S4110 (s4110-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.65 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4110-il-1000000.txt Download as CSV file: xf-s4110-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S4110
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4084 0.08226 0.08067 -0.0324 1.0000 0.0140
-8.250 -0.4158 0.07888 0.07733 -0.0325 1.0000 0.0140
-8.000 -0.4236 0.07686 0.07534 -0.0312 1.0000 0.0146
-7.750 -0.4534 0.03211 0.02993 -0.0810 0.9876 0.0132
-7.500 -0.4331 0.01837 0.01474 -0.0895 0.9838 0.0102
-7.250 -0.4052 0.01659 0.01270 -0.0904 0.9801 0.0103
-7.000 -0.3743 0.01524 0.01116 -0.0916 0.9772 0.0105
-6.750 -0.3423 0.01394 0.00965 -0.0930 0.9748 0.0107
-6.500 -0.3101 0.01271 0.00823 -0.0942 0.9724 0.0108
-6.250 -0.2794 0.01176 0.00714 -0.0949 0.9691 0.0110
-6.000 -0.2523 0.01104 0.00631 -0.0948 0.9627 0.0113
-5.750 -0.2221 0.01044 0.00562 -0.0953 0.9581 0.0118
-5.500 -0.1946 0.00996 0.00505 -0.0951 0.9512 0.0122
-5.250 -0.1661 0.00957 0.00459 -0.0952 0.9445 0.0124
-5.000 -0.1395 0.00883 0.00373 -0.0949 0.9364 0.0131
-4.750 -0.1117 0.00842 0.00323 -0.0947 0.9290 0.0139
-4.500 -0.0847 0.00812 0.00288 -0.0945 0.9201 0.0147
-4.250 -0.0571 0.00787 0.00257 -0.0942 0.9122 0.0157
-4.000 -0.0299 0.00763 0.00227 -0.0939 0.9033 0.0180
-3.750 -0.0027 0.00727 0.00199 -0.0937 0.8948 0.0337
-3.500 0.0247 0.00712 0.00185 -0.0934 0.8862 0.0466
-3.250 0.0523 0.00702 0.00172 -0.0932 0.8773 0.0527
-3.000 0.0798 0.00692 0.00161 -0.0930 0.8688 0.0602
-2.750 0.1073 0.00680 0.00149 -0.0928 0.8595 0.0688
-2.500 0.1349 0.00670 0.00138 -0.0927 0.8505 0.0790
-2.250 0.1623 0.00659 0.00128 -0.0925 0.8412 0.0963
-2.000 0.1899 0.00645 0.00119 -0.0923 0.8309 0.1201
-1.750 0.2173 0.00628 0.00111 -0.0922 0.8213 0.1557
-1.500 0.2447 0.00613 0.00104 -0.0920 0.8116 0.1992
-1.250 0.2721 0.00593 0.00099 -0.0919 0.8009 0.2583
-1.000 0.2993 0.00571 0.00096 -0.0918 0.7895 0.3344
-0.750 0.3265 0.00552 0.00094 -0.0916 0.7779 0.4104
-0.500 0.3536 0.00536 0.00093 -0.0915 0.7663 0.4856
-0.250 0.3805 0.00518 0.00094 -0.0912 0.7539 0.5698
0.000 0.4071 0.00501 0.00096 -0.0909 0.7406 0.6543
0.250 0.4331 0.00484 0.00100 -0.0904 0.7262 0.7423
0.500 0.4581 0.00471 0.00104 -0.0895 0.7113 0.8221
0.750 0.4785 0.00453 0.00108 -0.0875 0.6958 0.9256
1.000 0.5146 0.00453 0.00105 -0.0891 0.6770 1.0000
1.250 0.5414 0.00465 0.00108 -0.0887 0.6563 1.0000
1.500 0.5681 0.00478 0.00111 -0.0884 0.6339 1.0000
1.750 0.5945 0.00495 0.00116 -0.0880 0.6093 1.0000
2.000 0.6211 0.00511 0.00121 -0.0877 0.5839 1.0000
2.250 0.6476 0.00528 0.00128 -0.0873 0.5581 1.0000
2.500 0.6736 0.00551 0.00137 -0.0869 0.5269 1.0000
2.750 0.6996 0.00574 0.00147 -0.0865 0.4964 1.0000
3.000 0.7254 0.00599 0.00159 -0.0861 0.4640 1.0000
3.250 0.7509 0.00629 0.00172 -0.0856 0.4262 1.0000
3.750 0.8019 0.00690 0.00204 -0.0848 0.3573 1.0000
4.000 0.8270 0.00724 0.00222 -0.0843 0.3216 1.0000
4.250 0.8524 0.00756 0.00240 -0.0839 0.2915 1.0000
4.500 0.8775 0.00790 0.00261 -0.0834 0.2605 1.0000
4.750 0.9026 0.00825 0.00283 -0.0830 0.2312 1.0000
5.000 0.9277 0.00860 0.00305 -0.0825 0.2059 1.0000
5.250 0.9530 0.00892 0.00327 -0.0821 0.1836 1.0000
5.750 1.0032 0.00957 0.00376 -0.0812 0.1475 1.0000
6.000 1.0283 0.00989 0.00402 -0.0808 0.1321 1.0000
6.250 1.0534 0.01021 0.00428 -0.0803 0.1192 1.0000
6.500 1.0783 0.01054 0.00457 -0.0799 0.1074 1.0000
6.750 1.1030 0.01088 0.00485 -0.0794 0.0969 1.0000
7.000 1.1281 0.01117 0.00514 -0.0789 0.0890 1.0000
7.250 1.1527 0.01151 0.00545 -0.0784 0.0804 1.0000
7.500 1.1766 0.01191 0.00580 -0.0778 0.0699 1.0000
7.750 1.2006 0.01230 0.00614 -0.0772 0.0610 1.0000
8.000 1.2245 0.01267 0.00650 -0.0766 0.0538 1.0000
8.250 1.2478 0.01311 0.00691 -0.0760 0.0466 1.0000
8.500 1.2710 0.01353 0.00732 -0.0753 0.0415 1.0000
8.750 1.2940 0.01398 0.00778 -0.0745 0.0365 1.0000
9.000 1.3168 0.01442 0.00821 -0.0738 0.0327 1.0000
9.250 1.3384 0.01497 0.00876 -0.0729 0.0285 1.0000
9.500 1.3614 0.01535 0.00918 -0.0722 0.0265 1.0000
9.750 1.3824 0.01591 0.00974 -0.0712 0.0234 1.0000
10.000 1.4033 0.01648 0.01035 -0.0702 0.0210 1.0000
10.250 1.4248 0.01694 0.01084 -0.0693 0.0190 1.0000
10.500 1.4427 0.01774 0.01165 -0.0679 0.0161 1.0000
10.750 1.4632 0.01823 0.01220 -0.0668 0.0149 1.0000
11.000 1.4825 0.01881 0.01281 -0.0657 0.0135 1.0000
11.250 1.4980 0.01970 0.01373 -0.0639 0.0119 1.0000
11.500 1.5141 0.02046 0.01457 -0.0623 0.0111 1.0000
11.750 1.5306 0.02106 0.01525 -0.0607 0.0105 1.0000
12.000 1.5444 0.02170 0.01595 -0.0586 0.0099 1.0000
12.250 1.5559 0.02246 0.01675 -0.0563 0.0093 1.0000
12.500 1.5634 0.02349 0.01786 -0.0535 0.0087 1.0000
12.750 1.5642 0.02499 0.01948 -0.0500 0.0081 1.0000
13.000 1.5748 0.02584 0.02042 -0.0480 0.0079 1.0000
13.250 1.5831 0.02689 0.02156 -0.0459 0.0077 1.0000
13.500 1.5903 0.02806 0.02283 -0.0438 0.0075 1.0000
13.750 1.5965 0.02937 0.02422 -0.0418 0.0072 1.0000
14.000 1.6012 0.03084 0.02581 -0.0399 0.0070 1.0000
14.250 1.6060 0.03238 0.02743 -0.0382 0.0068 1.0000
14.500 1.6080 0.03425 0.02940 -0.0366 0.0066 1.0000
14.750 1.6091 0.03629 0.03155 -0.0352 0.0064 1.0000
15.000 1.6063 0.03885 0.03421 -0.0340 0.0062 1.0000
15.250 1.6002 0.04192 0.03741 -0.0331 0.0061 1.0000
15.500 1.5879 0.04592 0.04156 -0.0327 0.0058 1.0000
15.750 1.5716 0.05079 0.04661 -0.0330 0.0057 1.0000
16.000 1.5525 0.05649 0.05249 -0.0342 0.0056 1.0000
16.250 1.5414 0.06151 0.05766 -0.0358 0.0056 1.0000
16.500 1.5330 0.06644 0.06272 -0.0377 0.0056 1.0000
16.750 1.5214 0.07223 0.06866 -0.0402 0.0055 1.0000
17.000 1.5084 0.07859 0.07516 -0.0433 0.0055 1.0000
17.250 1.4902 0.08622 0.08294 -0.0472 0.0055 1.0000
17.500 1.4658 0.09544 0.09233 -0.0522 0.0055 1.0000
17.750 1.4439 0.10448 0.10153 -0.0573 0.0055 1.0000
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