500 0.6631 0.01127 0.00571 -0.1694 0.7207 0.7053
-0.250 0.6899 0.01135 0.00576 -0.1697 0.7193 0.7079
0.000 0.7161 0.01141 0.00580 -0.1699 0.7177 0.7100
0.250 0.7422 0.01145 0.00585 -0.1700 0.7161 0.7116
0.500 0.7688 0.01152 0.00592 -0.1703 0.7146 0.7133
0.750 0.7959 0.01160 0.00601 -0.1706 0.7133 0.7150
1.000 0.8237 0.01168 0.00609 -0.1711 0.7120 0.7170
1.250 0.8521 0.01177 0.00617 -0.1717 0.7108 0.7193
1.500 0.8812 0.01185 0.00625 -0.1725 0.7096 0.7218
1.750 0.9110 0.01194 0.00631 -0.1735 0.7085 0.7242
2.000 0.9416 0.01204 0.00638 -0.1746 0.7074 0.7263
2.250 0.9717 0.01218 0.00653 -0.1756 0.7062 0.7281
2.500 0.9959 0.01233 0.00675 -0.1754 0.7049 0.7300
2.750 1.0192 0.01248 0.00697 -0.1750 0.7035 0.7323
3.000 1.0433 0.01264 0.00718 -0.1748 0.7020 0.7347
3.250 1.0682 0.01280 0.00738 -0.1748 0.7005 0.7375
3.500 1.0941 0.01295 0.00757 -0.1750 0.6989 0.7403
3.750 1.1202 0.01307 0.00773 -0.1752 0.6975 0.7426
4.000 1.1468 0.01319 0.00792 -0.1755 0.6963 0.7448
4.250 1.1747 0.01333 0.00812 -0.1760 0.6952 0.7471
4.500 1.2039 0.01346 0.00828 -0.1769 0.6941 0.7496
4.750 1.2343 0.01360 0.00846 -0.1780 0.6929 0.7524
5.000 1.2652 0.01382 0.00872 -0.1792 0.6918 0.7552
5.250 1.2848 0.01407 0.00907 -0.1782 0.6902 0.7579
5.500 1.3011 0.01428 0.00941 -0.1764 0.6876 0.7606
5.750 1.3251 0.01397 0.00915 -0.1758 0.6823 0.7635
6.000 1.3540 0.01329 0.00844 -0.1759 0.6735 0.7666
6.250 1.3760 0.01285 0.00799 -0.1748 0.6655 0.7699
6.500 1.3942 0.01279 0.00798 -0.1731 0.6601 0.7729
6.750 1.4048 0.01279 0.00810 -0.1699 0.6551 0.7758
7.000 1.4269 0.01271 0.00807 -0.1691 0.6509 0.7790
7.250 1.4413 0.01277 0.00820 -0.1668 0.6464 0.7829
7.500 1.4443 0.01294 0.00846 -0.1622 0.6401 0.7871
7.750 1.4660 0.01287 0.00843 -0.1612 0.6341 0.7902
8.000 1.4619 0.01325 0.00896 -0.1555 0.6271 0.7944
8.250 1.4732 0.01340 0.00914 -0.1527 0.6187 0.7986
8.500 1.4735 0.01384 0.00968 -0.1480 0.6085 0.8029
8.750 1.4761 0.01435 0.01028 -0.1439 0.5971 0.8071
9.000 1.4755 0.01503 0.01100 -0.1393 0.5807 0.8121
9.250 1.4687 0.01607 0.01201 -0.1340 0.5536 0.8173
9.500 1.4512 0.01773 0.01352 -0.1272 0.5130 0.8223
9.750 1.4241 0.02025 0.01581 -0.1195 0.4682 0.8281
10.000 1.3940 0.02334 0.01867 -0.1121 0.4234 0.8334
10.250 1.3710 0.02637 0.02151 -0.1062 0.3836 0.8388
10.500 1.3476 0.02972 0.02463 -0.1008 0.3389 0.8448
10.750 1.3317 0.03272 0.02746 -0.0965 0.2998 0.8504
11.000 1.3175 0.03576 0.03029 -0.0927 0.2578 0.8568
11.250 1.3113 0.03828 0.03267 -0.0899 0.2222 0.8633
11.500 1.3071 0.04072 0.03496 -0.0874 0.1896 0.8709
11.750 1.3058 0.04295 0.03707 -0.0852 0.1605 0.8794
12.000 1.3068 0.04501 0.03905 -0.0834 0.1352 0.8905
12.250 1.3091 0.04691 0.04091 -0.0815 0.1141 0.9096
12.500 1.3134 0.04872 0.04271 -0.0802 0.0956 1.0000
12.750 1.3192 0.05073 0.04463 -0.0793 0.0788 1.0000
13.000 1.3258 0.05270 0.04654 -0.0784 0.0645 1.0000
13.250 1.3321 0.05472 0.04847 -0.0776 0.0507 1.0000
13.500 1.3388 0.05671 0.05042 -0.0768 0.0399 1.0000
13.750 1.3444 0.05885 0.05250 -0.0760 0.0302 1.0000
14.000 1.3518 0.06084 0.05447 -0.0754 0.0239 1.0000
14.250 1.3582 0.06294 0.05659 -0.0747 0.0192 1.0000
14.500 1.3632 0.06523 0.05889 -0.0739 0.0152 1.0000
14.750 1.3689 0.06749 0.06116 -0.0733 0.0118 1.0000
15.000 1.3753 0.06970 0.06344 -0.0728 0.0097 1.0000
15.250 1.3777 0.07241 0.06620 -0.0721 0.0073 1.0000
15.500 1.3766 0.07556 0.06942 -0.0713 0.0060 1.0000
15.750 1.3821 0.07800 0.07197 -0.0710 0.0050 1.0000
16.000 1.3845 0.08084 0.07489 -0.0706 0.0044 1.0000
16.250 1.3804 0.08459 0.07875 -0.0701 0.0040 1.0000
16.500 1.3831 0.08753 0.08181 -0.0700 0.0037 1.0000
16.750 1.3846 0.09063 0.08503 -0.0699 0.0034 1.0000
17.000 1.3850 0.09393 0.08844 -0.0699 0.0032 1.0000
17.250 1.3852 0.09728 0.09189 -0.0700 0.0031 1.0000
17.500 1.3845 0.10082 0.09553 -0.0703 0.0029 1.0000
17.750 1.3815 0.10471 0.09952 -0.0706 0.0028 1.0000
18.000 1.3765 0.10891 0.10384 -0.0711 0.0027 1.0000
18.250 1.3698 0.11332 0.10836 -0.0716 0.0026 1.0000
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