NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il) Reynolds number: 100,000 Max Cl/Cd: 49.6 at α=0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21010-il-100000-n5.txt Download as CSV file: xf-sc21010-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1010 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5278 0.09516 0.08945 -0.0446 0.9999 0.0396
-12.750 -0.5402 0.08896 0.08332 -0.0469 0.9999 0.0394
-12.500 -0.5599 0.08116 0.07558 -0.0502 0.9999 0.0391
-12.250 -0.5973 0.07080 0.06527 -0.0554 0.9999 0.0384
-12.000 -0.6387 0.06441 0.05888 -0.0571 0.9999 0.0379
-11.750 -0.6698 0.05786 0.05221 -0.0614 0.9999 0.0375
-11.500 -0.6841 0.05184 0.04585 -0.0654 0.9999 0.0376
-11.250 -0.6835 0.04641 0.03997 -0.0688 0.9999 0.0379
-11.000 -0.6717 0.04162 0.03463 -0.0719 0.9999 0.0385
-10.750 -0.6524 0.03754 0.02996 -0.0747 0.9999 0.0394
-10.500 -0.6281 0.03420 0.02594 -0.0772 0.9999 0.0408
-10.250 -0.6059 0.03266 0.02440 -0.0778 0.9999 0.0423
-10.000 -0.5819 0.03130 0.02289 -0.0786 0.9999 0.0441
-9.750 -0.5561 0.02962 0.02093 -0.0796 0.9999 0.0460
-9.500 -0.5292 0.02795 0.01894 -0.0805 0.9999 0.0478
-9.250 -0.5026 0.02658 0.01741 -0.0812 0.9999 0.0500
-9.000 -0.4767 0.02573 0.01654 -0.0818 0.9999 0.0528
-8.750 -0.4494 0.02481 0.01548 -0.0824 0.9999 0.0561
-8.500 -0.4212 0.02387 0.01438 -0.0831 0.9999 0.0592
-8.250 -0.3930 0.02310 0.01367 -0.0841 0.9999 0.0634
-8.000 -0.3644 0.02245 0.01293 -0.0848 0.9999 0.0683
-7.750 -0.3335 0.02172 0.01221 -0.0862 0.9996 0.0736
-7.500 -0.2983 0.02118 0.01161 -0.0884 0.9979 0.0820
-7.250 -0.2620 0.02055 0.01102 -0.0908 0.9965 0.0920
-7.000 -0.2252 0.02001 0.01051 -0.0934 0.9951 0.1076
-6.750 -0.1876 0.01947 0.01005 -0.0962 0.9941 0.1310
-6.500 -0.1506 0.01889 0.00966 -0.0990 0.9929 0.1710
-6.250 -0.1124 0.01823 0.00940 -0.1023 0.9919 0.2506
-6.000 -0.0750 0.01771 0.00941 -0.1052 0.9907 0.3672
-5.750 -0.0404 0.01761 0.00955 -0.1069 0.9885 0.4462
-5.500 -0.0066 0.01767 0.00970 -0.1083 0.9863 0.4958
-5.250 0.0269 0.01780 0.00989 -0.1096 0.9843 0.5344
-5.000 0.0580 0.01794 0.01005 -0.1103 0.9816 0.5630
-4.750 0.0883 0.01809 0.01020 -0.1108 0.9781 0.5889
-4.500 0.1181 0.01830 0.01048 -0.1111 0.9750 0.6134
-4.250 0.1499 0.01853 0.01073 -0.1118 0.9725 0.6360
-4.000 0.1809 0.01873 0.01094 -0.1124 0.9696 0.6538
-3.750 0.2076 0.01892 0.01115 -0.1122 0.9653 0.6669
-3.500 0.2377 0.01910 0.01135 -0.1128 0.9621 0.6795
-3.250 0.2709 0.01926 0.01152 -0.1140 0.9594 0.6922
-3.000 0.3045 0.01940 0.01168 -0.1152 0.9563 0.7046
-2.750 0.3294 0.01957 0.01190 -0.1146 0.9504 0.7142
-2.500 0.3611 0.01972 0.01210 -0.1155 0.9468 0.7250
-2.250 0.3947 0.01985 0.01229 -0.1166 0.9438 0.7352
-2.000 0.4214 0.02001 0.01252 -0.1164 0.9379 0.7446
-1.750 0.4543 0.02010 0.01267 -0.1175 0.9325 0.7556
-1.500 0.4894 0.02009 0.01277 -0.1186 0.9285 0.7641
-1.250 0.5161 0.02020 0.01297 -0.1184 0.9203 0.7736
-1.000 0.5537 0.02003 0.01291 -0.1199 0.9143 0.7822
-0.750 0.5912 0.01954 0.01256 -0.1209 0.9013 0.7907
-0.500 0.6400 0.01819 0.01130 -0.1226 0.8794 0.7997
-0.250 0.6756 0.01725 0.01047 -0.1222 0.8548 0.8079
0.000 0.7078 0.01663 0.00993 -0.1216 0.8247 0.8170
0.250 0.7358 0.01610 0.00944 -0.1200 0.7799 0.8246
0.500 0.7733 0.01559 0.00864 -0.1199 0.6607 0.8336
0.750 0.7898 0.01696 0.00852 -0.1164 0.4064 0.8414
1.000 0.8033 0.01855 0.00919 -0.1140 0.2453 0.8500
1.250 0.8210 0.01972 0.00980 -0.1123 0.1542 0.8585
1.500 0.8414 0.02056 0.01041 -0.1109 0.1165 0.8670
1.750 0.8630 0.02135 0.01110 -0.1098 0.0965 0.8765
2.000 0.8829 0.02198 0.01174 -0.1081 0.0853 0.8859
2.250 0.9028 0.02271 0.01246 -0.1066 0.0772 0.8959
2.500 0.9236 0.02339 0.01319 -0.1052 0.0704 0.9062
2.750 0.9425 0.02420 0.01403 -0.1034 0.0660 0.9168
3.000 0.9623 0.02486 0.01478 -0.1018 0.0614 0.9291
3.250 0.9815 0.02562 0.01553 -0.1002 0.0575 0.9461
3.500 1.0037 0.02660 0.01661 -0.0992 0.0547 1.0001
3.750 1.0315 0.02778 0.01788 -0.0993 0.0513 1.0001
4.000 1.0581 0.02895 0.01901 -0.0995 0.0482 1.0001
4.250 1.0859 0.03053 0.02063 -0.0998 0.0460 1.0001
4.500 1.1146 0.03217 0.02249 -0.0999 0.0441 1.0001
4.750 1.1415 0.03375 0.02423 -0.0999 0.0419 1.0001
5.000 1.1664 0.03516 0.02571 -0.0998 0.0400 1.0001
5.250 1.1909 0.03706 0.02767 -0.0997 0.0384 1.0001
5.500 1.2143 0.03940 0.03044 -0.0989 0.0373 1.0001
5.750 1.2349 0.04202 0.03348 -0.0979 0.0363 1.0001
6.000 1.2522 0.04482 0.03668 -0.0965 0.0354 1.0001
6.250 1.2667 0.04752 0.03973 -0.0948 0.0345 1.0001
6.500 1.2801 0.04986 0.04233 -0.0931 0.0336 1.0001
6.750 1.2931 0.05187 0.04448 -0.0916 0.0327 1.0001
7.000 1.3043 0.05422 0.04693 -0.0901 0.0320 1.0001
7.250 1.3002 0.05810 0.05135 -0.0864 0.0315 1.0001
7.500 1.2909 0.06225 0.05599 -0.0825 0.0312 1.0001
7.750 1.2764 0.06627 0.06039 -0.0783 0.0311 1.0001
8.000 1.2565 0.07014 0.06458 -0.0740 0.0310 1.0001
8.250 1.2339 0.07455 0.06928 -0.0707 0.0310 1.0001
8.500 1.2100 0.07942 0.07442 -0.0687 0.0310 1.0001
8.750 1.1839 0.08508 0.08032 -0.0681 0.0311 1.0001
9.000 1.1567 0.09164 0.08711 -0.0695 0.0312 1.0001
9.250 1.1288 0.09951 0.09516 -0.0731 0.0314 1.0001
9.500 1.1018 0.10904 0.10485 -0.0793 0.0316 1.0001
9.750 1.0776 0.12057 0.11648 -0.0878 0.0318 1.0001
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Polar data table (+)
Polar graphs
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