EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 100,000 Max Cl/Cd: 34.93 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stf86361-il-100000-n5.txt Download as CSV file: xf-stf86361-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STF 863-615 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3228 0.13082 0.12565 -0.0886 0.9538 0.0559
-12.000 -0.3322 0.12730 0.12218 -0.0917 0.9520 0.0564
-11.750 -0.3408 0.12340 0.11832 -0.0945 0.9506 0.0566
-11.500 -0.3154 0.12017 0.11505 -0.0887 0.9507 0.0599
-11.250 -0.3114 0.11739 0.11227 -0.0887 0.9499 0.0625
-10.250 -0.3774 0.10312 0.09825 -0.0940 0.9412 0.0701
-9.750 -0.3669 0.09701 0.09221 -0.0902 0.9389 0.0742
-9.250 -0.3127 0.08301 0.07856 -0.0846 0.9268 0.0782
-7.750 -0.4849 0.06293 0.05691 -0.0872 0.9149 0.0327
-7.500 -0.4764 0.05907 0.05290 -0.0871 0.9131 0.0307
-7.250 -0.4588 0.05428 0.04735 -0.0874 0.9112 0.0256
-7.000 -0.4368 0.05089 0.04349 -0.0887 0.9098 0.0257
-6.750 -0.4116 0.04749 0.03960 -0.0905 0.9087 0.0271
-6.500 -0.3955 0.04533 0.03726 -0.0899 0.9067 0.0279
-6.250 -0.3736 0.04318 0.03449 -0.0891 0.9045 0.0269
-6.000 -0.3487 0.04149 0.03242 -0.0890 0.9025 0.0266
-5.750 -0.3222 0.03975 0.03035 -0.0891 0.9009 0.0265
-5.500 -0.2953 0.03799 0.02837 -0.0892 0.8996 0.0268
-5.250 -0.2683 0.03651 0.02685 -0.0896 0.8983 0.0285
-5.000 -0.2396 0.03557 0.02582 -0.0902 0.8970 0.0309
-4.750 -0.2101 0.03461 0.02476 -0.0905 0.8959 0.0316
-4.500 -0.1836 0.03386 0.02396 -0.0905 0.8944 0.0322
-4.250 -0.1677 0.03328 0.02332 -0.0887 0.8908 0.0328
-4.000 -0.1424 0.03276 0.02274 -0.0889 0.8883 0.0340
-3.750 -0.1132 0.03221 0.02215 -0.0901 0.8864 0.0377
-3.500 -0.0819 0.03194 0.02174 -0.0914 0.8846 0.0398
-3.250 -0.0488 0.03178 0.02141 -0.0929 0.8831 0.0419
-3.000 -0.0141 0.03168 0.02117 -0.0948 0.8818 0.0456
-2.750 0.0045 0.03162 0.02108 -0.0939 0.8774 0.0531
-2.250 0.0638 0.03151 0.02326 -0.0960 0.8722 0.6615
-2.000 0.0888 0.03209 0.02371 -0.0948 0.8695 0.6786
-1.750 0.1230 0.03239 0.02384 -0.0963 0.8678 0.6885
-1.500 0.1314 0.03269 0.02412 -0.0927 0.8609 0.6944
-1.250 0.1523 0.03313 0.02453 -0.0909 0.8574 0.7095
-1.000 0.1768 0.03350 0.02484 -0.0897 0.8550 0.7230
-0.750 0.1906 0.03388 0.02522 -0.0869 0.8504 0.7356
-0.500 0.2037 0.03421 0.02557 -0.0838 0.8454 0.7494
-0.250 0.2324 0.03437 0.02567 -0.0843 0.8426 0.7555
0.000 0.2678 0.03447 0.02568 -0.0866 0.8407 0.7571
0.250 0.2890 0.03473 0.02589 -0.0866 0.8353 0.7586
0.500 0.3138 0.03491 0.02605 -0.0869 0.8311 0.7598
0.750 0.3447 0.03501 0.02613 -0.0881 0.8284 0.7610
1.000 0.3788 0.03508 0.02619 -0.0899 0.8264 0.7618
1.250 0.3935 0.03537 0.02651 -0.0885 0.8188 0.7630
1.500 0.4245 0.03541 0.02656 -0.0897 0.8152 0.7643
1.750 0.4605 0.03534 0.02652 -0.0917 0.8127 0.7655
2.000 0.4775 0.03550 0.02672 -0.0906 0.8037 0.7665
2.250 0.5124 0.03538 0.02664 -0.0924 0.8004 0.7674
2.500 0.5329 0.03555 0.02687 -0.0920 0.7927 0.7685
2.750 0.5636 0.03555 0.02696 -0.0931 0.7884 0.7698
3.000 0.5985 0.03549 0.02698 -0.0950 0.7859 0.7711
3.250 0.6142 0.03589 0.02747 -0.0939 0.7767 0.7722
3.750 0.6646 0.03619 0.02802 -0.0945 0.7649 0.7739
4.000 0.6962 0.03604 0.02802 -0.0955 0.7608 0.7747
4.250 0.7157 0.03620 0.02832 -0.0947 0.7515 0.7755
4.500 0.7497 0.03576 0.02808 -0.0959 0.7469 0.7766
4.750 0.7696 0.03583 0.02831 -0.0950 0.7364 0.7779
5.000 0.8069 0.03508 0.02778 -0.0964 0.7321 0.7792
5.250 0.8282 0.03495 0.02783 -0.0955 0.7201 0.7804
5.500 0.8555 0.03413 0.02725 -0.0950 0.7065 0.7815
5.750 0.8784 0.03295 0.02624 -0.0932 0.6825 0.7827
6.000 0.9077 0.03108 0.02446 -0.0916 0.6386 0.7838
6.250 0.9617 0.02753 0.01914 -0.0910 0.3633 0.7848
6.500 0.9590 0.02959 0.02025 -0.0870 0.2203 0.7858
6.750 0.9593 0.03180 0.02155 -0.0838 0.0850 0.7868
7.000 0.9680 0.03336 0.02281 -0.0815 0.0464 0.7878
7.250 0.9804 0.03455 0.02404 -0.0797 0.0385 0.7889
7.500 0.9937 0.03566 0.02531 -0.0780 0.0348 0.7903
7.750 1.0053 0.03690 0.02669 -0.0762 0.0324 0.7917
8.000 1.0132 0.03846 0.02838 -0.0739 0.0306 0.7931
8.250 1.0236 0.03987 0.02994 -0.0720 0.0296 0.7946
8.500 1.0353 0.04125 0.03151 -0.0702 0.0283 0.7960
8.750 1.0486 0.04259 0.03299 -0.0688 0.0263 0.7973
9.000 1.0626 0.04397 0.03446 -0.0675 0.0245 0.7987
9.250 1.0792 0.04548 0.03605 -0.0665 0.0234 0.8002
9.750 1.1390 0.04929 0.04008 -0.0669 0.0217 0.8031
10.000 1.1632 0.05117 0.04232 -0.0664 0.0208 0.8047
10.250 1.1801 0.05321 0.04473 -0.0652 0.0193 0.8063
10.500 1.1953 0.05570 0.04756 -0.0640 0.0184 0.8081
10.750 1.2060 0.05863 0.05087 -0.0623 0.0180 0.8099
11.000 1.2101 0.06177 0.05439 -0.0600 0.0177 0.8117
11.250 1.2085 0.06508 0.05807 -0.0573 0.0175 0.8135
11.500 1.2022 0.06857 0.06194 -0.0545 0.0174 0.8154
11.750 1.1919 0.07218 0.06591 -0.0515 0.0173 0.8171
12.000 1.1784 0.07602 0.07008 -0.0487 0.0173 0.8189
12.250 1.1624 0.08009 0.07447 -0.0463 0.0173 0.8208
12.500 1.1447 0.08438 0.07904 -0.0443 0.0173 0.8227
12.750 1.1252 0.08906 0.08401 -0.0430 0.0173 0.8245
13.000 1.1045 0.09412 0.08933 -0.0424 0.0173 0.8264
13.250 1.0823 0.09988 0.09534 -0.0428 0.0174 0.8283
13.750 1.0357 0.11364 0.10954 -0.0472 0.0178 0.8316
14.000 1.0120 0.12203 0.11814 -0.0516 0.0181 0.8332
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Polar data table (+)
Polar graphs
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