S8055 (12%) (s8055-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 200,000 Max Cl/Cd: 62.25 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8055-il-200000-n5.txt Download as CSV file: xf-s8055-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8055 (12%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4776 0.08977 0.08613 -0.0407 1.0000 0.0129
-10.750 -0.4884 0.08296 0.07936 -0.0443 1.0000 0.0128
-10.500 -0.5006 0.07557 0.07202 -0.0486 1.0000 0.0124
-10.250 -0.5414 0.05982 0.05616 -0.0610 1.0000 0.0120
-10.000 -0.5731 0.05301 0.04920 -0.0653 1.0000 0.0119
-9.750 -0.6018 0.04945 0.04552 -0.0640 1.0000 0.0118
-9.500 -0.6121 0.04386 0.03952 -0.0665 0.9757 0.0117
-9.250 -0.6123 0.03884 0.03398 -0.0677 0.9624 0.0117
-9.000 -0.6052 0.03498 0.02963 -0.0677 0.9525 0.0118
-8.750 -0.5931 0.03180 0.02595 -0.0673 0.9450 0.0120
-8.500 -0.5789 0.02934 0.02306 -0.0664 0.9376 0.0123
-8.250 -0.5609 0.02735 0.02069 -0.0656 0.9315 0.0126
-8.000 -0.5416 0.02570 0.01868 -0.0648 0.9262 0.0133
-7.750 -0.5213 0.02462 0.01750 -0.0641 0.9205 0.0138
-7.500 -0.4996 0.02351 0.01622 -0.0634 0.9158 0.0143
-7.250 -0.4775 0.02239 0.01494 -0.0627 0.9115 0.0147
-7.000 -0.4559 0.02131 0.01371 -0.0618 0.9064 0.0150
-6.750 -0.4337 0.02031 0.01256 -0.0609 0.9020 0.0156
-6.500 -0.4113 0.01942 0.01154 -0.0600 0.8983 0.0161
-6.250 -0.3897 0.01861 0.01064 -0.0591 0.8936 0.0167
-6.000 -0.3679 0.01791 0.00990 -0.0582 0.8890 0.0174
-5.750 -0.3452 0.01729 0.00922 -0.0574 0.8851 0.0186
-5.500 -0.3219 0.01674 0.00856 -0.0565 0.8815 0.0201
-5.250 -0.2991 0.01623 0.00802 -0.0558 0.8768 0.0226
-5.000 -0.2756 0.01574 0.00749 -0.0551 0.8724 0.0265
-4.750 -0.2519 0.01521 0.00693 -0.0543 0.8687 0.0326
-4.500 -0.2282 0.01473 0.00646 -0.0536 0.8649 0.0440
-4.250 -0.2050 0.01426 0.00610 -0.0529 0.8601 0.0675
-4.000 -0.1820 0.01373 0.00578 -0.0522 0.8559 0.1096
-3.750 -0.1590 0.01319 0.00548 -0.0515 0.8523 0.1690
-3.500 -0.1363 0.01270 0.00525 -0.0508 0.8480 0.2340
-3.250 -0.1139 0.01224 0.00506 -0.0500 0.8431 0.3054
-3.000 -0.0915 0.01177 0.00486 -0.0491 0.8388 0.3845
-2.750 -0.0693 0.01129 0.00468 -0.0480 0.8353 0.4710
-2.500 -0.0487 0.01090 0.00466 -0.0465 0.8296 0.5607
-2.250 -0.0263 0.01065 0.00469 -0.0451 0.8247 0.6429
-2.000 -0.0014 0.01054 0.00468 -0.0440 0.8208 0.6979
-1.750 0.0235 0.01053 0.00471 -0.0430 0.8157 0.7343
-1.500 0.0487 0.01053 0.00472 -0.0421 0.8103 0.7611
-1.250 0.0749 0.01051 0.00466 -0.0414 0.8060 0.7832
-1.000 0.1007 0.01051 0.00464 -0.0407 0.8009 0.8010
-0.750 0.1262 0.01051 0.00463 -0.0399 0.7945 0.8172
-0.500 0.1527 0.01047 0.00454 -0.0392 0.7893 0.8320
-0.250 0.1782 0.01047 0.00455 -0.0384 0.7821 0.8450
0.000 0.2047 0.01043 0.00449 -0.0377 0.7756 0.8573
0.250 0.2311 0.01040 0.00445 -0.0371 0.7687 0.8689
0.500 0.2571 0.01036 0.00439 -0.0364 0.7602 0.8809
0.750 0.2839 0.01033 0.00434 -0.0359 0.7510 0.8921
1.000 0.3127 0.01026 0.00425 -0.0357 0.7419 0.9018
1.250 0.3400 0.01024 0.00423 -0.0353 0.7302 0.9126
1.500 0.3701 0.01021 0.00419 -0.0355 0.7180 0.9220
1.750 0.4011 0.01018 0.00413 -0.0360 0.7048 0.9301
2.000 0.4324 0.01016 0.00408 -0.0365 0.6899 0.9379
2.250 0.4644 0.01015 0.00401 -0.0372 0.6723 0.9444
2.500 0.4973 0.01016 0.00394 -0.0381 0.6519 0.9501
2.750 0.5276 0.01022 0.00392 -0.0386 0.6293 0.9573
3.250 0.5923 0.01047 0.00396 -0.0405 0.5775 0.9691
3.500 0.6247 0.01066 0.00403 -0.0416 0.5485 0.9748
3.750 0.6561 0.01092 0.00415 -0.0425 0.5156 0.9815
4.000 0.6878 0.01121 0.00429 -0.0437 0.4821 0.9879
4.250 0.7190 0.01155 0.00448 -0.0448 0.4471 0.9950
4.750 0.7594 0.01228 0.00492 -0.0426 0.3822 1.0000
5.000 0.7737 0.01267 0.00517 -0.0404 0.3532 1.0000
5.250 0.7886 0.01309 0.00544 -0.0382 0.3252 1.0000
5.500 0.8048 0.01351 0.00575 -0.0363 0.2998 1.0000
5.750 0.8217 0.01394 0.00607 -0.0345 0.2776 1.0000
6.000 0.8397 0.01435 0.00640 -0.0329 0.2578 1.0000
6.250 0.8580 0.01478 0.00676 -0.0314 0.2403 1.0000
6.500 0.8765 0.01521 0.00714 -0.0300 0.2244 1.0000
6.750 0.8953 0.01564 0.00753 -0.0286 0.2099 1.0000
7.000 0.9140 0.01609 0.00793 -0.0273 0.1964 1.0000
7.250 0.9326 0.01654 0.00837 -0.0260 0.1841 1.0000
7.500 0.9508 0.01702 0.00881 -0.0246 0.1722 1.0000
7.750 0.9686 0.01751 0.00927 -0.0232 0.1612 1.0000
8.000 0.9871 0.01797 0.00974 -0.0219 0.1509 1.0000
8.250 1.0042 0.01846 0.01025 -0.0204 0.1416 1.0000
8.500 1.0193 0.01901 0.01077 -0.0186 0.1327 1.0000
8.750 1.0359 0.01950 0.01130 -0.0170 0.1240 1.0000
9.000 1.0508 0.02009 0.01189 -0.0152 0.1162 1.0000
9.250 1.0663 0.02067 0.01251 -0.0137 0.1081 1.0000
9.500 1.0814 0.02131 0.01317 -0.0121 0.1011 1.0000
9.750 1.0957 0.02200 0.01388 -0.0105 0.0943 1.0000
10.000 1.1104 0.02271 0.01463 -0.0091 0.0885 1.0000
10.250 1.1236 0.02351 0.01545 -0.0075 0.0826 1.0000
10.500 1.1367 0.02435 0.01634 -0.0060 0.0777 1.0000
10.750 1.1498 0.02520 0.01726 -0.0046 0.0731 1.0000
11.000 1.1601 0.02626 0.01832 -0.0030 0.0694 1.0000
11.250 1.1725 0.02721 0.01937 -0.0016 0.0662 1.0000
11.500 1.1841 0.02824 0.02049 -0.0002 0.0630 1.0000
11.750 1.1937 0.02941 0.02173 0.0012 0.0602 1.0000
12.000 1.2009 0.03079 0.02314 0.0027 0.0579 1.0000
12.250 1.2120 0.03194 0.02443 0.0038 0.0556 1.0000
12.500 1.2215 0.03323 0.02583 0.0050 0.0535 1.0000
12.750 1.2294 0.03466 0.02735 0.0061 0.0517 1.0000
13.000 1.2355 0.03626 0.02901 0.0073 0.0502 1.0000
13.250 1.2388 0.03816 0.03095 0.0084 0.0487 1.0000
13.500 1.2466 0.03974 0.03270 0.0093 0.0473 1.0000
13.750 1.2531 0.04148 0.03458 0.0100 0.0458 1.0000
14.000 1.2583 0.04335 0.03658 0.0107 0.0443 1.0000
14.250 1.2624 0.04536 0.03871 0.0112 0.0429 1.0000
14.500 1.2642 0.04765 0.04106 0.0115 0.0414 1.0000
14.750 1.2638 0.05026 0.04373 0.0116 0.0399 1.0000
15.000 1.2667 0.05268 0.04635 0.0116 0.0387 1.0000
15.250 1.2687 0.05528 0.04911 0.0113 0.0367 1.0000
15.500 1.2683 0.05826 0.05221 0.0108 0.0354 1.0000
15.750 1.2660 0.06160 0.05568 0.0099 0.0342 1.0000
16.000 1.2612 0.06542 0.05957 0.0088 0.0333 1.0000
16.250 1.2572 0.06930 0.06360 0.0076 0.0324 1.0000
16.500 1.2534 0.07331 0.06780 0.0061 0.0315 1.0000
16.750 1.2478 0.07775 0.07242 0.0043 0.0307 1.0000
17.000 1.2408 0.08257 0.07740 0.0021 0.0297 1.0000
17.250 1.2324 0.08770 0.08268 -0.0002 0.0292 1.0000
17.500 1.2224 0.09334 0.08846 -0.0031 0.0284 1.0000
17.750 1.2117 0.09919 0.09444 -0.0061 0.0280 1.0000
18.000 1.1996 0.10551 0.10087 -0.0096 0.0273 1.0000
18.250 1.1874 0.11186 0.10729 -0.0131 0.0268 1.0000
18.500 1.1728 0.11901 0.11465 -0.0171 0.0263 1.0000
18.750 1.1582 0.12630 0.12211 -0.0212 0.0259 1.0000
19.000 1.1410 0.13435 0.13033 -0.0260 0.0253 1.0000
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Polar data table (+)
Polar graphs
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