SIKORSKY SC2110 AIRFOIL (sc2110-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: SIKORSKY SC2110 AIRFOIL (sc2110-il) Reynolds number: 50,000 Max Cl/Cd: 27.59 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc2110-il-50000-n5.txt Download as CSV file: xf-sc2110-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5085 0.10404 0.09758 -0.0078 1.0000 0.1353
-8.500 -0.4954 0.10043 0.09398 -0.0071 1.0000 0.1408
-8.250 -0.5209 0.09678 0.09046 -0.0161 1.0000 0.1482
-8.000 -0.5026 0.09240 0.08610 -0.0137 1.0000 0.1525
-7.750 -0.4967 0.08870 0.08244 -0.0147 1.0000 0.1570
-7.250 -0.5037 0.07327 0.06652 -0.0295 1.0000 0.0704
-7.000 -0.5112 0.06830 0.06106 -0.0310 1.0000 0.0607
-6.750 -0.4994 0.06482 0.05766 -0.0300 1.0000 0.0584
-6.500 -0.4950 0.06159 0.05433 -0.0288 1.0000 0.0566
-6.250 -0.4919 0.05843 0.05101 -0.0272 1.0000 0.0548
-6.000 -0.4878 0.05517 0.04749 -0.0255 1.0000 0.0528
-5.750 -0.4819 0.05198 0.04345 -0.0231 1.0000 0.0492
-5.500 -0.4710 0.04913 0.04050 -0.0216 1.0000 0.0487
-5.250 -0.4591 0.04645 0.03762 -0.0200 1.0000 0.0482
-5.000 -0.4455 0.04389 0.03480 -0.0184 1.0000 0.0478
-4.750 -0.4300 0.04148 0.03205 -0.0170 1.0000 0.0477
-4.500 -0.4126 0.03928 0.02943 -0.0155 1.0000 0.0483
-4.250 -0.3933 0.03739 0.02705 -0.0141 1.0000 0.0492
-4.000 -0.3743 0.03518 0.02474 -0.0132 1.0000 0.0504
-3.750 -0.3532 0.03339 0.02275 -0.0122 1.0000 0.0513
-3.500 -0.3306 0.03173 0.02083 -0.0111 1.0000 0.0518
-3.250 -0.3074 0.03024 0.01911 -0.0102 1.0000 0.0526
-3.000 -0.2839 0.02896 0.01768 -0.0092 1.0000 0.0544
-2.750 -0.2600 0.02792 0.01646 -0.0082 1.0000 0.0577
-2.500 -0.2356 0.02702 0.01537 -0.0070 1.0000 0.0605
-2.250 -0.2118 0.02596 0.01432 -0.0061 1.0000 0.0632
-2.000 -0.1883 0.02523 0.01352 -0.0052 1.0000 0.0677
-1.750 -0.1657 0.02462 0.01278 -0.0043 1.0000 0.0741
-1.500 -0.1430 0.02396 0.01210 -0.0037 1.0000 0.0814
-1.250 -0.1153 0.02335 0.01147 -0.0042 0.9981 0.0962
-1.000 -0.0791 0.02231 0.01079 -0.0064 0.9939 0.1545
-0.750 -0.0324 0.02001 0.01144 -0.0052 0.9947 1.0000
-0.500 0.0162 0.02030 0.01132 -0.0097 0.9829 1.0000
-0.250 0.0828 0.02064 0.01130 -0.0174 0.9653 1.0000
0.000 0.1547 0.02079 0.01120 -0.0256 0.9436 1.0000
0.250 0.2142 0.02080 0.01104 -0.0312 0.9245 1.0000
0.500 0.2502 0.02077 0.01092 -0.0325 0.9057 1.0000
0.750 0.2796 0.02072 0.01081 -0.0324 0.8866 1.0000
1.000 0.3080 0.02059 0.01063 -0.0319 0.8665 1.0000
1.250 0.3360 0.02035 0.01037 -0.0310 0.8458 1.0000
1.500 0.3554 0.02016 0.01016 -0.0287 0.8205 1.0000
1.750 0.3765 0.01989 0.00987 -0.0265 0.7928 1.0000
2.000 0.3961 0.01962 0.00959 -0.0241 0.7587 1.0000
2.250 0.4160 0.01935 0.00930 -0.0216 0.7140 1.0000
2.500 0.4388 0.01901 0.00882 -0.0192 0.6472 1.0000
2.750 0.4627 0.01880 0.00805 -0.0162 0.5516 1.0000
3.000 0.4809 0.01932 0.00788 -0.0136 0.4676 1.0000
3.250 0.4994 0.02008 0.00813 -0.0119 0.4161 1.0000
3.500 0.5199 0.02082 0.00855 -0.0107 0.3821 1.0000
3.750 0.5416 0.02155 0.00901 -0.0098 0.3563 1.0000
4.000 0.5646 0.02223 0.00952 -0.0092 0.3349 1.0000
4.250 0.5883 0.02290 0.01006 -0.0086 0.3170 1.0000
4.500 0.6126 0.02356 0.01064 -0.0081 0.3011 1.0000
4.750 0.6376 0.02423 0.01124 -0.0078 0.2873 1.0000
5.000 0.6630 0.02491 0.01185 -0.0075 0.2748 1.0000
5.250 0.6884 0.02561 0.01249 -0.0072 0.2636 1.0000
5.500 0.7142 0.02631 0.01326 -0.0069 0.2525 1.0000
5.750 0.7399 0.02708 0.01403 -0.0067 0.2432 1.0000
6.000 0.7651 0.02785 0.01478 -0.0064 0.2340 1.0000
6.250 0.7904 0.02871 0.01577 -0.0062 0.2252 1.0000
6.500 0.8157 0.02957 0.01662 -0.0060 0.2182 1.0000
6.750 0.8404 0.03057 0.01778 -0.0058 0.2106 1.0000
7.000 0.8647 0.03148 0.01875 -0.0055 0.2035 1.0000
7.250 0.8885 0.03260 0.02001 -0.0053 0.1970 1.0000
7.500 0.9121 0.03378 0.02138 -0.0050 0.1910 1.0000
7.750 0.9364 0.03480 0.02235 -0.0048 0.1862 1.0000
8.000 0.9570 0.03632 0.02427 -0.0044 0.1797 1.0000
8.250 0.9790 0.03752 0.02560 -0.0040 0.1743 1.0000
8.500 1.0020 0.03881 0.02691 -0.0038 0.1705 1.0000
8.750 1.0186 0.04092 0.02953 -0.0032 0.1655 1.0000
9.000 1.0371 0.04251 0.03135 -0.0027 0.1607 1.0000
9.250 1.0590 0.04364 0.03247 -0.0023 0.1569 1.0000
9.500 1.0695 0.04631 0.03562 -0.0014 0.1527 1.0000
9.750 1.0792 0.04903 0.03876 -0.0006 0.1492 1.0000
10.000 1.0912 0.05122 0.04120 0.0001 0.1459 1.0000
10.250 1.1096 0.05261 0.04264 0.0007 0.1428 1.0000
10.500 1.1075 0.05611 0.04654 0.0018 0.1398 1.0000
10.750 1.0922 0.06067 0.05156 0.0031 0.1371 1.0000
11.000 1.0717 0.06542 0.05662 0.0041 0.1352 1.0000
11.250 1.0362 0.07148 0.06291 0.0043 0.1342 1.0000
11.500 0.9666 0.08377 0.07536 -0.0014 0.1338 1.0000
11.750 0.9009 0.10150 0.09307 -0.0135 0.1324 1.0000
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Polar data table (+)
Polar graphs
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