S8055 (12%) (s8055-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 100,000 Max Cl/Cd: 48.31 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8055-il-100000-n5.txt Download as CSV file: xf-s8055-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4493 0.10006 0.09489 -0.0394 1.0000 0.0251
-10.750 -0.4493 0.09583 0.09070 -0.0412 1.0000 0.0249
-10.500 -0.4508 0.09134 0.08627 -0.0432 1.0000 0.0246
-10.250 -0.4549 0.08625 0.08123 -0.0458 1.0000 0.0243
-10.000 -0.4639 0.07974 0.07478 -0.0496 1.0000 0.0240
-9.750 -0.4821 0.07055 0.06563 -0.0564 1.0000 0.0234
-9.500 -0.5064 0.06405 0.05909 -0.0609 1.0000 0.0230
-9.250 -0.5349 0.06013 0.05513 -0.0607 1.0000 0.0228
-9.000 -0.5668 0.05861 0.05361 -0.0557 1.0000 0.0226
-8.750 -0.5979 0.05705 0.05199 -0.0500 1.0000 0.0225
-8.500 -0.6030 0.05154 0.04608 -0.0519 0.9900 0.0223
-8.250 -0.5984 0.04659 0.04064 -0.0533 0.9818 0.0220
-8.000 -0.5891 0.04236 0.03589 -0.0537 0.9746 0.0221
-7.750 -0.5746 0.03884 0.03187 -0.0539 0.9688 0.0221
-7.500 -0.5569 0.03592 0.02848 -0.0538 0.9631 0.0224
-7.250 -0.5327 0.03325 0.02535 -0.0544 0.9594 0.0228
-7.000 -0.5105 0.03109 0.02282 -0.0541 0.9547 0.0233
-6.750 -0.4864 0.02915 0.02053 -0.0539 0.9501 0.0241
-6.500 -0.4578 0.02747 0.01850 -0.0543 0.9467 0.0253
-6.250 -0.4285 0.02626 0.01727 -0.0554 0.9439 0.0272
-6.000 -0.4070 0.02531 0.01618 -0.0545 0.9383 0.0292
-5.750 -0.3813 0.02412 0.01483 -0.0543 0.9340 0.0313
-5.500 -0.3538 0.02305 0.01376 -0.0547 0.9306 0.0337
-5.250 -0.3284 0.02222 0.01278 -0.0544 0.9264 0.0375
-5.000 -0.3080 0.02150 0.01207 -0.0534 0.9206 0.0433
-4.750 -0.2816 0.02070 0.01124 -0.0533 0.9165 0.0548
-4.500 -0.2533 0.01982 0.01047 -0.0537 0.9133 0.0768
-4.250 -0.2368 0.01916 0.01001 -0.0519 0.9065 0.1122
-4.000 -0.2130 0.01838 0.00958 -0.0516 0.9019 0.1814
-3.750 -0.1867 0.01759 0.00922 -0.0517 0.8984 0.2776
-3.500 -0.1712 0.01707 0.00907 -0.0497 0.8916 0.3670
-3.250 -0.1502 0.01647 0.00893 -0.0484 0.8866 0.4769
-3.000 -0.1252 0.01604 0.00897 -0.0472 0.8831 0.5944
-2.750 -0.1066 0.01605 0.00919 -0.0447 0.8766 0.6751
-2.500 -0.0820 0.01612 0.00927 -0.0433 0.8716 0.7306
-2.250 -0.0532 0.01617 0.00927 -0.0426 0.8678 0.7705
-2.000 -0.0328 0.01631 0.00935 -0.0407 0.8611 0.8004
-1.750 -0.0054 0.01640 0.00937 -0.0398 0.8559 0.8248
-1.500 0.0250 0.01642 0.00929 -0.0396 0.8520 0.8473
-1.250 0.0502 0.01655 0.00936 -0.0386 0.8453 0.8658
-1.000 0.0820 0.01660 0.00933 -0.0388 0.8400 0.8824
-0.750 0.1186 0.01659 0.00923 -0.0399 0.8364 0.8972
-0.500 0.1486 0.01669 0.00927 -0.0401 0.8293 0.9113
-0.250 0.1886 0.01669 0.00919 -0.0421 0.8240 0.9223
0.000 0.2311 0.01658 0.00900 -0.0445 0.8200 0.9314
0.250 0.2631 0.01664 0.00903 -0.0454 0.8111 0.9426
0.500 0.3080 0.01648 0.00881 -0.0484 0.8056 0.9489
0.750 0.3430 0.01645 0.00875 -0.0498 0.7968 0.9579
1.000 0.3848 0.01622 0.00849 -0.0523 0.7896 0.9636
1.250 0.4180 0.01613 0.00839 -0.0534 0.7787 0.9720
1.500 0.4560 0.01589 0.00813 -0.0552 0.7688 0.9781
1.750 0.4908 0.01567 0.00789 -0.0565 0.7579 0.9850
2.000 0.5253 0.01549 0.00774 -0.0579 0.7442 0.9917
2.250 0.5598 0.01530 0.00756 -0.0592 0.7298 0.9984
2.500 0.5811 0.01519 0.00745 -0.0580 0.7146 1.0000
2.750 0.5982 0.01509 0.00736 -0.0559 0.6987 1.0000
3.000 0.6160 0.01498 0.00723 -0.0539 0.6819 1.0000
3.250 0.6332 0.01492 0.00714 -0.0517 0.6629 1.0000
3.500 0.6509 0.01488 0.00707 -0.0497 0.6423 1.0000
3.750 0.6703 0.01485 0.00697 -0.0478 0.6203 1.0000
4.000 0.6886 0.01491 0.00697 -0.0458 0.5955 1.0000
4.250 0.7076 0.01502 0.00697 -0.0440 0.5692 1.0000
4.500 0.7262 0.01520 0.00702 -0.0421 0.5407 1.0000
4.750 0.7442 0.01545 0.00716 -0.0402 0.5102 1.0000
5.000 0.7618 0.01577 0.00734 -0.0382 0.4790 1.0000
5.250 0.7790 0.01615 0.00758 -0.0363 0.4464 1.0000
5.500 0.7959 0.01659 0.00787 -0.0344 0.4141 1.0000
5.750 0.8125 0.01708 0.00822 -0.0325 0.3827 1.0000
6.000 0.8290 0.01762 0.00861 -0.0306 0.3533 1.0000
6.500 0.8622 0.01876 0.00953 -0.0272 0.3014 1.0000
6.750 0.8787 0.01937 0.01003 -0.0255 0.2800 1.0000
7.000 0.8960 0.01996 0.01056 -0.0240 0.2606 1.0000
7.250 0.9131 0.02057 0.01113 -0.0225 0.2436 1.0000
7.500 0.9301 0.02119 0.01173 -0.0210 0.2279 1.0000
7.750 0.9468 0.02184 0.01235 -0.0195 0.2140 1.0000
8.000 0.9631 0.02250 0.01299 -0.0180 0.2009 1.0000
8.250 0.9786 0.02321 0.01366 -0.0164 0.1889 1.0000
8.500 0.9941 0.02387 0.01438 -0.0148 0.1772 1.0000
8.750 1.0087 0.02457 0.01511 -0.0130 0.1659 1.0000
9.000 1.0224 0.02532 0.01587 -0.0113 0.1563 1.0000
9.250 1.0350 0.02614 0.01669 -0.0094 0.1470 1.0000
9.500 1.0494 0.02694 0.01758 -0.0079 0.1375 1.0000
9.750 1.0616 0.02786 0.01851 -0.0062 0.1296 1.0000
10.000 1.0746 0.02877 0.01950 -0.0047 0.1215 1.0000
10.250 1.0867 0.02978 0.02056 -0.0031 0.1144 1.0000
10.500 1.0983 0.03082 0.02167 -0.0016 0.1078 1.0000
10.750 1.1096 0.03196 0.02287 -0.0002 0.1020 1.0000
11.000 1.1208 0.03310 0.02412 0.0012 0.0962 1.0000
11.250 1.1293 0.03442 0.02542 0.0027 0.0920 1.0000
11.500 1.1412 0.03571 0.02689 0.0039 0.0873 1.0000
11.750 1.1504 0.03707 0.02835 0.0052 0.0835 1.0000
12.250 1.1676 0.04016 0.03165 0.0076 0.0767 1.0000
12.500 1.1755 0.04178 0.03341 0.0087 0.0736 1.0000
12.750 1.1823 0.04348 0.03520 0.0097 0.0711 1.0000
13.000 1.1895 0.04529 0.03702 0.0107 0.0691 1.0000
13.250 1.1957 0.04733 0.03929 0.0116 0.0669 1.0000
13.500 1.1997 0.04950 0.04169 0.0124 0.0646 1.0000
13.750 1.2028 0.05176 0.04411 0.0131 0.0626 1.0000
14.000 1.2049 0.05406 0.04655 0.0136 0.0608 1.0000
14.250 1.2081 0.05641 0.04898 0.0140 0.0594 1.0000
14.500 1.2117 0.05893 0.05156 0.0143 0.0580 1.0000
14.750 1.2054 0.06244 0.05538 0.0142 0.0568 1.0000
15.000 1.1972 0.06631 0.05954 0.0138 0.0556 1.0000
15.250 1.1876 0.07053 0.06400 0.0129 0.0545 1.0000
15.500 1.1761 0.07516 0.06886 0.0115 0.0535 1.0000
15.750 1.1634 0.08022 0.07413 0.0096 0.0526 1.0000
16.000 1.1491 0.08585 0.07995 0.0072 0.0518 1.0000
16.250 1.1327 0.09213 0.08642 0.0041 0.0512 1.0000
16.500 1.1107 0.09985 0.09434 -0.0001 0.0508 1.0000
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Polar data table (+)
Polar graphs
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