NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S821 Airfoil (s821-nr) Reynolds number: 1,000,000 Max Cl/Cd: 87.55 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s821-nr-1000000.txt Download as CSV file: xf-s821-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S821 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0796 0.08612 0.08273 -0.0501 1.0000 0.1738
-16.500 -1.0773 0.08405 0.08066 -0.0505 1.0000 0.1749
-16.250 -1.0776 0.08161 0.07821 -0.0510 1.0000 0.1759
-16.000 -1.0780 0.07921 0.07579 -0.0515 1.0000 0.1768
-15.750 -1.0831 0.07624 0.07279 -0.0522 1.0000 0.1778
-15.500 -1.1034 0.07155 0.06804 -0.0536 1.0000 0.1792
-15.250 -1.1311 0.06615 0.06254 -0.0551 1.0000 0.1806
-15.000 -1.1569 0.06113 0.05741 -0.0564 1.0000 0.1817
-14.750 -1.1735 0.05726 0.05345 -0.0573 1.0000 0.1825
-14.500 -1.1882 0.05369 0.04980 -0.0579 1.0000 0.1830
-14.250 -1.2006 0.05056 0.04659 -0.0583 1.0000 0.1836
-14.000 -1.1975 0.04929 0.04531 -0.0575 1.0000 0.1848
-13.750 -1.1845 0.04780 0.04382 -0.0588 0.9994 0.1859
-13.500 -1.1641 0.04601 0.04202 -0.0619 0.9977 0.1867
-13.250 -1.1473 0.04388 0.03987 -0.0651 0.9957 0.1875
-13.000 -1.1286 0.04200 0.03795 -0.0683 0.9939 0.1883
-12.750 -1.1076 0.04031 0.03624 -0.0715 0.9923 0.1890
-12.500 -1.0871 0.03843 0.03432 -0.0751 0.9911 0.1898
-12.250 -1.0632 0.03691 0.03276 -0.0788 0.9902 0.1905
-12.000 -1.0621 0.03491 0.03072 -0.0787 0.9853 0.1912
-11.750 -1.0457 0.03323 0.02900 -0.0811 0.9825 0.1919
-11.500 -1.0252 0.03162 0.02736 -0.0840 0.9803 0.1925
-11.250 -1.0018 0.03007 0.02576 -0.0874 0.9785 0.1932
-11.000 -0.9754 0.02865 0.02429 -0.0910 0.9771 0.1937
-10.750 -0.9469 0.02735 0.02294 -0.0947 0.9760 0.1942
-10.500 -0.9415 0.02592 0.02147 -0.0944 0.9701 0.1945
-10.250 -0.9229 0.02475 0.02027 -0.0957 0.9661 0.1952
-10.000 -0.8990 0.02361 0.01913 -0.0978 0.9636 0.1965
-9.750 -0.8712 0.02247 0.01799 -0.1007 0.9617 0.1975
-9.500 -0.8415 0.02132 0.01683 -0.1040 0.9603 0.1984
-9.250 -0.8427 0.01996 0.01544 -0.1021 0.9513 0.1991
-9.000 -0.8134 0.01886 0.01433 -0.1049 0.9483 0.1998
-8.750 -0.7788 0.01792 0.01337 -0.1083 0.9465 0.2006
-8.500 -0.7418 0.01706 0.01249 -0.1120 0.9453 0.2014
-8.250 -0.7028 0.01627 0.01169 -0.1159 0.9444 0.2022
-8.000 -0.6621 0.01556 0.01096 -0.1199 0.9436 0.2031
-7.750 -0.6536 0.01490 0.01027 -0.1177 0.9333 0.2037
-7.500 -0.6192 0.01440 0.00975 -0.1198 0.9306 0.2044
-7.250 -0.5818 0.01395 0.00928 -0.1223 0.9283 0.2051
-7.000 -0.5419 0.01353 0.00884 -0.1251 0.9262 0.2056
-6.750 -0.5321 0.01316 0.00844 -0.1222 0.9123 0.2060
-6.500 -0.4874 0.01282 0.00808 -0.1258 0.9088 0.2064
-6.250 -0.4550 0.01239 0.00763 -0.1272 0.8972 0.2072
-6.000 -0.4094 0.01188 0.00709 -0.1312 0.8878 0.2089
-5.750 -0.3686 0.01151 0.00667 -0.1342 0.8721 0.2102
-5.500 -0.3342 0.01128 0.00636 -0.1358 0.8523 0.2112
-5.250 -0.3046 0.01113 0.00613 -0.1363 0.8317 0.2122
-5.000 -0.2770 0.01101 0.00593 -0.1365 0.8119 0.2131
-4.750 -0.2500 0.01092 0.00577 -0.1364 0.7936 0.2140
-4.500 -0.2229 0.01083 0.00562 -0.1364 0.7774 0.2150
-4.250 -0.1962 0.01077 0.00547 -0.1363 0.7614 0.2159
-4.000 -0.1689 0.01068 0.00534 -0.1362 0.7459 0.2167
-3.750 -0.1415 0.01061 0.00520 -0.1362 0.7313 0.2175
-3.500 -0.1148 0.01057 0.00508 -0.1359 0.7163 0.2181
-3.250 -0.0863 0.01050 0.00497 -0.1360 0.7040 0.2187
-3.000 -0.0589 0.01047 0.00488 -0.1359 0.6912 0.2191
-2.750 -0.0302 0.01028 0.00467 -0.1362 0.6793 0.2208
-2.500 -0.0022 0.01016 0.00451 -0.1363 0.6671 0.2225
-2.250 0.0267 0.01005 0.00439 -0.1365 0.6553 0.2240
-2.000 0.0549 0.01000 0.00430 -0.1365 0.6433 0.2253
-1.750 0.0840 0.00994 0.00422 -0.1366 0.6322 0.2266
-1.500 0.1122 0.00993 0.00416 -0.1366 0.6212 0.2280
-1.250 0.1417 0.00988 0.00410 -0.1368 0.6115 0.2293
-1.000 0.1697 0.00989 0.00406 -0.1366 0.6003 0.2305
-0.750 0.1994 0.00986 0.00401 -0.1368 0.5912 0.2316
-0.500 0.2277 0.00988 0.00398 -0.1367 0.5803 0.2323
-0.250 0.2575 0.00979 0.00389 -0.1369 0.5710 0.2344
0.000 0.2872 0.00972 0.00382 -0.1371 0.5616 0.2369
0.250 0.3159 0.00972 0.00379 -0.1371 0.5520 0.2389
0.500 0.3459 0.00969 0.00377 -0.1373 0.5437 0.2409
0.750 0.3742 0.00972 0.00376 -0.1372 0.5337 0.2427
1.000 0.4037 0.00972 0.00376 -0.1372 0.5259 0.2445
1.250 0.4328 0.00975 0.00377 -0.1372 0.5174 0.2459
1.500 0.4610 0.00979 0.00377 -0.1370 0.5074 0.2482
1.750 0.4912 0.00974 0.00375 -0.1372 0.4986 0.2519
2.000 0.5191 0.00980 0.00378 -0.1370 0.4875 0.2547
2.250 0.5485 0.00981 0.00380 -0.1370 0.4790 0.2574
2.500 0.5764 0.00988 0.00384 -0.1367 0.4688 0.2597
2.750 0.6047 0.00996 0.00388 -0.1364 0.4601 0.2614
3.000 0.6342 0.00995 0.00390 -0.1365 0.4515 0.2656
3.250 0.6617 0.01004 0.00396 -0.1361 0.4415 0.2692
3.500 0.6909 0.01006 0.00401 -0.1361 0.4336 0.2725
3.750 0.7181 0.01017 0.00408 -0.1356 0.4239 0.2753
4.000 0.7461 0.01026 0.00416 -0.1352 0.4164 0.2773
4.250 0.7748 0.01029 0.00421 -0.1351 0.4080 0.2823
4.500 0.8012 0.01040 0.00431 -0.1345 0.3987 0.2862
4.750 0.8291 0.01046 0.00439 -0.1341 0.3911 0.2900
5.000 0.8544 0.01060 0.00449 -0.1333 0.3815 0.2929
5.250 0.8813 0.01068 0.00458 -0.1327 0.3733 0.2969
5.500 0.9074 0.01079 0.00470 -0.1321 0.3632 0.3017
5.750 0.9331 0.01092 0.00482 -0.1313 0.3533 0.3057
6.000 0.9572 0.01111 0.00497 -0.1302 0.3409 0.3091
6.250 0.9818 0.01128 0.00511 -0.1292 0.3282 0.3115
6.500 1.0059 0.01149 0.00529 -0.1283 0.3126 0.3170
6.750 1.0288 0.01177 0.00551 -0.1271 0.2935 0.3215
7.000 1.0488 0.01221 0.00581 -0.1255 0.2663 0.3254
7.250 1.0667 0.01274 0.00618 -0.1235 0.2366 0.3285
7.500 1.0837 0.01330 0.00660 -0.1214 0.2112 0.3317
7.750 1.1030 0.01375 0.00697 -0.1198 0.1918 0.3375
8.000 1.1222 0.01421 0.00737 -0.1181 0.1752 0.3423
8.250 1.1409 0.01468 0.00777 -0.1163 0.1598 0.3464
8.500 1.1589 0.01517 0.00818 -0.1144 0.1465 0.3493
8.750 1.1773 0.01563 0.00861 -0.1127 0.1349 0.3550
9.000 1.1955 0.01612 0.00906 -0.1110 0.1244 0.3601
9.250 1.2131 0.01663 0.00953 -0.1091 0.1146 0.3647
9.500 1.2293 0.01718 0.01004 -0.1071 0.1057 0.3683
9.750 1.2462 0.01771 0.01054 -0.1053 0.0979 0.3728
10.000 1.2641 0.01822 0.01106 -0.1036 0.0914 0.3791
10.250 1.2799 0.01881 0.01164 -0.1017 0.0854 0.3846
10.750 1.3116 0.02004 0.01285 -0.0979 0.0756 0.3937
11.000 1.3262 0.02072 0.01355 -0.0960 0.0714 0.4006
11.250 1.3417 0.02139 0.01424 -0.0943 0.0676 0.4065
11.500 1.3552 0.02217 0.01502 -0.0923 0.0642 0.4113
11.750 1.3692 0.02295 0.01582 -0.0906 0.0608 0.4165
12.000 1.3823 0.02382 0.01672 -0.0888 0.0577 0.4233
12.250 1.3948 0.02474 0.01767 -0.0870 0.0547 0.4292
12.500 1.4066 0.02575 0.01869 -0.0853 0.0521 0.4342
12.750 1.4178 0.02682 0.01979 -0.0836 0.0494 0.4400
13.000 1.4285 0.02799 0.02100 -0.0820 0.0470 0.4470
13.250 1.4391 0.02920 0.02225 -0.0805 0.0446 0.4531
13.500 1.4473 0.03063 0.02369 -0.0789 0.0425 0.4581
13.750 1.4573 0.03200 0.02511 -0.0776 0.0404 0.4647
14.000 1.4646 0.03364 0.02679 -0.0763 0.0383 0.4721
14.250 1.4735 0.03521 0.02842 -0.0752 0.0366 0.4787
14.500 1.4799 0.03705 0.03028 -0.0741 0.0348 0.4834
14.750 1.4867 0.03894 0.03223 -0.0732 0.0333 0.4914
15.000 1.4935 0.04089 0.03424 -0.0724 0.0318 0.4988
15.250 1.4972 0.04319 0.03659 -0.0716 0.0303 0.5051
15.500 1.5027 0.04542 0.03888 -0.0711 0.0292 0.5125
15.750 1.5080 0.04773 0.04126 -0.0706 0.0280 0.5208
16.000 1.5107 0.05038 0.04396 -0.0703 0.0269 0.5278
16.250 1.5125 0.05321 0.04686 -0.0702 0.0260 0.5346
16.500 1.5171 0.05582 0.04956 -0.0701 0.0251 0.5435
16.750 1.5196 0.05872 0.05252 -0.0701 0.0243 0.5516
17.000 1.5198 0.06199 0.05586 -0.0704 0.0235 0.5598
17.250 1.5180 0.06561 0.05956 -0.0709 0.0227 0.5685
17.500 1.5215 0.06860 0.06263 -0.0713 0.0222 0.5771
17.750 1.5224 0.07204 0.06617 -0.0719 0.0217 0.5868
18.000 1.5221 0.07567 0.06988 -0.0727 0.0211 0.5967
18.250 1.5217 0.07940 0.07369 -0.0736 0.0206 0.6069
18.500 1.5181 0.08367 0.07805 -0.0748 0.0200 0.6174
18.750 1.5121 0.08835 0.08284 -0.0762 0.0195 0.6269
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