NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S823 Airfoil (s823-nr) Reynolds number: 100,000 Max Cl/Cd: 43.25 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s823-nr-100000-n5.txt Download as CSV file: xf-s823-nr-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3572 0.08638 0.07883 -0.0502 0.9904 0.1557
-8.250 -0.5793 0.04836 0.03987 -0.0752 0.9675 0.1670
-8.000 -0.6117 0.04174 0.03284 -0.0806 0.9484 0.1691
-7.750 -0.5851 0.04073 0.03191 -0.0825 0.9413 0.1708
-7.500 -0.5686 0.03948 0.03068 -0.0837 0.9311 0.1724
-7.250 -0.5453 0.03786 0.02905 -0.0867 0.9244 0.1746
-7.000 -0.5329 0.03601 0.02711 -0.0885 0.9125 0.1768
-6.750 -0.5122 0.03411 0.02509 -0.0915 0.9045 0.1794
-6.500 -0.4923 0.03244 0.02324 -0.0935 0.8954 0.1822
-6.250 -0.4638 0.03118 0.02188 -0.0959 0.8891 0.1848
-6.000 -0.4380 0.03052 0.02128 -0.0967 0.8805 0.1869
-5.750 -0.4023 0.02969 0.02045 -0.0994 0.8758 0.1899
-5.500 -0.3809 0.02893 0.01965 -0.0998 0.8657 0.1928
-5.250 -0.3480 0.02792 0.01853 -0.1022 0.8600 0.1968
-5.000 -0.3240 0.02721 0.01776 -0.1028 0.8507 0.2000
-4.750 -0.2910 0.02668 0.01729 -0.1044 0.8443 0.2033
-4.500 -0.2631 0.02616 0.01676 -0.1053 0.8362 0.2070
-4.250 -0.2333 0.02551 0.01602 -0.1065 0.8285 0.2116
-4.000 -0.2029 0.02497 0.01546 -0.1078 0.8212 0.2160
-3.750 -0.1752 0.02465 0.01519 -0.1083 0.8127 0.2201
-3.500 -0.1417 0.02418 0.01466 -0.1099 0.8064 0.2258
-3.250 -0.1170 0.02379 0.01423 -0.1100 0.7969 0.2308
-3.000 -0.0818 0.02347 0.01397 -0.1116 0.7911 0.2357
-2.750 -0.0587 0.02323 0.01371 -0.1112 0.7813 0.2408
-2.500 -0.0251 0.02281 0.01323 -0.1126 0.7750 0.2466
-2.250 -0.0008 0.02269 0.01319 -0.1123 0.7660 0.2510
-2.000 0.0311 0.02241 0.01287 -0.1133 0.7592 0.2574
-1.750 0.0574 0.02220 0.01266 -0.1133 0.7508 0.2631
-1.500 0.0873 0.02206 0.01257 -0.1138 0.7435 0.2686
-1.250 0.1159 0.02187 0.01232 -0.1142 0.7362 0.2758
-1.000 0.1435 0.02177 0.01230 -0.1142 0.7283 0.2814
-0.750 0.1746 0.02164 0.01216 -0.1149 0.7219 0.2883
-0.500 0.2002 0.02152 0.01205 -0.1147 0.7134 0.2948
-0.250 0.2319 0.02143 0.01201 -0.1153 0.7074 0.3009
0.000 0.2569 0.02137 0.01194 -0.1150 0.6990 0.3081
0.250 0.2868 0.02129 0.01192 -0.1153 0.6923 0.3139
0.500 0.3138 0.02126 0.01194 -0.1152 0.6851 0.3204
0.750 0.3420 0.02119 0.01186 -0.1153 0.6778 0.3275
1.000 0.3722 0.02116 0.01189 -0.1155 0.6717 0.3337
1.250 0.3975 0.02116 0.01191 -0.1152 0.6637 0.3413
1.500 0.4279 0.02112 0.01194 -0.1155 0.6576 0.3474
1.750 0.4532 0.02118 0.01206 -0.1150 0.6500 0.3545
2.000 0.4818 0.02117 0.01209 -0.1151 0.6433 0.3616
2.250 0.5104 0.02120 0.01219 -0.1150 0.6369 0.3688
2.500 0.5362 0.02126 0.01228 -0.1147 0.6293 0.3766
2.750 0.5668 0.02127 0.01237 -0.1149 0.6235 0.3836
3.000 0.5912 0.02139 0.01252 -0.1143 0.6157 0.3921
3.250 0.6191 0.02145 0.01271 -0.1141 0.6091 0.3987
3.500 0.6466 0.02153 0.01282 -0.1139 0.6023 0.4074
3.750 0.6717 0.02166 0.01307 -0.1133 0.5949 0.4144
4.000 0.7032 0.02168 0.01309 -0.1137 0.5889 0.4237
4.250 0.7244 0.02187 0.01346 -0.1124 0.5803 0.4307
4.500 0.7546 0.02190 0.01349 -0.1125 0.5734 0.4400
4.750 0.7763 0.02209 0.01383 -0.1113 0.5644 0.4474
5.000 0.8057 0.02211 0.01387 -0.1112 0.5566 0.4570
5.250 0.8265 0.02230 0.01421 -0.1098 0.5469 0.4645
5.500 0.8554 0.02233 0.01424 -0.1096 0.5386 0.4746
5.750 0.8747 0.02253 0.01460 -0.1080 0.5281 0.4822
6.000 0.8995 0.02263 0.01476 -0.1071 0.5184 0.4922
6.250 0.9219 0.02275 0.01498 -0.1059 0.5079 0.5004
6.500 0.9425 0.02295 0.01526 -0.1044 0.4966 0.5106
6.750 0.9642 0.02308 0.01549 -0.1030 0.4856 0.5190
7.000 0.9854 0.02323 0.01570 -0.1016 0.4737 0.5291
7.250 1.0020 0.02348 0.01608 -0.0995 0.4607 0.5382
7.500 1.0195 0.02372 0.01640 -0.0976 0.4473 0.5478
7.750 1.0354 0.02397 0.01672 -0.0954 0.4332 0.5579
8.000 1.0483 0.02424 0.01707 -0.0927 0.4187 0.5672
8.500 1.0708 0.02507 0.01801 -0.0871 0.3856 0.5872
8.750 1.0809 0.02563 0.01860 -0.0844 0.3669 0.5978
9.000 1.0895 0.02630 0.01927 -0.0816 0.3472 0.6086
9.250 1.0963 0.02710 0.02005 -0.0787 0.3268 0.6189
9.500 1.1019 0.02806 0.02098 -0.0760 0.3057 0.6303
9.750 1.1057 0.02917 0.02207 -0.0732 0.2842 0.6414
10.000 1.1081 0.03046 0.02332 -0.0705 0.2638 0.6527
10.250 1.1092 0.03195 0.02475 -0.0680 0.2444 0.6648
10.500 1.1108 0.03354 0.02632 -0.0658 0.2262 0.6776
10.750 1.1115 0.03526 0.02806 -0.0637 0.2093 0.6904
11.000 1.1120 0.03711 0.02991 -0.0618 0.1938 0.7043
11.250 1.1121 0.03908 0.03189 -0.0601 0.1796 0.7192
11.500 1.1119 0.04115 0.03398 -0.0585 0.1666 0.7356
11.750 1.1128 0.04319 0.03608 -0.0571 0.1542 0.7543
12.000 1.1134 0.04530 0.03826 -0.0557 0.1434 0.7760
12.250 1.1114 0.04754 0.04056 -0.0543 0.1341 0.8015
12.500 1.1093 0.04961 0.04274 -0.0526 0.1251 0.8398
12.750 1.1016 0.05143 0.04470 -0.0503 0.1185 1.0000
13.000 1.1045 0.05418 0.04742 -0.0504 0.1099 1.0000
13.250 1.1082 0.05690 0.05013 -0.0506 0.1022 1.0000
13.500 1.1095 0.05992 0.05314 -0.0509 0.0955 1.0000
13.750 1.1131 0.06277 0.05601 -0.0511 0.0889 1.0000
14.000 1.1139 0.06597 0.05920 -0.0516 0.0832 1.0000
14.250 1.1165 0.06905 0.06229 -0.0520 0.0780 1.0000
14.500 1.1182 0.07231 0.06559 -0.0526 0.0730 1.0000
14.750 1.1175 0.07589 0.06913 -0.0534 0.0690 1.0000
15.000 1.1208 0.07908 0.07242 -0.0541 0.0645 1.0000
15.250 1.1207 0.08276 0.07613 -0.0551 0.0610 1.0000
15.500 1.1207 0.08645 0.07982 -0.0561 0.0579 1.0000
15.750 1.1229 0.08995 0.08342 -0.0570 0.0545 1.0000
16.000 1.1224 0.09387 0.08739 -0.0583 0.0518 1.0000
16.250 1.1213 0.09788 0.09137 -0.0597 0.0496 1.0000
16.500 1.1234 0.10154 0.09518 -0.0609 0.0469 1.0000
16.750 1.1236 0.10552 0.09924 -0.0624 0.0446 1.0000
17.000 1.1229 0.10965 0.10340 -0.0642 0.0429 1.0000
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