SIKORSKY SC2110 AIRFOIL (sc2110-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SIKORSKY SC2110 AIRFOIL (sc2110-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.11 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc2110-il-1000000-n5.txt Download as CSV file: xf-sc2110-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6341 0.08655 0.08488 0.0113 0.8968 0.0063
-8.750 -0.6478 0.07829 0.07659 0.0019 0.8916 0.0063
-8.500 -0.6601 0.07156 0.06978 -0.0034 0.8864 0.0063
-8.250 -0.6625 0.06588 0.06398 -0.0064 0.8823 0.0064
-8.000 -0.6603 0.06074 0.05870 -0.0082 0.8787 0.0064
-7.750 -0.6533 0.05606 0.05388 -0.0094 0.8754 0.0065
-7.500 -0.6433 0.05155 0.04921 -0.0102 0.8720 0.0065
-7.250 -0.6313 0.04703 0.04451 -0.0105 0.8687 0.0066
-7.000 -0.6186 0.04201 0.03924 -0.0105 0.8655 0.0067
-6.750 -0.6353 0.01905 0.01441 -0.0063 0.8619 0.0069
-6.500 -0.6113 0.01667 0.01168 -0.0059 0.8593 0.0070
-6.250 -0.5851 0.01541 0.01023 -0.0057 0.8566 0.0071
-6.000 -0.5584 0.01445 0.00913 -0.0055 0.8538 0.0072
-5.750 -0.5314 0.01366 0.00821 -0.0054 0.8510 0.0074
-5.500 -0.5042 0.01298 0.00742 -0.0052 0.8483 0.0075
-5.000 -0.4489 0.01186 0.00614 -0.0051 0.8431 0.0080
-4.750 -0.4207 0.01140 0.00562 -0.0052 0.8401 0.0082
-4.500 -0.3924 0.01102 0.00519 -0.0052 0.8367 0.0083
-4.250 -0.3648 0.01055 0.00466 -0.0051 0.8312 0.0086
-4.000 -0.3363 0.01020 0.00428 -0.0052 0.8236 0.0089
-3.750 -0.3080 0.00995 0.00399 -0.0052 0.8157 0.0093
-3.500 -0.2792 0.00968 0.00370 -0.0054 0.8082 0.0096
-3.250 -0.2504 0.00944 0.00342 -0.0055 0.8005 0.0101
-3.000 -0.2214 0.00921 0.00315 -0.0056 0.7924 0.0105
-2.750 -0.1925 0.00901 0.00290 -0.0058 0.7826 0.0109
-2.500 -0.1633 0.00876 0.00263 -0.0060 0.7718 0.0117
-2.250 -0.1340 0.00862 0.00247 -0.0062 0.7601 0.0126
-2.000 -0.1046 0.00850 0.00230 -0.0065 0.7441 0.0136
-1.750 -0.0751 0.00836 0.00210 -0.0067 0.7250 0.0148
-1.500 -0.0452 0.00830 0.00195 -0.0071 0.6932 0.0161
-1.250 -0.0147 0.00838 0.00181 -0.0077 0.6340 0.0174
-1.000 0.0161 0.00854 0.00173 -0.0085 0.5632 0.0201
-0.750 0.0470 0.00881 0.00170 -0.0095 0.4742 0.0231
-0.500 0.0776 0.00913 0.00169 -0.0104 0.3836 0.0272
-0.250 0.1075 0.00922 0.00167 -0.0110 0.3407 0.0379
0.000 0.1372 0.00913 0.00164 -0.0116 0.3098 0.0999
0.250 0.1668 0.00778 0.00149 -0.0131 0.2892 0.5207
0.500 0.1960 0.00726 0.00152 -0.0138 0.2715 0.7097
0.750 0.2248 0.00719 0.00159 -0.0140 0.2543 0.7769
1.000 0.2534 0.00721 0.00166 -0.0140 0.2402 0.8175
1.250 0.2818 0.00726 0.00172 -0.0141 0.2290 0.8395
1.750 0.3397 0.00746 0.00183 -0.0145 0.2061 0.8589
2.000 0.3688 0.00758 0.00189 -0.0148 0.1969 0.8668
2.250 0.3974 0.00768 0.00196 -0.0149 0.1884 0.8743
2.500 0.4263 0.00779 0.00204 -0.0151 0.1816 0.8821
2.750 0.4545 0.00791 0.00212 -0.0152 0.1730 0.8893
3.000 0.4831 0.00803 0.00221 -0.0153 0.1663 0.8968
3.250 0.5112 0.00815 0.00231 -0.0154 0.1597 0.9036
3.500 0.5394 0.00828 0.00241 -0.0155 0.1545 0.9107
3.750 0.5675 0.00840 0.00251 -0.0155 0.1494 0.9170
4.000 0.5950 0.00855 0.00263 -0.0155 0.1427 0.9236
4.250 0.6232 0.00868 0.00275 -0.0156 0.1382 0.9299
4.500 0.6501 0.00881 0.00287 -0.0154 0.1334 0.9358
4.750 0.6774 0.00898 0.00300 -0.0153 0.1282 0.9421
5.000 0.7046 0.00911 0.00314 -0.0153 0.1246 0.9477
5.250 0.7310 0.00926 0.00327 -0.0150 0.1198 0.9538
5.750 0.7841 0.00957 0.00356 -0.0146 0.1126 0.9659
6.000 0.8109 0.00971 0.00371 -0.0144 0.1096 0.9725
6.250 0.8381 0.00988 0.00387 -0.0144 0.1058 0.9792
6.500 0.8667 0.01009 0.00405 -0.0148 0.1013 0.9864
7.000 0.9258 0.01045 0.00443 -0.0159 0.0965 1.0000
7.250 0.9541 0.01069 0.00465 -0.0163 0.0934 1.0000
7.500 0.9821 0.01094 0.00489 -0.0166 0.0900 1.0000
7.750 1.0101 0.01116 0.00513 -0.0169 0.0879 1.0000
8.000 1.0380 0.01139 0.00537 -0.0171 0.0855 1.0000
8.250 1.0657 0.01165 0.00563 -0.0174 0.0830 1.0000
8.500 1.0930 0.01194 0.00591 -0.0176 0.0802 1.0000
8.750 1.1201 0.01223 0.00621 -0.0178 0.0775 1.0000
9.000 1.1474 0.01247 0.00649 -0.0179 0.0758 1.0000
9.250 1.1744 0.01275 0.00678 -0.0181 0.0733 1.0000
9.500 1.2009 0.01309 0.00711 -0.0182 0.0702 1.0000
9.750 1.2271 0.01344 0.00747 -0.0183 0.0670 1.0000
10.000 1.2535 0.01373 0.00779 -0.0184 0.0651 1.0000
10.250 1.2796 0.01406 0.00814 -0.0184 0.0628 1.0000
10.500 1.3051 0.01444 0.00853 -0.0184 0.0604 1.0000
10.750 1.3302 0.01485 0.00895 -0.0184 0.0575 1.0000
11.000 1.3556 0.01520 0.00933 -0.0183 0.0552 1.0000
11.250 1.3803 0.01561 0.00976 -0.0182 0.0525 1.0000
11.500 1.4043 0.01610 0.01025 -0.0181 0.0495 1.0000
11.750 1.4285 0.01651 0.01070 -0.0179 0.0475 1.0000
12.000 1.4522 0.01696 0.01119 -0.0177 0.0451 1.0000
12.250 1.4746 0.01754 0.01177 -0.0174 0.0418 1.0000
12.500 1.4972 0.01806 0.01232 -0.0170 0.0390 1.0000
12.750 1.5180 0.01873 0.01300 -0.0166 0.0351 1.0000
13.000 1.5387 0.01938 0.01367 -0.0160 0.0319 1.0000
13.250 1.5572 0.02020 0.01450 -0.0153 0.0277 1.0000
13.500 1.5738 0.02114 0.01544 -0.0144 0.0231 1.0000
13.750 1.5883 0.02220 0.01652 -0.0132 0.0185 1.0000
14.000 1.5982 0.02341 0.01776 -0.0116 0.0141 1.0000
14.250 1.6044 0.02476 0.01916 -0.0095 0.0106 1.0000
14.500 1.6108 0.02615 0.02061 -0.0077 0.0085 1.0000
14.750 1.6172 0.02757 0.02210 -0.0060 0.0073 1.0000
15.000 1.6242 0.02898 0.02360 -0.0046 0.0067 1.0000
15.250 1.6299 0.03053 0.02525 -0.0033 0.0063 1.0000
15.500 1.6340 0.03228 0.02709 -0.0021 0.0060 1.0000
15.750 1.6363 0.03425 0.02917 -0.0010 0.0057 1.0000
16.000 1.6364 0.03653 0.03157 -0.0001 0.0054 1.0000
16.250 1.6364 0.03894 0.03408 0.0004 0.0053 1.0000
16.500 1.6345 0.04168 0.03695 0.0007 0.0052 1.0000
16.750 1.6297 0.04493 0.04033 0.0005 0.0051 1.0000
17.000 1.6215 0.04886 0.04440 -0.0003 0.0050 1.0000
17.250 1.6084 0.05380 0.04949 -0.0020 0.0050 1.0000
17.500 1.5888 0.06032 0.05620 -0.0051 0.0049 1.0000
17.750 1.5574 0.06978 0.06588 -0.0104 0.0050 1.0000
18.000 1.4974 0.08553 0.08194 -0.0194 0.0052 1.0000
18.250 1.4087 0.10555 0.10224 -0.0294 0.0055 1.0000
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