S4180-098-84 (s4180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4180-098-84 (s4180-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.6 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4180-il-1000000-n5.txt Download as CSV file: xf-s4180-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4180-098-84
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3653 0.10642 0.10470 -0.0193 1.0000 0.0082
-9.000 -0.5284 0.02710 0.02424 -0.0822 0.8426 0.0096
-8.750 -0.5120 0.02280 0.01943 -0.0842 0.8298 0.0097
-8.500 -0.4895 0.02077 0.01709 -0.0849 0.8176 0.0099
-8.250 -0.4651 0.01936 0.01543 -0.0852 0.8060 0.0101
-8.000 -0.4400 0.01806 0.01388 -0.0854 0.7949 0.0103
-7.750 -0.4143 0.01698 0.01257 -0.0856 0.7835 0.0104
-7.500 -0.3878 0.01607 0.01147 -0.0857 0.7721 0.0105
-7.250 -0.3610 0.01531 0.01053 -0.0857 0.7610 0.0106
-7.000 -0.3338 0.01468 0.00973 -0.0857 0.7497 0.0107
-6.750 -0.3072 0.01351 0.00834 -0.0859 0.7379 0.0110
-6.500 -0.2797 0.01285 0.00756 -0.0859 0.7265 0.0112
-6.250 -0.2520 0.01237 0.00696 -0.0859 0.7149 0.0113
-6.000 -0.2241 0.01197 0.00645 -0.0859 0.7032 0.0115
-5.750 -0.1960 0.01159 0.00598 -0.0859 0.6912 0.0117
-5.500 -0.1678 0.01123 0.00552 -0.0859 0.6798 0.0119
-5.250 -0.1396 0.01089 0.00508 -0.0859 0.6686 0.0121
-5.000 -0.1113 0.01058 0.00467 -0.0859 0.6566 0.0124
-4.750 -0.0829 0.01029 0.00429 -0.0858 0.6453 0.0126
-4.500 -0.0545 0.01001 0.00393 -0.0858 0.6346 0.0129
-4.250 -0.0260 0.00977 0.00361 -0.0858 0.6235 0.0131
-4.000 0.0025 0.00958 0.00334 -0.0858 0.6121 0.0135
-3.750 0.0311 0.00942 0.00311 -0.0857 0.6021 0.0137
-3.500 0.0597 0.00914 0.00276 -0.0858 0.5916 0.0142
-3.250 0.0883 0.00894 0.00249 -0.0858 0.5806 0.0147
-3.000 0.1170 0.00878 0.00229 -0.0858 0.5705 0.0152
-2.750 0.1457 0.00866 0.00211 -0.0857 0.5606 0.0157
-2.500 0.1744 0.00856 0.00195 -0.0857 0.5498 0.0163
-2.250 0.2031 0.00846 0.00181 -0.0857 0.5403 0.0169
-2.000 0.2318 0.00839 0.00168 -0.0857 0.5306 0.0175
-1.750 0.2605 0.00829 0.00155 -0.0857 0.5208 0.0190
-1.500 0.2892 0.00823 0.00146 -0.0857 0.5118 0.0212
-1.250 0.3179 0.00814 0.00137 -0.0857 0.5024 0.0298
-1.000 0.3466 0.00805 0.00131 -0.0858 0.4937 0.0467
-0.750 0.3752 0.00802 0.00128 -0.0858 0.4850 0.0575
-0.500 0.4040 0.00797 0.00125 -0.0858 0.4768 0.0692
-0.250 0.4326 0.00794 0.00124 -0.0858 0.4684 0.0858
0.000 0.4613 0.00790 0.00123 -0.0859 0.4606 0.1063
0.250 0.4898 0.00787 0.00123 -0.0859 0.4527 0.1314
0.500 0.5185 0.00782 0.00124 -0.0860 0.4449 0.1632
1.000 0.5757 0.00763 0.00131 -0.0862 0.4296 0.2828
1.250 0.6042 0.00757 0.00136 -0.0863 0.4221 0.3479
1.500 0.6328 0.00741 0.00142 -0.0865 0.4143 0.4463
1.750 0.6612 0.00719 0.00152 -0.0867 0.4064 0.5873
2.000 0.6891 0.00696 0.00162 -0.0867 0.3982 0.7255
2.250 0.7136 0.00672 0.00173 -0.0858 0.3902 0.8650
2.500 0.7386 0.00660 0.00175 -0.0848 0.3816 1.0000
2.750 0.7669 0.00673 0.00182 -0.0848 0.3731 1.0000
3.000 0.7951 0.00687 0.00190 -0.0848 0.3635 1.0000
3.250 0.8233 0.00699 0.00198 -0.0848 0.3550 1.0000
3.500 0.8513 0.00715 0.00208 -0.0847 0.3458 1.0000
3.750 0.8794 0.00729 0.00218 -0.0847 0.3359 1.0000
4.000 0.9073 0.00745 0.00229 -0.0847 0.3259 1.0000
4.250 0.9349 0.00764 0.00242 -0.0846 0.3141 1.0000
4.500 0.9624 0.00785 0.00256 -0.0846 0.3008 1.0000
4.750 0.9898 0.00808 0.00271 -0.0845 0.2863 1.0000
5.000 1.0168 0.00834 0.00289 -0.0844 0.2689 1.0000
5.250 1.0438 0.00859 0.00307 -0.0843 0.2544 1.0000
5.500 1.0705 0.00887 0.00328 -0.0841 0.2384 1.0000
5.750 1.0969 0.00920 0.00351 -0.0840 0.2201 1.0000
6.000 1.1233 0.00951 0.00374 -0.0838 0.2045 1.0000
6.250 1.1495 0.00984 0.00400 -0.0836 0.1898 1.0000
6.500 1.1752 0.01021 0.00428 -0.0834 0.1737 1.0000
6.750 1.2007 0.01060 0.00459 -0.0831 0.1578 1.0000
7.000 1.2263 0.01096 0.00489 -0.0829 0.1451 1.0000
7.250 1.2519 0.01131 0.00519 -0.0826 0.1343 1.0000
7.500 1.2771 0.01168 0.00551 -0.0823 0.1230 1.0000
7.750 1.3020 0.01208 0.00585 -0.0820 0.1121 1.0000
8.000 1.3266 0.01249 0.00621 -0.0817 0.1027 1.0000
8.250 1.3516 0.01284 0.00655 -0.0813 0.0956 1.0000
8.500 1.3759 0.01325 0.00692 -0.0809 0.0881 1.0000
8.750 1.3997 0.01368 0.00732 -0.0805 0.0807 1.0000
9.000 1.4239 0.01406 0.00769 -0.0801 0.0755 1.0000
9.250 1.4472 0.01452 0.00812 -0.0796 0.0698 1.0000
9.500 1.4706 0.01492 0.00853 -0.0791 0.0655 1.0000
9.750 1.4937 0.01534 0.00896 -0.0785 0.0619 1.0000
10.000 1.5156 0.01584 0.00944 -0.0779 0.0575 1.0000
10.250 1.5383 0.01624 0.00987 -0.0773 0.0552 1.0000
10.500 1.5602 0.01669 0.01034 -0.0766 0.0528 1.0000
10.750 1.5805 0.01723 0.01088 -0.0757 0.0496 1.0000
11.000 1.6008 0.01775 0.01141 -0.0748 0.0467 1.0000
11.250 1.6206 0.01825 0.01194 -0.0739 0.0444 1.0000
11.500 1.6386 0.01884 0.01255 -0.0728 0.0418 1.0000
11.750 1.6554 0.01947 0.01319 -0.0714 0.0396 1.0000
12.000 1.6716 0.02002 0.01378 -0.0700 0.0384 1.0000
12.250 1.6839 0.02061 0.01442 -0.0679 0.0370 1.0000
12.500 1.6940 0.02132 0.01517 -0.0657 0.0355 1.0000
12.750 1.7016 0.02223 0.01610 -0.0634 0.0333 1.0000
13.000 1.7103 0.02317 0.01708 -0.0615 0.0319 1.0000
13.250 1.7196 0.02415 0.01812 -0.0598 0.0306 1.0000
13.500 1.7273 0.02531 0.01933 -0.0582 0.0291 1.0000
13.750 1.7335 0.02667 0.02073 -0.0567 0.0277 1.0000
14.000 1.7388 0.02821 0.02231 -0.0553 0.0262 1.0000
14.250 1.7458 0.02969 0.02387 -0.0543 0.0255 1.0000
14.500 1.7516 0.03138 0.02563 -0.0533 0.0244 1.0000
14.750 1.7555 0.03331 0.02762 -0.0525 0.0233 1.0000
15.000 1.7571 0.03558 0.02994 -0.0518 0.0220 1.0000
15.250 1.7590 0.03793 0.03236 -0.0514 0.0210 1.0000
15.500 1.7612 0.04034 0.03486 -0.0511 0.0203 1.0000
15.750 1.7611 0.04309 0.03768 -0.0510 0.0191 1.0000
16.000 1.7595 0.04613 0.04079 -0.0511 0.0182 1.0000
16.250 1.7557 0.04953 0.04426 -0.0514 0.0172 1.0000
16.500 1.7527 0.05294 0.04776 -0.0518 0.0163 1.0000
16.750 1.7488 0.05662 0.05153 -0.0525 0.0154 1.0000
17.000 1.7421 0.06078 0.05578 -0.0535 0.0144 1.0000
17.250 1.7349 0.06519 0.06028 -0.0547 0.0136 1.0000
17.500 1.7288 0.06952 0.06471 -0.0559 0.0129 1.0000
17.750 1.7198 0.07445 0.06973 -0.0576 0.0118 1.0000
18.000 1.7088 0.07978 0.07514 -0.0594 0.0108 1.0000
18.250 1.6991 0.08505 0.08051 -0.0614 0.0100 1.0000
18.500 1.6850 0.09117 0.08673 -0.0639 0.0087 1.0000
18.750 1.6723 0.09717 0.09283 -0.0664 0.0079 1.0000
19.000 1.6562 0.10394 0.09970 -0.0694 0.0066 1.0000
19.250 1.6414 0.11062 0.10648 -0.0726 0.0057 1.0000
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