EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 50,000 Max Cl/Cd: 22.2 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stf86361-il-50000.txt Download as CSV file: xf-stf86361-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4863 0.13380 0.12771 -0.0150 1.0019 0.3028
-9.250 -0.5190 0.13429 0.12834 -0.0136 1.0019 0.3163
-9.000 -0.5021 0.13026 0.12429 -0.0115 1.0019 0.3354
-8.750 -0.4884 0.12655 0.12057 -0.0095 1.0019 0.3536
-8.500 -0.4816 0.12349 0.11753 -0.0075 1.0019 0.3720
-8.250 -0.4822 0.12126 0.11533 -0.0052 1.0019 0.3937
-8.000 -0.4926 0.11996 0.11411 -0.0022 1.0019 0.4164
-7.750 -0.4702 0.11586 0.10999 -0.0005 1.0019 0.4419
-7.500 -0.4566 0.11292 0.10704 0.0014 1.0019 0.4663
-7.250 -0.4520 0.11038 0.10453 0.0035 1.0019 0.4873
-7.000 -0.4492 0.10766 0.10183 0.0053 1.0019 0.5032
-6.000 -0.5243 0.08968 0.08472 0.0021 1.0019 0.3648
-5.750 -0.6517 0.07716 0.07186 -0.0171 1.0019 0.3372
-5.500 -0.5704 0.05571 0.04752 -0.0509 1.0019 0.1395
-5.250 -0.5400 0.05165 0.04290 -0.0522 1.0019 0.1249
-5.000 -0.5067 0.04864 0.03903 -0.0536 1.0019 0.1165
-4.750 -0.4793 0.04596 0.03604 -0.0539 1.0019 0.1135
-4.500 -0.4477 0.04404 0.03331 -0.0539 1.0019 0.1070
-4.250 -0.4225 0.04210 0.03123 -0.0531 1.0019 0.1049
-4.000 -0.3979 0.04065 0.02958 -0.0518 1.0019 0.1034
-3.750 -0.3757 0.03962 0.02839 -0.0497 1.0019 0.1036
-3.500 -0.3549 0.03901 0.02761 -0.0474 1.0019 0.1071
-3.250 -0.3369 0.03838 0.02710 -0.0446 1.0019 0.1119
-3.000 -0.3158 0.03795 0.02657 -0.0427 1.0019 0.1159
-2.750 -0.2918 0.03735 0.02598 -0.0422 1.0019 0.1225
-2.500 -0.2612 0.03674 0.02537 -0.0437 1.0019 0.1382
-2.250 -0.2295 0.03559 0.02708 -0.0445 1.0019 0.6113
-2.000 -0.2349 0.03760 0.02897 -0.0339 1.0019 0.7305
-1.750 -0.2497 0.03821 0.02958 -0.0216 1.0019 0.7822
-1.500 -0.2639 0.03815 0.02949 -0.0101 1.0019 0.8254
-1.250 -0.2749 0.03778 0.02903 0.0000 1.0019 0.8682
-1.000 -0.1391 0.04043 0.03079 -0.0135 1.0019 0.9981
-0.750 -0.1328 0.04016 0.03039 -0.0113 1.0019 0.9981
-0.500 -0.1267 0.03990 0.03001 -0.0092 1.0019 0.9981
-0.250 -0.1206 0.03965 0.02961 -0.0071 1.0019 0.9981
0.000 -0.1146 0.03940 0.02926 -0.0049 1.0019 0.9981
0.250 -0.1085 0.03916 0.02894 -0.0029 1.0019 0.9981
0.500 -0.1021 0.03894 0.02864 -0.0009 1.0019 0.9981
0.750 -0.0955 0.03874 0.02837 0.0010 1.0019 0.9981
1.000 -0.0873 0.03862 0.02819 0.0026 1.0019 0.9981
1.250 -0.0762 0.03866 0.02816 0.0035 1.0019 0.9981
1.500 -0.0619 0.03888 0.02828 0.0038 1.0019 0.9981
1.750 -0.0449 0.03926 0.02860 0.0036 1.0019 0.9981
2.000 -0.0258 0.03981 0.02909 0.0029 1.0019 0.9981
2.250 -0.0053 0.04048 0.02972 0.0019 1.0019 0.9981
2.500 0.0164 0.04127 0.03048 0.0006 1.0019 0.9981
2.750 0.0387 0.04216 0.03136 -0.0008 1.0019 0.9981
3.000 0.0614 0.04315 0.03234 -0.0024 1.0019 0.9981
3.250 0.0843 0.04422 0.03342 -0.0041 1.0019 0.9981
3.500 0.1073 0.04538 0.03460 -0.0058 1.0019 0.9981
3.750 0.1301 0.04662 0.03587 -0.0077 1.0019 0.9981
4.000 0.1527 0.04794 0.03724 -0.0095 1.0019 0.9981
4.250 0.1750 0.04935 0.03871 -0.0114 1.0019 0.9981
4.500 0.1970 0.05083 0.04026 -0.0133 1.0019 0.9981
4.750 0.2211 0.05255 0.04211 -0.0158 1.0003 0.9981
5.000 0.2637 0.05565 0.04531 -0.0218 0.9910 0.9981
5.250 0.2984 0.05827 0.04805 -0.0264 0.9800 0.9981
5.500 0.3304 0.06064 0.05057 -0.0305 0.9669 0.9981
5.750 0.3674 0.06357 0.05366 -0.0354 0.9547 0.9981
6.000 0.3888 0.06529 0.05560 -0.0374 0.9407 0.9981
6.250 0.4190 0.06749 0.05799 -0.0409 0.9227 0.9981
6.500 0.4539 0.07014 0.06085 -0.0451 0.9040 0.9981
6.750 0.5360 0.07001 0.06110 -0.0523 0.8248 0.9981
7.000 0.5823 0.07044 0.06184 -0.0558 0.7935 0.9981
7.250 0.6219 0.07080 0.06252 -0.0585 0.7670 0.9981
7.500 0.6565 0.07107 0.06311 -0.0603 0.7409 0.9981
7.750 0.7140 0.07053 0.06308 -0.0641 0.7147 0.9981
8.000 0.7730 0.06859 0.06172 -0.0666 0.6848 0.9981
8.250 0.8956 0.04034 0.03193 -0.0440 0.2281 0.9981
8.500 0.8851 0.04412 0.03466 -0.0403 0.1567 0.9981
8.750 0.8991 0.04634 0.03650 -0.0385 0.1266 0.9981
9.000 0.9946 0.04683 0.03665 -0.0434 0.0972 0.9981
9.250 1.1778 0.05396 0.04400 -0.0623 0.0826 0.9981
9.500 1.2036 0.05800 0.04875 -0.0619 0.0817 0.9981
9.750 1.2335 0.06314 0.05447 -0.0624 0.0829 0.9981
10.000 1.2215 0.06610 0.05816 -0.0569 0.0851 0.9981
10.250 1.2176 0.07016 0.06273 -0.0534 0.0875 0.9981
10.500 1.2386 0.07626 0.06911 -0.0536 0.0905 0.9981
10.750 1.1995 0.07814 0.07154 -0.0462 0.0923 0.9981
11.000 1.1720 0.08181 0.07562 -0.0415 0.0945 0.9981
11.250 1.1565 0.08632 0.08040 -0.0388 0.0970 0.9981
11.500 1.1432 0.09103 0.08537 -0.0367 0.1000 0.9981
11.750 1.1035 0.09511 0.08974 -0.0337 0.1010 0.9981
12.000 1.0662 0.10021 0.09506 -0.0324 0.1022 0.9981
12.250 1.0308 0.10619 0.10122 -0.0329 0.1035 0.9981
12.500 1.0009 0.11307 0.10821 -0.0350 0.1054 0.9981
12.750 0.9831 0.12047 0.11570 -0.0379 0.1095 0.9981
13.000 0.9276 0.13394 0.12915 -0.0484 0.1133 0.9981
13.250 0.9078 0.14673 0.14186 -0.0573 0.1267 0.9981
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