SIKORSKY SC1095 AIRFOIL (sc1095-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SIKORSKY SC1095 AIRFOIL (sc1095-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.55 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc1095-il-1000000-n5.txt Download as CSV file: xf-sc1095-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1095 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
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0032 0.10707 0.10466 0.0182 1.0000 0.0032
-14.750 -1.0759 0.08938 0.08686 0.0079 1.0000 0.0031
-14.500 -1.2586 0.04490 0.04171 -0.0250 1.0000 0.0030
-14.250 -1.2759 0.03956 0.03616 -0.0279 1.0000 0.0030
-14.000 -1.2852 0.03632 0.03276 -0.0277 1.0000 0.0030
-13.750 -1.2898 0.03401 0.03031 -0.0259 1.0000 0.0030
-13.500 -1.2852 0.03205 0.02819 -0.0246 1.0000 0.0030
-13.250 -1.2759 0.03029 0.02630 -0.0236 1.0000 0.0030
-13.000 -1.2636 0.02872 0.02459 -0.0226 1.0000 0.0030
-12.750 -1.2489 0.02730 0.02304 -0.0218 1.0000 0.0031
-12.500 -1.2325 0.02599 0.02161 -0.0210 1.0000 0.0031
-12.250 -1.2145 0.02479 0.02029 -0.0203 1.0000 0.0031
-12.000 -1.1953 0.02367 0.01906 -0.0197 1.0000 0.0031
-11.750 -1.1751 0.02264 0.01792 -0.0191 1.0000 0.0031
-11.500 -1.1540 0.02168 0.01685 -0.0186 1.0000 0.0032
-11.250 -1.1321 0.02078 0.01586 -0.0182 1.0000 0.0032
-11.000 -1.1098 0.01987 0.01485 -0.0177 1.0000 0.0032
-10.750 -1.0876 0.01889 0.01376 -0.0172 1.0000 0.0033
-10.500 -1.0644 0.01800 0.01276 -0.0168 1.0000 0.0033
-10.250 -1.0405 0.01722 0.01189 -0.0165 1.0000 0.0034
-10.000 -1.0161 0.01650 0.01108 -0.0162 1.0000 0.0035
-9.750 -0.9912 0.01583 0.01034 -0.0159 1.0000 0.0036
-9.500 -0.9658 0.01522 0.00966 -0.0157 1.0000 0.0037
-9.250 -0.9401 0.01467 0.00905 -0.0155 1.0000 0.0038
-9.000 -0.9141 0.01415 0.00847 -0.0154 1.0000 0.0040
-8.750 -0.8877 0.01368 0.00794 -0.0152 1.0000 0.0041
-8.500 -0.8612 0.01323 0.00745 -0.0151 1.0000 0.0042
-8.250 -0.8344 0.01282 0.00699 -0.0150 1.0000 0.0044
-8.000 -0.8075 0.01242 0.00655 -0.0149 1.0000 0.0045
-7.750 -0.7804 0.01206 0.00615 -0.0148 1.0000 0.0047
-7.500 -0.7534 0.01167 0.00573 -0.0147 1.0000 0.0054
-7.250 -0.7266 0.01120 0.00526 -0.0146 1.0000 0.0076
-7.000 -0.7005 0.01062 0.00477 -0.0145 1.0000 0.0185
-6.500 -0.6392 0.01003 0.00420 -0.0158 0.9885 0.0260
-6.250 -0.6081 0.00976 0.00394 -0.0165 0.9832 0.0290
-6.000 -0.5783 0.00954 0.00371 -0.0169 0.9778 0.0320
-5.750 -0.5496 0.00930 0.00348 -0.0171 0.9724 0.0355
-5.500 -0.5224 0.00908 0.00328 -0.0169 0.9659 0.0407
-5.250 -0.4960 0.00884 0.00310 -0.0165 0.9587 0.0499
-5.000 -0.4692 0.00865 0.00293 -0.0162 0.9506 0.0585
-4.750 -0.4428 0.00847 0.00280 -0.0157 0.9421 0.0674
-4.500 -0.4165 0.00832 0.00266 -0.0152 0.9321 0.0733
-4.250 -0.3904 0.00819 0.00253 -0.0147 0.9185 0.0784
-4.000 -0.3648 0.00812 0.00238 -0.0139 0.8974 0.0810
-3.750 -0.3384 0.00805 0.00223 -0.0133 0.8733 0.0839
-3.500 -0.3108 0.00795 0.00210 -0.0131 0.8570 0.0882
-3.250 -0.2828 0.00786 0.00198 -0.0130 0.8432 0.0919
-3.000 -0.2545 0.00781 0.00187 -0.0129 0.8289 0.0948
-2.750 -0.2262 0.00773 0.00177 -0.0129 0.8140 0.0994
-2.500 -0.1979 0.00764 0.00166 -0.0128 0.7979 0.1064
-2.250 -0.1695 0.00759 0.00157 -0.0128 0.7815 0.1121
-2.000 -0.1410 0.00753 0.00149 -0.0128 0.7632 0.1194
-1.750 -0.1126 0.00749 0.00140 -0.0128 0.7382 0.1278
-1.500 -0.0844 0.00751 0.00132 -0.0128 0.6982 0.1402
-1.250 -0.0564 0.00757 0.00126 -0.0128 0.6415 0.1591
-1.000 -0.0282 0.00762 0.00120 -0.0129 0.5859 0.1850
-0.750 0.0000 0.00762 0.00117 -0.0131 0.5358 0.2230
-0.500 0.0283 0.00763 0.00115 -0.0133 0.4866 0.2647
-0.250 0.0566 0.00763 0.00113 -0.0135 0.4447 0.3073
0.000 0.0849 0.00761 0.00113 -0.0137 0.4038 0.3566
0.250 0.1132 0.00757 0.00114 -0.0139 0.3687 0.4112
0.750 0.1698 0.00738 0.00118 -0.0144 0.3100 0.5508
1.000 0.1980 0.00730 0.00122 -0.0145 0.2867 0.6189
1.250 0.2263 0.00728 0.00127 -0.0146 0.2642 0.6692
1.500 0.2540 0.00718 0.00135 -0.0146 0.2454 0.7423
1.750 0.2813 0.00715 0.00144 -0.0144 0.2248 0.8003
2.000 0.3083 0.00723 0.00154 -0.0141 0.2019 0.8402
2.250 0.3343 0.00731 0.00166 -0.0135 0.1798 0.8774
2.500 0.3593 0.00742 0.00178 -0.0126 0.1630 0.9082
2.750 0.3845 0.00752 0.00188 -0.0118 0.1524 0.9297
3.000 0.4100 0.00765 0.00199 -0.0111 0.1427 0.9451
3.250 0.4361 0.00777 0.00208 -0.0106 0.1349 0.9575
3.500 0.4628 0.00789 0.00217 -0.0102 0.1274 0.9671
3.750 0.4910 0.00801 0.00227 -0.0102 0.1194 0.9749
4.000 0.5210 0.00815 0.00237 -0.0106 0.1120 0.9819
4.250 0.5528 0.00831 0.00249 -0.0115 0.1055 0.9891
4.500 0.5848 0.00847 0.00263 -0.0124 0.1001 0.9972
4.750 0.6139 0.00863 0.00277 -0.0126 0.0959 1.0000
5.000 0.6419 0.00882 0.00293 -0.0127 0.0912 1.0000
5.250 0.6701 0.00900 0.00310 -0.0128 0.0874 1.0000
5.500 0.6983 0.00916 0.00326 -0.0128 0.0849 1.0000
5.750 0.7263 0.00936 0.00345 -0.0129 0.0813 1.0000
6.000 0.7542 0.00959 0.00365 -0.0129 0.0774 1.0000
6.250 0.7821 0.00978 0.00385 -0.0130 0.0749 1.0000
6.500 0.8101 0.00997 0.00405 -0.0130 0.0723 1.0000
6.750 0.8377 0.01020 0.00426 -0.0131 0.0688 1.0000
7.000 0.8653 0.01046 0.00451 -0.0131 0.0657 1.0000
7.250 0.8928 0.01069 0.00476 -0.0131 0.0635 1.0000
7.500 0.9205 0.01089 0.00498 -0.0131 0.0618 1.0000
7.750 0.9477 0.01115 0.00523 -0.0131 0.0575 1.0000
8.000 0.9746 0.01146 0.00551 -0.0130 0.0529 1.0000
8.250 1.0018 0.01171 0.00578 -0.0130 0.0500 1.0000
8.500 1.0281 0.01208 0.00610 -0.0129 0.0440 1.0000
8.750 1.0544 0.01245 0.00645 -0.0128 0.0376 1.0000
9.000 1.0789 0.01310 0.00701 -0.0125 0.0246 1.0000
9.250 1.1017 0.01405 0.00788 -0.0120 0.0115 1.0000
9.500 1.1263 0.01465 0.00848 -0.0117 0.0083 1.0000
9.750 1.1513 0.01516 0.00903 -0.0114 0.0070 1.0000
10.000 1.1759 0.01570 0.00961 -0.0111 0.0062 1.0000
10.250 1.2003 0.01623 0.01019 -0.0108 0.0057 1.0000
10.500 1.2247 0.01675 0.01077 -0.0104 0.0054 1.0000
10.750 1.2485 0.01731 0.01138 -0.0100 0.0052 1.0000
11.000 1.2719 0.01792 0.01205 -0.0096 0.0049 1.0000
11.250 1.2947 0.01856 0.01276 -0.0091 0.0047 1.0000
11.500 1.3168 0.01928 0.01355 -0.0085 0.0045 1.0000
11.750 1.3378 0.02009 0.01444 -0.0078 0.0043 1.0000
12.000 1.3579 0.02097 0.01541 -0.0071 0.0041 1.0000
12.250 1.3787 0.02169 0.01621 -0.0064 0.0040 1.0000
12.500 1.3986 0.02248 0.01707 -0.0056 0.0039 1.0000
12.750 1.4173 0.02334 0.01801 -0.0048 0.0038 1.0000
13.000 1.4348 0.02426 0.01904 -0.0038 0.0037 1.0000
13.250 1.4509 0.02526 0.02013 -0.0027 0.0037 1.0000
13.500 1.4654 0.02632 0.02129 -0.0014 0.0036 1.0000
13.750 1.4777 0.02747 0.02255 0.0000 0.0035 1.0000
14.000 1.4856 0.02869 0.02387 0.0020 0.0034 1.0000
14.250 1.4898 0.03007 0.02536 0.0042 0.0034 1.0000
14.500 1.4923 0.03171 0.02711 0.0060 0.0034 1.0000
14.750 1.4930 0.03367 0.02918 0.0074 0.0033 1.0000
15.000 1.4916 0.03605 0.03169 0.0081 0.0033 1.0000
15.250 1.4875 0.03902 0.03480 0.0082 0.0032 1.0000
15.500 1.4799 0.04284 0.03877 0.0072 0.0032 1.0000
15.750 1.4677 0.04789 0.04399 0.0047 0.0032 1.0000
16.000 1.4479 0.05503 0.05133 0.0002 0.0032 1.0000
16.250 1.4112 0.06640 0.06294 -0.0076 0.0032 1.0000
16.500 1.3387 0.08464 0.08149 -0.0182 0.0033 1.0000
16.750 1.2427 0.10641 0.10355 -0.0293 0.0035 1.0000
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Polar data table (+)
Polar graphs
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