S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 100,000 Max Cl/Cd: 46.52 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8065-il-100000-n5.txt Download as CSV file: xf-s8065-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8065 (11% version of S8064)
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5385 0.08837 0.08342 -0.0403 1.0000 0.0187
-10.500 -0.5510 0.07986 0.07495 -0.0455 1.0000 0.0181
-10.250 -0.5781 0.06897 0.06401 -0.0537 1.0000 0.0171
-10.000 -0.6026 0.06257 0.05751 -0.0578 1.0000 0.0170
-9.750 -0.6318 0.05734 0.05214 -0.0586 1.0000 0.0165
-9.500 -0.6572 0.05414 0.04880 -0.0558 1.0000 0.0163
-9.250 -0.6808 0.05156 0.04605 -0.0513 1.0000 0.0162
-9.000 -0.7017 0.04909 0.04337 -0.0463 1.0000 0.0161
-8.750 -0.7166 0.04683 0.04087 -0.0416 1.0000 0.0160
-8.500 -0.7246 0.04490 0.03875 -0.0375 1.0000 0.0163
-8.250 -0.7286 0.04296 0.03660 -0.0339 1.0000 0.0167
-8.000 -0.7298 0.04086 0.03419 -0.0304 1.0000 0.0171
-7.750 -0.7261 0.03867 0.03169 -0.0276 0.9996 0.0178
-7.500 -0.7070 0.03578 0.02830 -0.0276 0.9956 0.0189
-7.250 -0.6860 0.03305 0.02505 -0.0274 0.9920 0.0198
-7.000 -0.6627 0.03063 0.02218 -0.0271 0.9885 0.0204
-6.750 -0.6374 0.02843 0.01967 -0.0272 0.9856 0.0211
-6.500 -0.6122 0.02663 0.01775 -0.0275 0.9828 0.0225
-6.250 -0.5888 0.02529 0.01625 -0.0272 0.9790 0.0241
-6.000 -0.5632 0.02403 0.01480 -0.0272 0.9755 0.0270
-5.750 -0.5361 0.02292 0.01363 -0.0277 0.9724 0.0328
-5.500 -0.5120 0.02184 0.01246 -0.0275 0.9688 0.0405
-5.250 -0.4884 0.02099 0.01163 -0.0272 0.9644 0.0568
-5.000 -0.4619 0.02016 0.01085 -0.0276 0.9609 0.0815
-4.750 -0.4325 0.01937 0.01012 -0.0284 0.9580 0.1127
-4.500 -0.4114 0.01867 0.00958 -0.0277 0.9531 0.1509
-4.250 -0.3872 0.01789 0.00909 -0.0276 0.9489 0.2167
-4.000 -0.3616 0.01699 0.00871 -0.0280 0.9455 0.3270
-3.750 -0.3405 0.01631 0.00851 -0.0270 0.9411 0.4487
-3.500 -0.3196 0.01592 0.00846 -0.0256 0.9360 0.5472
-3.250 -0.2918 0.01576 0.00854 -0.0252 0.9325 0.6258
-3.000 -0.2599 0.01580 0.00865 -0.0254 0.9299 0.6870
-2.750 -0.2409 0.01588 0.00870 -0.0233 0.9235 0.7262
-2.500 -0.2121 0.01599 0.00875 -0.0231 0.9194 0.7601
-2.250 -0.1795 0.01610 0.00880 -0.0235 0.9165 0.7894
-2.000 -0.1572 0.01622 0.00886 -0.0220 0.9107 0.8143
-1.750 -0.1287 0.01634 0.00892 -0.0217 0.9061 0.8372
-1.500 -0.0946 0.01643 0.00894 -0.0225 0.9029 0.8559
-1.250 -0.0649 0.01653 0.00895 -0.0226 0.8982 0.8711
-1.000 -0.0350 0.01660 0.00896 -0.0230 0.8929 0.8846
-0.750 0.0039 0.01666 0.00895 -0.0251 0.8897 0.8950
-0.500 0.0455 0.01669 0.00892 -0.0277 0.8872 0.9040
-0.250 0.0730 0.01677 0.00898 -0.0278 0.8800 0.9153
0.000 0.1128 0.01680 0.00898 -0.0303 0.8761 0.9233
0.250 0.1545 0.01678 0.00893 -0.0330 0.8732 0.9304
0.500 0.1862 0.01687 0.00902 -0.0341 0.8659 0.9395
0.750 0.2270 0.01684 0.00901 -0.0368 0.8615 0.9456
1.000 0.2708 0.01675 0.00895 -0.0399 0.8583 0.9507
1.250 0.3030 0.01681 0.00905 -0.0412 0.8496 0.9590
1.500 0.3454 0.01668 0.00896 -0.0441 0.8451 0.9639
1.750 0.3783 0.01666 0.00903 -0.0454 0.8361 0.9721
2.000 0.4196 0.01644 0.00888 -0.0479 0.8302 0.9771
2.250 0.4529 0.01634 0.00887 -0.0492 0.8194 0.9850
2.500 0.4899 0.01611 0.00876 -0.0510 0.8085 0.9915
2.750 0.5267 0.01580 0.00856 -0.0526 0.7959 0.9981
3.000 0.5479 0.01555 0.00839 -0.0511 0.7799 1.0000
3.250 0.5646 0.01528 0.00821 -0.0486 0.7622 1.0000
3.500 0.5824 0.01500 0.00798 -0.0462 0.7419 1.0000
3.750 0.6018 0.01470 0.00770 -0.0440 0.7174 1.0000
4.000 0.6220 0.01446 0.00745 -0.0419 0.6875 1.0000
4.250 0.6412 0.01435 0.00733 -0.0397 0.6496 1.0000
4.500 0.6611 0.01436 0.00721 -0.0375 0.6020 1.0000
4.750 0.6783 0.01458 0.00721 -0.0351 0.5405 1.0000
5.000 0.6919 0.01506 0.00734 -0.0322 0.4622 1.0000
5.250 0.7012 0.01585 0.00765 -0.0289 0.3722 1.0000
5.500 0.7097 0.01681 0.00813 -0.0257 0.2875 1.0000
5.750 0.7200 0.01780 0.00876 -0.0230 0.2163 1.0000
6.000 0.7324 0.01876 0.00941 -0.0207 0.1643 1.0000
6.250 0.7464 0.01966 0.01012 -0.0187 0.1307 1.0000
6.500 0.7615 0.02051 0.01088 -0.0168 0.1083 1.0000
6.750 0.7768 0.02137 0.01172 -0.0149 0.0942 1.0000
7.000 0.7919 0.02228 0.01264 -0.0130 0.0832 1.0000
7.250 0.8067 0.02323 0.01356 -0.0112 0.0738 1.0000
7.500 0.8231 0.02416 0.01460 -0.0095 0.0663 1.0000
7.750 0.8383 0.02524 0.01570 -0.0078 0.0594 1.0000
8.000 0.8548 0.02618 0.01671 -0.0063 0.0521 1.0000
8.250 0.8712 0.02728 0.01791 -0.0048 0.0455 1.0000
8.500 0.8862 0.02832 0.01901 -0.0033 0.0400 1.0000
8.750 0.9035 0.02986 0.02070 -0.0019 0.0360 1.0000
9.000 0.9209 0.03131 0.02230 -0.0006 0.0325 1.0000
9.250 0.9342 0.03272 0.02371 0.0009 0.0297 1.0000
9.500 0.9516 0.03452 0.02581 0.0021 0.0271 1.0000
9.750 0.9681 0.03661 0.02818 0.0034 0.0254 1.0000
10.000 0.9808 0.03873 0.03054 0.0050 0.0242 1.0000
10.250 0.9900 0.04079 0.03283 0.0069 0.0232 1.0000
10.500 0.9966 0.04300 0.03530 0.0090 0.0226 1.0000
10.750 0.9996 0.04543 0.03791 0.0112 0.0220 1.0000
11.000 0.9987 0.04838 0.04109 0.0134 0.0216 1.0000
11.250 0.9914 0.05148 0.04451 0.0160 0.0213 1.0000
11.500 0.9805 0.05464 0.04802 0.0183 0.0210 1.0000
11.750 0.9672 0.05818 0.05186 0.0201 0.0209 1.0000
12.000 0.9493 0.06217 0.05616 0.0211 0.0206 1.0000
12.250 0.9303 0.06668 0.06093 0.0212 0.0205 1.0000
12.500 0.9099 0.07183 0.06631 0.0201 0.0205 1.0000
12.750 0.8896 0.07762 0.07227 0.0178 0.0207 1.0000
13.000 0.8695 0.08407 0.07887 0.0144 0.0209 1.0000
13.250 0.8473 0.09188 0.08681 0.0096 0.0211 1.0000
13.500 0.8250 0.10096 0.09598 0.0036 0.0214 1.0000
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Polar data table (+)
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