NASA SC(2)-1006 AIRFOIL (sc21006-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1006 AIRFOIL (sc21006-il) Reynolds number: 100,000 Max Cl/Cd: 48.87 at α=-0.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21006-il-100000-n5.txt Download as CSV file: xf-sc21006-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1006 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5094 0.09765 0.09252 -0.0246 0.9999 0.0343
-11.000 -0.5120 0.09414 0.08907 -0.0246 0.9999 0.0322
-10.750 -0.5184 0.09054 0.08555 -0.0247 0.9999 0.0306
-10.500 -0.5300 0.08667 0.08178 -0.0248 0.9999 0.0289
-10.250 -0.5338 0.07998 0.07516 -0.0310 0.9999 0.0260
-10.000 -0.5342 0.07563 0.07085 -0.0328 0.9999 0.0255
-9.750 -0.5301 0.06993 0.06516 -0.0382 0.9999 0.0251
-9.500 -0.5215 0.06324 0.05839 -0.0451 0.9999 0.0247
-9.250 -0.5076 0.05633 0.05130 -0.0521 0.9999 0.0243
-9.000 -0.4856 0.04910 0.04373 -0.0598 0.9999 0.0240
-8.750 -0.4533 0.04195 0.03596 -0.0679 0.9999 0.0247
-8.500 -0.4142 0.03626 0.02935 -0.0749 0.9999 0.0265
-8.250 -0.3772 0.03145 0.02389 -0.0799 0.9999 0.0269
-8.000 -0.3408 0.02785 0.01970 -0.0834 0.9999 0.0273
-7.750 -0.3062 0.02516 0.01657 -0.0858 0.9999 0.0280
-7.500 -0.2731 0.02315 0.01424 -0.0875 0.9999 0.0292
-7.250 -0.2408 0.02154 0.01239 -0.0888 0.9999 0.0310
-7.000 -0.2097 0.02043 0.01102 -0.0898 0.9999 0.0353
-6.750 -0.1766 0.01916 0.00963 -0.0914 0.9999 0.0401
-6.500 -0.1424 0.01816 0.00854 -0.0931 0.9999 0.0458
-6.250 -0.1081 0.01737 0.00769 -0.0949 0.9999 0.0593
-6.000 -0.0708 0.01646 0.00682 -0.0974 0.9999 0.0903
-5.750 -0.0296 0.01516 0.00627 -0.1015 0.9999 0.2529
-5.500 0.0061 0.01448 0.00627 -0.1039 0.9999 0.4414
-5.250 0.0350 0.01430 0.00634 -0.1041 0.9999 0.5361
-5.000 0.0618 0.01427 0.00639 -0.1038 0.9999 0.5906
-4.750 0.0875 0.01430 0.00643 -0.1032 0.9999 0.6333
-4.500 0.1124 0.01437 0.00653 -0.1024 0.9999 0.6732
-4.250 0.1364 0.01446 0.00665 -0.1014 0.9999 0.7079
-4.000 0.1605 0.01456 0.00675 -0.1005 0.9999 0.7359
-3.750 0.1849 0.01465 0.00684 -0.0997 0.9999 0.7597
-3.500 0.2095 0.01475 0.00692 -0.0990 0.9999 0.7814
-3.250 0.2335 0.01483 0.00702 -0.0981 0.9999 0.8004
-3.000 0.2578 0.01492 0.00713 -0.0974 0.9999 0.8194
-2.750 0.2821 0.01500 0.00725 -0.0968 0.9999 0.8384
-2.500 0.3053 0.01506 0.00738 -0.0958 0.9999 0.8568
-2.250 0.3286 0.01512 0.00751 -0.0950 0.9999 0.8770
-2.000 0.3503 0.01514 0.00761 -0.0938 0.9999 0.8994
-1.750 0.3702 0.01512 0.00771 -0.0923 0.9999 0.9281
-1.500 0.3840 0.01520 0.00790 -0.0899 0.9999 1.0001
-1.250 0.4141 0.01551 0.00832 -0.0910 0.9999 1.0001
-1.000 0.4435 0.01584 0.00876 -0.0918 0.9999 1.0001
-0.750 0.4813 0.01613 0.00919 -0.0944 0.9953 1.0001
-0.500 0.5386 0.01606 0.00937 -0.1004 0.9773 1.0001
-0.250 0.6583 0.01347 0.00531 -0.1114 0.4578 1.0001
0.000 0.6767 0.01625 0.00624 -0.1104 0.1051 1.0001
0.250 0.7023 0.01755 0.00720 -0.1101 0.0567 1.0001
0.500 0.7286 0.01856 0.00835 -0.1096 0.0469 1.0001
0.750 0.7538 0.01971 0.00953 -0.1091 0.0392 1.0001
1.000 0.7796 0.02079 0.01072 -0.1086 0.0343 1.0001
1.250 0.8052 0.02219 0.01215 -0.1081 0.0317 1.0001
1.500 0.8317 0.02411 0.01409 -0.1077 0.0299 1.0001
1.750 0.8604 0.02645 0.01657 -0.1075 0.0288 1.0001
2.000 0.8890 0.02804 0.01856 -0.1070 0.0268 1.0001
2.250 0.9165 0.02994 0.02081 -0.1065 0.0243 1.0001
2.500 0.9429 0.03258 0.02388 -0.1057 0.0236 1.0001
2.750 0.9673 0.03559 0.02737 -0.1044 0.0232 1.0001
3.000 0.9892 0.03899 0.03132 -0.1028 0.0230 1.0001
3.250 1.0083 0.04285 0.03573 -0.1009 0.0232 1.0001
3.500 1.0244 0.04711 0.04052 -0.0987 0.0235 1.0001
3.750 1.0375 0.05172 0.04563 -0.0964 0.0240 1.0001
4.000 1.0474 0.05661 0.05097 -0.0941 0.0246 1.0001
4.250 1.0549 0.06147 0.05622 -0.0920 0.0248 1.0001
4.500 1.0599 0.06625 0.06142 -0.0900 0.0242 1.0001
4.750 1.0623 0.07094 0.06640 -0.0883 0.0234 1.0001
5.000 1.0619 0.07563 0.07132 -0.0869 0.0227 1.0001
5.250 1.0572 0.08075 0.07666 -0.0857 0.0226 1.0001
5.500 1.0480 0.08621 0.08230 -0.0849 0.0231 1.0001
5.750 1.0342 0.09142 0.08763 -0.0844 0.0235 1.0001
6.000 1.0186 0.09681 0.09311 -0.0849 0.0240 1.0001
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Polar data table (+)
Polar graphs
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