SIKORSKY SC2110 AIRFOIL (sc2110-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC2110 AIRFOIL (sc2110-il) Reynolds number: 100,000 Max Cl/Cd: 34.71 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc2110-il-100000.txt Download as CSV file: xf-sc2110-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC2110 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5123 0.10427 0.09969 -0.0055 1.0000 0.0854
-8.750 -0.5278 0.09930 0.09478 -0.0168 1.0000 0.0866
-8.500 -0.5460 0.09551 0.09088 -0.0244 1.0000 0.0870
-8.250 -0.5043 0.09078 0.08633 -0.0138 1.0000 0.0908
-8.000 -0.4981 0.08705 0.08262 -0.0155 1.0000 0.0940
-7.750 -0.3985 0.07275 0.06859 -0.0247 1.0000 0.1076
-7.500 -0.4071 0.06850 0.06437 -0.0271 1.0000 0.1102
-7.250 -0.4252 0.06488 0.06077 -0.0280 1.0000 0.1122
-7.000 -0.4478 0.06205 0.05792 -0.0269 1.0000 0.1143
-6.750 -0.4805 0.06039 0.05607 -0.0249 1.0000 0.1164
-6.500 -0.4958 0.05671 0.05229 -0.0230 1.0000 0.1182
-6.250 -0.5147 0.06238 0.05755 -0.0239 1.0000 0.1200
-6.000 -0.5083 0.05982 0.05505 -0.0217 1.0000 0.1246
-5.750 -0.5128 0.05782 0.05269 -0.0205 1.0000 0.1346
-5.500 -0.5028 0.05460 0.04964 -0.0184 1.0000 0.1393
-5.250 -0.4986 0.05224 0.04705 -0.0172 1.0000 0.1517
-4.750 -0.4788 0.04731 0.04207 -0.0141 1.0000 0.1756
-4.500 -0.4703 0.04500 0.03960 -0.0130 1.0000 0.2001
-4.250 -0.4585 0.04245 0.03717 -0.0112 1.0000 0.2210
-3.750 -0.4369 0.03814 0.03291 -0.0077 1.0000 0.2962
-3.500 -0.4221 0.03579 0.03063 -0.0060 1.0000 0.3283
-3.250 -0.3403 0.03104 0.02318 -0.0094 1.0000 0.0995
-3.000 -0.3110 0.02809 0.01979 -0.0085 1.0000 0.0812
-2.750 -0.2823 0.02674 0.01785 -0.0072 1.0000 0.0724
-2.500 -0.2549 0.02489 0.01585 -0.0069 1.0000 0.0709
-2.250 -0.2287 0.02392 0.01465 -0.0063 1.0000 0.0723
-2.000 -0.2026 0.02300 0.01359 -0.0057 1.0000 0.0733
-1.750 -0.1756 0.02158 0.01219 -0.0054 1.0000 0.0744
-1.500 -0.1498 0.02057 0.01131 -0.0051 1.0000 0.0778
-1.250 -0.1249 0.02003 0.01080 -0.0048 1.0000 0.0851
-1.000 -0.0989 0.01931 0.01018 -0.0047 1.0000 0.0927
-0.750 -0.0407 0.01852 0.00955 -0.0106 0.9904 0.1358
-0.500 0.0187 0.01637 0.01023 -0.0111 0.9847 1.0000
-0.250 0.0838 0.01669 0.01026 -0.0185 0.9712 1.0000
0.000 0.1449 0.01690 0.01029 -0.0251 0.9587 1.0000
0.250 0.2114 0.01697 0.01024 -0.0323 0.9459 1.0000
0.500 0.2745 0.01688 0.01007 -0.0386 0.9316 1.0000
0.750 0.3207 0.01669 0.00986 -0.0414 0.9148 1.0000
1.000 0.3552 0.01641 0.00956 -0.0415 0.8964 1.0000
1.250 0.3809 0.01604 0.00918 -0.0397 0.8777 1.0000
1.500 0.3972 0.01566 0.00880 -0.0364 0.8547 1.0000
1.750 0.4143 0.01509 0.00821 -0.0326 0.8319 1.0000
2.000 0.4295 0.01451 0.00762 -0.0285 0.8025 1.0000
2.250 0.4447 0.01389 0.00697 -0.0244 0.7601 1.0000
2.500 0.4592 0.01327 0.00613 -0.0197 0.6748 1.0000
2.750 0.4714 0.01358 0.00541 -0.0149 0.5107 1.0000
3.000 0.4898 0.01454 0.00564 -0.0131 0.4299 1.0000
3.250 0.5110 0.01535 0.00599 -0.0120 0.3911 1.0000
3.500 0.5341 0.01603 0.00642 -0.0113 0.3630 1.0000
3.750 0.5578 0.01673 0.00687 -0.0107 0.3414 1.0000
4.000 0.5825 0.01738 0.00737 -0.0103 0.3231 1.0000
4.250 0.6076 0.01805 0.00792 -0.0099 0.3076 1.0000
4.500 0.6329 0.01874 0.00846 -0.0096 0.2937 1.0000
4.750 0.6585 0.01939 0.00903 -0.0094 0.2809 1.0000
5.000 0.6845 0.02007 0.00973 -0.0092 0.2694 1.0000
5.250 0.7105 0.02084 0.01045 -0.0091 0.2594 1.0000
5.500 0.7365 0.02154 0.01108 -0.0090 0.2496 1.0000
5.750 0.7625 0.02233 0.01196 -0.0088 0.2403 1.0000
6.000 0.7887 0.02319 0.01272 -0.0088 0.2330 1.0000
6.250 0.8144 0.02406 0.01377 -0.0086 0.2249 1.0000
6.500 0.8404 0.02489 0.01452 -0.0086 0.2178 1.0000
6.750 0.8655 0.02591 0.01574 -0.0084 0.2107 1.0000
7.000 0.8911 0.02685 0.01676 -0.0083 0.2047 1.0000
7.250 0.9162 0.02808 0.01804 -0.0082 0.1992 1.0000
7.500 0.9402 0.02915 0.01937 -0.0080 0.1927 1.0000
7.750 0.9654 0.03015 0.02035 -0.0079 0.1875 1.0000
8.000 0.9879 0.03184 0.02233 -0.0076 0.1831 1.0000
8.250 1.0098 0.03337 0.02417 -0.0073 0.1780 1.0000
8.500 1.0341 0.03444 0.02526 -0.0071 0.1734 1.0000
8.750 1.0545 0.03635 0.02737 -0.0068 0.1692 1.0000
9.000 1.0704 0.03868 0.03020 -0.0060 0.1650 1.0000
9.250 1.0889 0.04065 0.03240 -0.0055 0.1614 1.0000
9.500 1.1128 0.04186 0.03359 -0.0054 0.1579 1.0000
9.750 1.1242 0.04483 0.03692 -0.0046 0.1546 1.0000
10.000 1.1249 0.04872 0.04140 -0.0032 0.1514 1.0000
10.250 1.1240 0.05284 0.04595 -0.0020 0.1492 1.0000
10.500 1.1203 0.05703 0.05047 -0.0009 0.1474 1.0000
10.750 1.1308 0.05929 0.05285 -0.0002 0.1449 1.0000
11.000 1.1628 0.06012 0.05351 -0.0003 0.1415 1.0000
11.250 1.1320 0.06635 0.06020 0.0013 0.1409 1.0000
11.500 1.0954 0.07275 0.06684 0.0023 0.1410 1.0000
11.750 1.0583 0.08000 0.07424 0.0015 0.1415 1.0000
12.000 0.8372 0.13724 0.13147 -0.0362 0.2014 1.0000
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Polar data table (+)
Polar graphs
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