NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S823 Airfoil (s823-nr) Reynolds number: 100,000 Max Cl/Cd: 42.33 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s823-nr-100000.txt Download as CSV file: xf-s823-nr-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1850 0.13559 0.12910 -0.0172 1.0000 0.2382
-8.000 -0.1957 0.13541 0.12900 -0.0145 1.0000 0.2409
-7.750 -0.2786 0.13836 0.13203 -0.0130 1.0000 0.2455
-7.500 -0.2390 0.13380 0.12750 -0.0145 0.9974 0.2462
-7.250 -0.1925 0.12958 0.12329 -0.0182 0.9933 0.2476
-7.000 -0.1561 0.12634 0.12006 -0.0218 0.9879 0.2501
-6.750 -0.1266 0.12340 0.11713 -0.0262 0.9828 0.2543
-6.500 -0.1595 0.12144 0.11513 -0.0329 0.9739 0.2617
-6.250 -0.1123 0.11694 0.11065 -0.0362 0.9698 0.2626
-6.000 -0.0735 0.11346 0.10719 -0.0392 0.9643 0.2643
-5.750 -0.0420 0.11046 0.10421 -0.0425 0.9578 0.2668
-4.750 -0.0443 0.08954 0.08310 -0.0629 0.9270 0.2447
-4.500 -0.0015 0.08639 0.07995 -0.0668 0.9242 0.2429
-4.250 0.0063 0.08300 0.07657 -0.0683 0.9134 0.2415
-4.000 0.0200 0.07754 0.07107 -0.0740 0.9089 0.2401
-3.750 0.1027 0.08130 0.07500 -0.0753 0.9076 0.2676
-3.500 0.1172 0.08034 0.07410 -0.0756 0.8965 0.2813
-3.250 -0.2592 0.03696 0.02879 -0.0912 0.8491 0.2551
-3.000 -0.2185 0.03504 0.02660 -0.0957 0.8445 0.2629
-2.750 -0.1680 0.03495 0.02674 -0.0986 0.8421 0.2684
-2.500 -0.1585 0.03464 0.02631 -0.0970 0.8299 0.2742
-2.250 -0.1108 0.03395 0.02569 -0.1004 0.8270 0.2815
-2.000 -0.0954 0.03418 0.02600 -0.0987 0.8167 0.2864
-1.750 -0.0513 0.03310 0.02479 -0.1023 0.8122 0.2955
-1.500 -0.0011 0.03286 0.02473 -0.1053 0.8095 0.3024
-1.250 0.0110 0.03243 0.02406 -0.1045 0.7983 0.3101
-1.000 0.0543 0.03237 0.02427 -0.1060 0.7945 0.3159
-0.750 0.1052 0.03139 0.02317 -0.1103 0.7917 0.3271
-0.500 0.1102 0.03208 0.02403 -0.1066 0.7797 0.3306
-0.250 0.1588 0.03130 0.02313 -0.1103 0.7763 0.3421
0.000 0.1684 0.03188 0.02390 -0.1073 0.7658 0.3462
0.250 0.2091 0.03155 0.02363 -0.1091 0.7611 0.3551
0.500 0.2558 0.03094 0.02308 -0.1117 0.7580 0.3638
0.750 0.2603 0.03162 0.02383 -0.1084 0.7463 0.3693
1.000 0.3058 0.03095 0.02317 -0.1111 0.7425 0.3792
1.250 0.3145 0.03161 0.02393 -0.1083 0.7322 0.3847
1.500 0.3561 0.03100 0.02329 -0.1105 0.7274 0.3947
1.750 0.4015 0.03056 0.02294 -0.1125 0.7240 0.4040
2.000 0.4057 0.03121 0.02360 -0.1098 0.7125 0.4108
2.250 0.4481 0.03084 0.02335 -0.1111 0.7085 0.4195
2.500 0.4575 0.03141 0.02392 -0.1092 0.6982 0.4271
2.750 0.4953 0.03115 0.02380 -0.1099 0.6933 0.4353
3.000 0.5417 0.03055 0.02322 -0.1123 0.6895 0.4464
3.250 0.5428 0.03154 0.02434 -0.1086 0.6781 0.4522
3.500 0.5910 0.03083 0.02366 -0.1110 0.6742 0.4636
3.750 0.5928 0.03186 0.02482 -0.1075 0.6632 0.4699
4.000 0.6389 0.03118 0.02419 -0.1095 0.6585 0.4814
4.250 0.6488 0.03192 0.02502 -0.1071 0.6484 0.4895
4.500 0.6911 0.03131 0.02450 -0.1083 0.6426 0.5001
4.750 0.7124 0.03162 0.02483 -0.1075 0.6334 0.5110
5.000 0.7479 0.03120 0.02455 -0.1075 0.6263 0.5205
5.250 0.7724 0.03129 0.02471 -0.1068 0.6173 0.5308
5.500 0.8118 0.03075 0.02420 -0.1078 0.6093 0.5440
5.750 0.8304 0.03094 0.02456 -0.1057 0.5996 0.5520
6.000 0.8739 0.03015 0.02379 -0.1070 0.5914 0.5651
6.250 0.8919 0.03037 0.02412 -0.1052 0.5802 0.5760
6.500 0.9426 0.02927 0.02301 -0.1070 0.5723 0.5894
6.750 0.9555 0.02951 0.02340 -0.1044 0.5598 0.5994
7.000 0.9809 0.02937 0.02332 -0.1035 0.5481 0.6125
7.250 1.0186 0.02866 0.02263 -0.1036 0.5374 0.6254
7.500 1.0412 0.02840 0.02247 -0.1018 0.5245 0.6369
7.750 1.0604 0.02829 0.02246 -0.0998 0.5107 0.6494
8.000 1.0831 0.02805 0.02227 -0.0983 0.4965 0.6632
8.250 1.1036 0.02779 0.02209 -0.0962 0.4818 0.6761
8.500 1.1219 0.02755 0.02191 -0.0937 0.4662 0.6890
8.750 1.1373 0.02740 0.02182 -0.0910 0.4496 0.7024
9.000 1.1494 0.02733 0.02180 -0.0879 0.4318 0.7166
9.250 1.1574 0.02734 0.02185 -0.0842 0.4133 0.7312
9.500 1.1620 0.02745 0.02198 -0.0801 0.3941 0.7462
9.750 1.1676 0.02769 0.02216 -0.0763 0.3736 0.7622
10.000 1.1652 0.02834 0.02286 -0.0718 0.3518 0.7783
10.250 1.1635 0.02906 0.02356 -0.0676 0.3295 0.7958
10.500 1.1609 0.02993 0.02433 -0.0634 0.3078 0.8148
10.750 1.1547 0.03106 0.02547 -0.0593 0.2860 0.8370
11.000 1.1478 0.03223 0.02660 -0.0552 0.2663 0.8651
11.250 1.1377 0.03324 0.02762 -0.0505 0.2492 0.9131
11.500 1.1404 0.03491 0.02907 -0.0496 0.2287 1.0000
11.750 1.1463 0.03730 0.03132 -0.0499 0.2075 1.0000
12.000 1.1513 0.03964 0.03350 -0.0497 0.1892 1.0000
12.250 1.1556 0.04198 0.03568 -0.0492 0.1733 1.0000
12.500 1.1600 0.04432 0.03789 -0.0486 0.1592 1.0000
12.750 1.1650 0.04664 0.04006 -0.0480 0.1466 1.0000
13.000 1.1717 0.04886 0.04210 -0.0475 0.1352 1.0000
13.250 1.1737 0.05142 0.04470 -0.0470 0.1252 1.0000
13.500 1.1793 0.05386 0.04711 -0.0465 0.1158 1.0000
13.750 1.1899 0.05593 0.04894 -0.0460 0.1069 1.0000
14.000 1.1897 0.05884 0.05203 -0.0457 0.1000 1.0000
14.250 1.2018 0.06091 0.05390 -0.0453 0.0929 1.0000
14.500 1.2017 0.06397 0.05715 -0.0452 0.0873 1.0000
14.750 1.2187 0.06573 0.05864 -0.0447 0.0810 1.0000
15.000 1.2156 0.06921 0.06241 -0.0448 0.0771 1.0000
15.250 1.2204 0.07193 0.06515 -0.0448 0.0729 1.0000
15.500 1.2344 0.07419 0.06731 -0.0444 0.0686 1.0000
15.750 1.2303 0.07803 0.07141 -0.0449 0.0659 1.0000
16.000 1.2310 0.08142 0.07493 -0.0453 0.0631 1.0000
16.250 1.2509 0.08296 0.07623 -0.0448 0.0596 1.0000
16.500 1.2439 0.08748 0.08101 -0.0457 0.0580 1.0000
16.750 1.2314 0.09257 0.08640 -0.0472 0.0566 1.0000
17.000 1.2208 0.09765 0.09172 -0.0489 0.0552 1.0000
17.250 1.2120 0.10265 0.09692 -0.0507 0.0540 1.0000
17.500 1.2012 0.10808 0.10255 -0.0530 0.0530 1.0000
17.750 1.1905 0.11358 0.10821 -0.0555 0.0521 1.0000
18.000 1.1833 0.11867 0.11341 -0.0579 0.0513 1.0000
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