S8055 (12%) (s8055-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 200,000 Max Cl/Cd: 71 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8055-il-200000.txt Download as CSV file: xf-s8055-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3311 0.08670 0.08354 -0.0440 1.0000 0.0592
-9.750 -0.3299 0.08340 0.08027 -0.0442 1.0000 0.0605
-9.500 -0.3364 0.07999 0.07691 -0.0443 1.0000 0.0615
-9.250 -0.3542 0.07788 0.07488 -0.0420 1.0000 0.0624
-9.000 -0.3757 0.07580 0.07287 -0.0394 1.0000 0.0628
-8.750 -0.5809 0.07653 0.07317 -0.0450 0.9996 0.0565
-8.500 -0.5719 0.06927 0.06600 -0.0475 0.9969 0.0578
-8.250 -0.5505 0.06623 0.06301 -0.0491 0.9942 0.0589
-8.000 -0.5374 0.06286 0.05958 -0.0512 0.9892 0.0608
-7.750 -0.5266 0.05821 0.05473 -0.0551 0.9843 0.0637
-7.500 -0.5370 0.05251 0.04834 -0.0573 0.9747 0.0693
-7.250 -0.5113 0.04901 0.04494 -0.0592 0.9726 0.0712
-7.000 -0.5272 0.03304 0.02698 -0.0535 0.9633 0.0301
-6.750 -0.5012 0.03026 0.02372 -0.0540 0.9601 0.0304
-6.500 -0.4726 0.02856 0.02153 -0.0545 0.9572 0.0310
-6.250 -0.4545 0.02644 0.01918 -0.0530 0.9518 0.0308
-6.000 -0.4245 0.02448 0.01696 -0.0536 0.9486 0.0307
-5.750 -0.3905 0.02264 0.01490 -0.0547 0.9464 0.0312
-5.500 -0.3547 0.02080 0.01307 -0.0565 0.9448 0.0326
-5.250 -0.3298 0.01992 0.01217 -0.0561 0.9405 0.0342
-5.000 -0.3051 0.01917 0.01136 -0.0555 0.9355 0.0369
-4.750 -0.2743 0.01820 0.01045 -0.0564 0.9324 0.0431
-4.500 -0.2421 0.01723 0.00949 -0.0574 0.9297 0.0533
-4.250 -0.2266 0.01644 0.00880 -0.0552 0.9234 0.0806
-4.000 -0.2051 0.01536 0.00828 -0.0545 0.9184 0.1721
-3.750 -0.1789 0.01439 0.00796 -0.0548 0.9149 0.3115
-3.500 -0.1639 0.01385 0.00789 -0.0527 0.9086 0.4243
-3.250 -0.1449 0.01327 0.00785 -0.0509 0.9030 0.5497
-3.000 -0.1185 0.01294 0.00795 -0.0499 0.8996 0.6691
-2.750 -0.0987 0.01304 0.00817 -0.0476 0.8935 0.7307
-2.500 -0.0747 0.01314 0.00828 -0.0462 0.8879 0.7721
-2.250 -0.0453 0.01320 0.00832 -0.0455 0.8844 0.8044
-2.000 -0.0239 0.01337 0.00846 -0.0435 0.8784 0.8297
-1.750 -0.0004 0.01347 0.00854 -0.0419 0.8725 0.8505
-1.500 0.0292 0.01350 0.00852 -0.0412 0.8688 0.8690
-1.250 0.0531 0.01363 0.00861 -0.0397 0.8629 0.8858
-1.000 0.0805 0.01368 0.00862 -0.0388 0.8568 0.9007
-0.750 0.1151 0.01362 0.00849 -0.0392 0.8529 0.9137
-0.500 0.1447 0.01370 0.00851 -0.0390 0.8463 0.9266
-0.250 0.1901 0.01368 0.00844 -0.0418 0.8411 0.9337
0.000 0.2301 0.01356 0.00824 -0.0435 0.8370 0.9427
0.250 0.2789 0.01350 0.00814 -0.0474 0.8303 0.9475
0.500 0.3192 0.01332 0.00791 -0.0493 0.8233 0.9554
0.750 0.3648 0.01309 0.00763 -0.0524 0.8165 0.9605
1.000 0.4053 0.01288 0.00738 -0.0547 0.8078 0.9669
1.250 0.4438 0.01266 0.00714 -0.0565 0.7992 0.9734
1.500 0.4849 0.01236 0.00680 -0.0589 0.7902 0.9793
1.750 0.5219 0.01215 0.00659 -0.0607 0.7793 0.9856
2.000 0.5613 0.01182 0.00624 -0.0629 0.7687 0.9912
2.250 0.6000 0.01149 0.00588 -0.0649 0.7573 0.9966
2.500 0.6315 0.01126 0.00567 -0.0658 0.7436 1.0000
2.750 0.6507 0.01111 0.00552 -0.0642 0.7295 1.0000
3.000 0.6699 0.01096 0.00537 -0.0626 0.7143 1.0000
3.250 0.6893 0.01082 0.00520 -0.0609 0.6976 1.0000
3.500 0.7081 0.01072 0.00508 -0.0592 0.6783 1.0000
3.750 0.7263 0.01068 0.00499 -0.0573 0.6566 1.0000
4.000 0.7442 0.01069 0.00491 -0.0553 0.6331 1.0000
4.250 0.7610 0.01078 0.00490 -0.0532 0.6060 1.0000
4.500 0.7767 0.01094 0.00496 -0.0509 0.5758 1.0000
4.750 0.7917 0.01119 0.00505 -0.0484 0.5430 1.0000
5.000 0.8060 0.01150 0.00521 -0.0459 0.5062 1.0000
5.250 0.8198 0.01191 0.00541 -0.0434 0.4678 1.0000
5.500 0.8336 0.01236 0.00569 -0.0409 0.4290 1.0000
5.750 0.8472 0.01288 0.00601 -0.0384 0.3914 1.0000
6.000 0.8612 0.01345 0.00637 -0.0360 0.3573 1.0000
6.250 0.8762 0.01402 0.00677 -0.0339 0.3268 1.0000
6.500 0.8923 0.01458 0.00721 -0.0321 0.2998 1.0000
6.750 0.9086 0.01517 0.00767 -0.0303 0.2772 1.0000
7.000 0.9257 0.01573 0.00815 -0.0286 0.2570 1.0000
7.250 0.9428 0.01630 0.00865 -0.0270 0.2394 1.0000
7.500 0.9600 0.01687 0.00915 -0.0255 0.2235 1.0000
7.750 0.9773 0.01744 0.00968 -0.0239 0.2091 1.0000
8.000 0.9945 0.01801 0.01023 -0.0224 0.1959 1.0000
8.250 1.0111 0.01861 0.01081 -0.0209 0.1835 1.0000
8.500 1.0266 0.01926 0.01141 -0.0191 0.1720 1.0000
8.750 1.0405 0.01993 0.01202 -0.0172 0.1610 1.0000
9.000 1.0554 0.02049 0.01265 -0.0153 0.1502 1.0000
9.250 1.0694 0.02122 0.01339 -0.0135 0.1404 1.0000
9.500 1.0822 0.02209 0.01418 -0.0116 0.1314 1.0000
9.750 1.0967 0.02275 0.01494 -0.0099 0.1226 1.0000
10.000 1.1101 0.02368 0.01586 -0.0083 0.1148 1.0000
10.250 1.1229 0.02452 0.01671 -0.0066 0.1075 1.0000
10.500 1.1366 0.02550 0.01775 -0.0051 0.1008 1.0000
10.750 1.1495 0.02642 0.01869 -0.0036 0.0953 1.0000
11.000 1.1638 0.02764 0.01993 -0.0022 0.0904 1.0000
11.250 1.1771 0.02862 0.02101 -0.0008 0.0858 1.0000
11.500 1.1902 0.02979 0.02214 0.0005 0.0818 1.0000
11.750 1.2054 0.03110 0.02357 0.0016 0.0784 1.0000
12.000 1.2186 0.03228 0.02489 0.0029 0.0754 1.0000
12.250 1.2318 0.03349 0.02616 0.0040 0.0726 1.0000
12.500 1.2490 0.03497 0.02761 0.0047 0.0698 1.0000
12.750 1.2622 0.03665 0.02946 0.0058 0.0676 1.0000
13.000 1.2705 0.03811 0.03113 0.0073 0.0657 1.0000
13.250 1.2791 0.03970 0.03290 0.0086 0.0637 1.0000
13.500 1.2867 0.04112 0.03440 0.0097 0.0616 1.0000
13.750 1.2984 0.04273 0.03598 0.0105 0.0592 1.0000
14.000 1.3002 0.04502 0.03847 0.0117 0.0573 1.0000
14.250 1.2978 0.04692 0.04059 0.0131 0.0556 1.0000
14.500 1.2962 0.04896 0.04281 0.0141 0.0538 1.0000
14.750 1.2968 0.05068 0.04458 0.0147 0.0516 1.0000
15.000 1.3025 0.05257 0.04647 0.0151 0.0498 1.0000
15.250 1.3009 0.05573 0.04977 0.0156 0.0482 1.0000
15.500 1.2921 0.05891 0.05323 0.0157 0.0474 1.0000
15.750 1.2829 0.06244 0.05700 0.0155 0.0463 1.0000
16.000 1.2737 0.06621 0.06098 0.0149 0.0452 1.0000
16.250 1.2652 0.07004 0.06497 0.0138 0.0440 1.0000
16.500 1.2614 0.07341 0.06843 0.0127 0.0426 1.0000
16.750 1.2664 0.07578 0.07073 0.0122 0.0408 1.0000
17.000 1.2499 0.08146 0.07660 0.0100 0.0399 1.0000
17.250 1.2306 0.08793 0.08332 0.0070 0.0396 1.0000
17.500 1.2083 0.09527 0.09092 0.0030 0.0391 1.0000
17.750 1.1834 0.10361 0.09949 -0.0017 0.0390 1.0000
18.000 1.1541 0.11334 0.10946 -0.0077 0.0390 1.0000
18.250 1.1180 0.12521 0.12155 -0.0152 0.0394 1.0000
18.500 1.0728 0.13994 0.13643 -0.0244 0.0402 1.0000
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Polar data table (+)
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