NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S823 Airfoil (s823-nr) Reynolds number: 200,000 Max Cl/Cd: 60.05 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s823-nr-200000-n5.txt Download as CSV file: xf-s823-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S823 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5282 0.09980 0.09384 -0.0516 1.0000 0.1286
-12.250 -0.5393 0.09528 0.08931 -0.0526 1.0000 0.1298
-12.000 -0.7445 0.06390 0.05734 -0.0655 1.0000 0.1350
-11.750 -0.7696 0.05887 0.05219 -0.0666 1.0000 0.1357
-11.500 -0.7872 0.05515 0.04838 -0.0669 1.0000 0.1365
-11.250 -0.8027 0.05204 0.04519 -0.0665 1.0000 0.1371
-11.000 -0.8167 0.04942 0.04251 -0.0656 1.0000 0.1375
-10.750 -0.8100 0.04660 0.03960 -0.0684 0.9973 0.1383
-10.500 -0.7921 0.04404 0.03693 -0.0726 0.9931 0.1391
-10.250 -0.7757 0.04161 0.03439 -0.0761 0.9876 0.1399
-10.000 -0.7558 0.03948 0.03217 -0.0796 0.9823 0.1406
-9.750 -0.7396 0.03745 0.03004 -0.0823 0.9745 0.1413
-9.500 -0.7173 0.03594 0.02855 -0.0848 0.9683 0.1425
-9.250 -0.7024 0.03436 0.02698 -0.0862 0.9579 0.1435
-9.000 -0.6858 0.03275 0.02535 -0.0880 0.9484 0.1445
-8.750 -0.6658 0.03110 0.02368 -0.0905 0.9405 0.1457
-8.500 -0.6505 0.02956 0.02210 -0.0920 0.9299 0.1469
-8.250 -0.6247 0.02804 0.02052 -0.0951 0.9240 0.1484
-8.000 -0.6069 0.02668 0.01910 -0.0966 0.9126 0.1498
-7.750 -0.5739 0.02536 0.01770 -0.1005 0.9070 0.1515
-7.500 -0.5466 0.02424 0.01650 -0.1031 0.8971 0.1531
-7.250 -0.5098 0.02321 0.01536 -0.1070 0.8913 0.1549
-7.000 -0.4838 0.02228 0.01443 -0.1089 0.8806 0.1568
-6.750 -0.4509 0.02145 0.01359 -0.1117 0.8726 0.1591
-6.500 -0.4218 0.02079 0.01289 -0.1134 0.8626 0.1616
-6.250 -0.3918 0.02021 0.01226 -0.1150 0.8532 0.1644
-6.000 -0.3615 0.01972 0.01168 -0.1164 0.8437 0.1674
-5.750 -0.3350 0.01927 0.01118 -0.1170 0.8336 0.1701
-5.250 -0.2811 0.01840 0.01029 -0.1184 0.8141 0.1765
-5.000 -0.2530 0.01806 0.00989 -0.1191 0.8052 0.1800
-4.750 -0.2265 0.01778 0.00953 -0.1193 0.7955 0.1833
-4.500 -0.1998 0.01744 0.00920 -0.1196 0.7868 0.1866
-4.250 -0.1731 0.01715 0.00890 -0.1199 0.7778 0.1902
-4.000 -0.1460 0.01691 0.00863 -0.1201 0.7691 0.1942
-3.750 -0.1185 0.01671 0.00835 -0.1203 0.7603 0.1981
-3.500 -0.0916 0.01647 0.00813 -0.1205 0.7522 0.2018
-3.250 -0.0641 0.01626 0.00792 -0.1207 0.7439 0.2060
-3.000 -0.0366 0.01609 0.00772 -0.1208 0.7357 0.2106
-2.750 -0.0090 0.01594 0.00752 -0.1209 0.7274 0.2148
-2.500 0.0188 0.01576 0.00737 -0.1212 0.7199 0.2191
-2.250 0.0464 0.01562 0.00723 -0.1212 0.7119 0.2239
-2.000 0.0748 0.01551 0.00707 -0.1214 0.7045 0.2289
-1.750 0.1021 0.01537 0.00697 -0.1215 0.6963 0.2338
-1.500 0.1309 0.01528 0.00686 -0.1217 0.6895 0.2395
-1.250 0.1583 0.01520 0.00677 -0.1217 0.6816 0.2451
-1.000 0.1868 0.01510 0.00670 -0.1218 0.6745 0.2505
-0.750 0.2146 0.01503 0.00665 -0.1219 0.6670 0.2563
-0.500 0.2430 0.01497 0.00657 -0.1219 0.6598 0.2621
-0.250 0.2712 0.01491 0.00656 -0.1220 0.6529 0.2678
0.000 0.2993 0.01488 0.00653 -0.1220 0.6455 0.2747
0.250 0.3281 0.01485 0.00651 -0.1221 0.6392 0.2812
0.500 0.3557 0.01482 0.00654 -0.1221 0.6317 0.2881
0.750 0.3842 0.01481 0.00652 -0.1221 0.6250 0.2948
1.000 0.4123 0.01480 0.00657 -0.1221 0.6183 0.3011
1.250 0.4404 0.01480 0.00658 -0.1220 0.6113 0.3078
1.500 0.4689 0.01481 0.00661 -0.1220 0.6052 0.3136
1.750 0.4965 0.01481 0.00669 -0.1219 0.5980 0.3199
2.000 0.5248 0.01485 0.00671 -0.1218 0.5915 0.3268
2.250 0.5527 0.01487 0.00681 -0.1217 0.5851 0.3332
2.500 0.5804 0.01492 0.00689 -0.1215 0.5782 0.3402
2.750 0.6089 0.01497 0.00695 -0.1215 0.5723 0.3464
3.000 0.6359 0.01501 0.00709 -0.1212 0.5652 0.3534
3.250 0.6636 0.01508 0.00718 -0.1210 0.5585 0.3607
3.500 0.6910 0.01515 0.00732 -0.1207 0.5516 0.3677
3.750 0.7178 0.01523 0.00742 -0.1203 0.5438 0.3754
4.000 0.7446 0.01531 0.00757 -0.1199 0.5360 0.3823
4.250 0.7706 0.01539 0.00769 -0.1193 0.5271 0.3903
4.500 0.7968 0.01549 0.00784 -0.1188 0.5187 0.3973
4.750 0.8223 0.01559 0.00800 -0.1182 0.5095 0.4052
5.000 0.8476 0.01570 0.00817 -0.1175 0.5004 0.4128
5.250 0.8724 0.01583 0.00832 -0.1167 0.4906 0.4208
5.500 0.8967 0.01596 0.00852 -0.1158 0.4802 0.4285
5.750 0.9206 0.01611 0.00872 -0.1149 0.4700 0.4366
6.000 0.9438 0.01627 0.00892 -0.1138 0.4586 0.4447
6.250 0.9663 0.01644 0.00916 -0.1126 0.4466 0.4527
6.500 0.9880 0.01664 0.00938 -0.1113 0.4339 0.4610
6.750 1.0083 0.01686 0.00964 -0.1097 0.4197 0.4692
7.000 1.0274 0.01712 0.00991 -0.1080 0.4040 0.4777
7.250 1.0442 0.01739 0.01021 -0.1059 0.3871 0.4856
7.500 1.0587 0.01772 0.01052 -0.1034 0.3685 0.4942
7.750 1.0717 0.01813 0.01092 -0.1007 0.3484 0.5020
8.000 1.0828 0.01868 0.01140 -0.0979 0.3265 0.5108
8.250 1.0937 0.01929 0.01199 -0.0951 0.3040 0.5188
8.500 1.1026 0.02003 0.01265 -0.0922 0.2804 0.5277
8.750 1.1098 0.02086 0.01343 -0.0892 0.2572 0.5358
9.000 1.1167 0.02179 0.01427 -0.0864 0.2349 0.5447
9.250 1.1224 0.02281 0.01526 -0.0835 0.2146 0.5531
9.500 1.1283 0.02391 0.01630 -0.0809 0.1962 0.5625
9.750 1.1348 0.02505 0.01742 -0.0785 0.1794 0.5717
10.000 1.1411 0.02627 0.01862 -0.0763 0.1641 0.5813
10.250 1.1470 0.02758 0.01993 -0.0742 0.1502 0.5915
10.500 1.1534 0.02893 0.02129 -0.0723 0.1373 0.6016
10.750 1.1602 0.03032 0.02271 -0.0706 0.1257 0.6128
11.000 1.1663 0.03183 0.02424 -0.0689 0.1152 0.6238
11.250 1.1713 0.03347 0.02590 -0.0674 0.1057 0.6352
11.500 1.1772 0.03513 0.02759 -0.0660 0.0966 0.6476
11.750 1.1833 0.03684 0.02935 -0.0648 0.0887 0.6607
12.000 1.1873 0.03879 0.03133 -0.0637 0.0816 0.6740
12.250 1.1942 0.04056 0.03319 -0.0627 0.0750 0.6888
12.500 1.1977 0.04267 0.03535 -0.0618 0.0694 0.7041
12.750 1.2040 0.04459 0.03737 -0.0610 0.0640 0.7217
13.000 1.2069 0.04685 0.03969 -0.0602 0.0596 0.7407
13.250 1.2121 0.04891 0.04187 -0.0594 0.0556 0.7634
13.500 1.2147 0.05120 0.04426 -0.0587 0.0518 0.7907
13.750 1.2156 0.05349 0.04668 -0.0577 0.0487 0.8302
14.000 1.2121 0.05530 0.04870 -0.0557 0.0460 1.0000
14.250 1.2155 0.05807 0.05148 -0.0558 0.0431 1.0000
14.500 1.2187 0.06091 0.05436 -0.0560 0.0406 1.0000
14.750 1.2229 0.06371 0.05721 -0.0562 0.0380 1.0000
15.000 1.2248 0.06684 0.06037 -0.0567 0.0359 1.0000
15.250 1.2266 0.07005 0.06363 -0.0572 0.0340 1.0000
15.500 1.2298 0.07315 0.06680 -0.0577 0.0319 1.0000
15.750 1.2310 0.07657 0.07027 -0.0584 0.0303 1.0000
16.000 1.2297 0.08039 0.07412 -0.0593 0.0289 1.0000
16.250 1.2319 0.08382 0.07765 -0.0602 0.0275 1.0000
16.500 1.2327 0.08748 0.08138 -0.0612 0.0262 1.0000
16.750 1.2321 0.09141 0.08538 -0.0624 0.0251 1.0000
17.000 1.2293 0.09574 0.08976 -0.0639 0.0242 1.0000
17.250 1.2288 0.09978 0.09389 -0.0653 0.0232 1.0000
17.500 1.2285 0.10385 0.09806 -0.0668 0.0222 1.0000
17.750 1.2271 0.10812 0.10241 -0.0685 0.0214 1.0000
18.000 1.2247 0.11261 0.10698 -0.0704 0.0207 1.0000
18.250 1.2209 0.11738 0.11182 -0.0726 0.0201 1.0000
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