S8025 (8%) (s8025-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 500,000 Max Cl/Cd: 65.57 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8025-il-500000.txt Download as CSV file: xf-s8025-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S8025 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6657 0.10433 0.10210 0.0200 1.0000 0.0191
-10.000 -0.6685 0.09821 0.09600 0.0168 1.0000 0.0191
-7.750 -0.7769 0.02829 0.02367 -0.0112 1.0000 0.0095
-7.500 -0.7616 0.02436 0.01944 -0.0102 1.0000 0.0089
-7.250 -0.7427 0.02148 0.01619 -0.0092 1.0000 0.0085
-7.000 -0.7213 0.01933 0.01376 -0.0082 1.0000 0.0084
-6.750 -0.6986 0.01761 0.01182 -0.0073 1.0000 0.0083
-6.500 -0.6752 0.01623 0.01028 -0.0065 1.0000 0.0084
-6.250 -0.6514 0.01508 0.00899 -0.0057 1.0000 0.0087
-6.000 -0.6269 0.01414 0.00792 -0.0050 1.0000 0.0091
-5.750 -0.6029 0.01310 0.00677 -0.0042 1.0000 0.0097
-5.500 -0.5787 0.01213 0.00573 -0.0035 1.0000 0.0108
-5.250 -0.5530 0.01155 0.00509 -0.0030 1.0000 0.0123
-5.000 -0.5276 0.01088 0.00436 -0.0024 1.0000 0.0157
-4.750 -0.5034 0.00988 0.00357 -0.0017 1.0000 0.0520
-4.500 -0.4776 0.00946 0.00325 -0.0013 1.0000 0.0768
-4.250 -0.4516 0.00911 0.00299 -0.0009 1.0000 0.0999
-4.000 -0.4261 0.00869 0.00275 -0.0005 1.0000 0.1359
-3.750 -0.4004 0.00832 0.00253 -0.0001 1.0000 0.1721
-3.500 -0.3748 0.00798 0.00232 0.0004 1.0000 0.2103
-3.250 -0.3492 0.00764 0.00214 0.0009 1.0000 0.2500
-3.000 -0.3236 0.00735 0.00198 0.0013 1.0000 0.2887
-2.750 -0.2982 0.00706 0.00184 0.0019 1.0000 0.3313
-2.500 -0.2731 0.00677 0.00172 0.0025 1.0000 0.3807
-2.250 -0.2482 0.00649 0.00162 0.0031 1.0000 0.4290
-2.000 -0.2234 0.00624 0.00155 0.0037 1.0000 0.4781
-1.750 -0.1953 0.00597 0.00151 0.0037 0.9970 0.5400
-1.500 -0.1544 0.00571 0.00148 0.0009 0.9762 0.6042
-1.250 -0.1096 0.00553 0.00144 -0.0025 0.9372 0.6550
-1.000 -0.0784 0.00547 0.00138 -0.0026 0.8724 0.6994
-0.750 -0.0555 0.00550 0.00134 -0.0009 0.8105 0.7432
-0.500 -0.0323 0.00552 0.00132 0.0005 0.7594 0.7877
-0.250 -0.0088 0.00552 0.00132 0.0019 0.7177 0.8341
0.000 0.0151 0.00554 0.00132 0.0033 0.6795 0.8814
0.250 0.0428 0.00560 0.00133 0.0039 0.6420 0.9251
0.500 0.0801 0.00574 0.00134 0.0022 0.6029 0.9571
0.750 0.1217 0.00591 0.00133 -0.0006 0.5592 0.9788
1.250 0.1969 0.00624 0.00133 -0.0047 0.4848 1.0000
1.500 0.2216 0.00639 0.00135 -0.0041 0.4554 1.0000
1.750 0.2467 0.00655 0.00139 -0.0034 0.4271 1.0000
2.000 0.2720 0.00670 0.00144 -0.0029 0.4019 1.0000
2.250 0.2975 0.00687 0.00150 -0.0023 0.3774 1.0000
2.750 0.3489 0.00724 0.00168 -0.0013 0.3284 1.0000
3.000 0.3748 0.00743 0.00178 -0.0008 0.3045 1.0000
3.250 0.4008 0.00764 0.00190 -0.0004 0.2833 1.0000
3.500 0.4270 0.00783 0.00203 0.0000 0.2638 1.0000
3.750 0.4533 0.00805 0.00218 0.0004 0.2433 1.0000
4.000 0.4795 0.00828 0.00234 0.0007 0.2247 1.0000
4.250 0.5060 0.00850 0.00252 0.0011 0.2076 1.0000
4.500 0.5324 0.00874 0.00272 0.0014 0.1908 1.0000
4.750 0.5587 0.00900 0.00293 0.0017 0.1732 1.0000
5.000 0.5850 0.00930 0.00315 0.0020 0.1559 1.0000
5.250 0.6113 0.00958 0.00340 0.0023 0.1399 1.0000
5.500 0.6376 0.00987 0.00366 0.0026 0.1248 1.0000
5.750 0.6639 0.01020 0.00396 0.0029 0.1113 1.0000
6.000 0.6900 0.01055 0.00428 0.0032 0.0982 1.0000
6.250 0.7160 0.01092 0.00464 0.0035 0.0857 1.0000
6.500 0.7417 0.01135 0.00504 0.0039 0.0744 1.0000
6.750 0.7675 0.01177 0.00545 0.0042 0.0649 1.0000
7.000 0.7933 0.01221 0.00593 0.0046 0.0565 1.0000
7.250 0.8182 0.01283 0.00656 0.0050 0.0487 1.0000
7.500 0.8435 0.01334 0.00711 0.0054 0.0426 1.0000
7.750 0.8677 0.01410 0.00794 0.0059 0.0383 1.0000
8.000 0.8931 0.01454 0.00844 0.0063 0.0350 1.0000
8.250 0.9171 0.01526 0.00918 0.0067 0.0309 1.0000
8.500 0.9412 0.01592 0.00993 0.0072 0.0286 1.0000
8.750 0.9659 0.01645 0.01056 0.0076 0.0265 1.0000
9.000 0.9901 0.01704 0.01123 0.0080 0.0244 1.0000
9.250 1.0089 0.01866 0.01296 0.0088 0.0215 1.0000
9.500 1.0343 0.01895 0.01336 0.0091 0.0201 1.0000
9.750 1.0587 0.01939 0.01386 0.0094 0.0177 1.0000
10.000 1.0769 0.02090 0.01547 0.0102 0.0149 1.0000
10.250 1.1002 0.02148 0.01617 0.0106 0.0131 1.0000
10.500 1.1212 0.02238 0.01713 0.0112 0.0116 1.0000
10.750 1.1325 0.02473 0.01970 0.0124 0.0104 1.0000
11.000 1.1507 0.02592 0.02107 0.0131 0.0097 1.0000
11.250 1.1666 0.02729 0.02261 0.0139 0.0090 1.0000
11.500 1.1835 0.02837 0.02379 0.0145 0.0084 1.0000
11.750 1.1967 0.02977 0.02528 0.0153 0.0078 1.0000
12.000 1.1966 0.03243 0.02812 0.0166 0.0074 1.0000
12.500 1.1817 0.03768 0.03374 0.0193 0.0070 1.0000
12.750 1.1689 0.04194 0.03819 0.0171 0.0070 1.0000
13.000 1.1557 0.04770 0.04415 0.0128 0.0069 1.0000
13.250 1.1461 0.05350 0.05010 0.0083 0.0069 1.0000
13.500 1.1235 0.06171 0.05849 0.0026 0.0069 1.0000
13.750 1.1080 0.06867 0.06557 -0.0020 0.0070 1.0000
14.250 1.0638 0.08514 0.08228 -0.0121 0.0071 1.0000
14.500 1.0464 0.09272 0.08996 -0.0165 0.0073 1.0000
14.750 1.0186 0.10283 0.10018 -0.0225 0.0072 1.0000
15.000 1.0133 0.10881 0.10625 -0.0258 0.0075 1.0000
15.250 0.9930 0.11826 0.11579 -0.0312 0.0074 1.0000
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Polar data table (+)
Polar graphs
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