S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 100,000 Max Cl/Cd: 56.59 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7055-il-100000-n5.txt Download as CSV file: xf-s7055-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7055 (10.5%) Flat-Bottomed
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3320 0.09172 0.08700 -0.0409 1.0000 0.0322
-8.500 -0.3348 0.08851 0.08387 -0.0413 1.0000 0.0311
-8.250 -0.3417 0.08545 0.08092 -0.0414 1.0000 0.0303
-8.000 -0.3548 0.08279 0.07839 -0.0406 1.0000 0.0298
-7.750 -0.3764 0.08113 0.07686 -0.0379 1.0000 0.0292
-7.500 -0.3801 0.07562 0.07140 -0.0438 0.9911 0.0281
-7.000 -0.3510 0.05605 0.05137 -0.0662 0.9682 0.0258
-6.500 -0.3129 0.04837 0.04333 -0.0730 0.9528 0.0281
-6.250 -0.2922 0.04456 0.03924 -0.0755 0.9446 0.0295
-6.000 -0.2732 0.03994 0.03417 -0.0772 0.9362 0.0302
-5.750 -0.2513 0.03550 0.02917 -0.0784 0.9290 0.0305
-5.500 -0.2311 0.03209 0.02520 -0.0782 0.9205 0.0312
-5.250 -0.2046 0.02902 0.02153 -0.0786 0.9145 0.0323
-5.000 -0.1811 0.02674 0.01872 -0.0780 0.9065 0.0339
-4.750 -0.1526 0.02494 0.01653 -0.0783 0.9007 0.0372
-4.500 -0.1275 0.02383 0.01524 -0.0780 0.8930 0.0404
-4.250 -0.0983 0.02239 0.01351 -0.0780 0.8870 0.0438
-4.000 -0.0721 0.02127 0.01214 -0.0774 0.8795 0.0484
-3.750 -0.0445 0.02045 0.01130 -0.0774 0.8729 0.0551
-3.500 -0.0191 0.01969 0.01040 -0.0768 0.8651 0.0625
-3.250 0.0080 0.01897 0.00962 -0.0765 0.8584 0.0697
-3.000 0.0322 0.01839 0.00899 -0.0757 0.8500 0.0782
-2.750 0.0595 0.01784 0.00833 -0.0753 0.8434 0.0876
-2.500 0.0830 0.01734 0.00783 -0.0744 0.8344 0.0988
-2.250 0.1102 0.01676 0.00730 -0.0741 0.8282 0.1228
-2.000 0.1328 0.01618 0.00699 -0.0732 0.8188 0.1833
-1.750 0.1573 0.01535 0.00673 -0.0727 0.8118 0.3458
-1.500 0.1778 0.01445 0.00665 -0.0712 0.8033 0.5663
-1.250 0.2464 0.01351 0.00652 -0.0772 0.8000 0.9325
-1.000 0.3151 0.01341 0.00618 -0.0854 0.7926 1.0000
-0.750 0.3383 0.01340 0.00596 -0.0844 0.7842 1.0000
-0.500 0.3604 0.01344 0.00585 -0.0833 0.7742 1.0000
-0.250 0.3830 0.01350 0.00576 -0.0822 0.7644 1.0000
0.000 0.4068 0.01352 0.00563 -0.0813 0.7557 1.0000
0.250 0.4299 0.01358 0.00556 -0.0802 0.7458 1.0000
0.500 0.4530 0.01365 0.00553 -0.0792 0.7357 1.0000
0.750 0.4771 0.01370 0.00546 -0.0784 0.7266 1.0000
1.000 0.5010 0.01377 0.00542 -0.0775 0.7169 1.0000
1.250 0.5244 0.01388 0.00545 -0.0765 0.7065 1.0000
1.500 0.5485 0.01397 0.00546 -0.0757 0.6967 1.0000
1.750 0.5733 0.01404 0.00544 -0.0749 0.6873 1.0000
2.000 0.5967 0.01418 0.00554 -0.0740 0.6761 1.0000
2.250 0.6206 0.01430 0.00561 -0.0731 0.6653 1.0000
2.500 0.6450 0.01442 0.00567 -0.0723 0.6548 1.0000
2.750 0.6699 0.01453 0.00573 -0.0716 0.6445 1.0000
3.000 0.6936 0.01469 0.00587 -0.0708 0.6326 1.0000
3.250 0.7176 0.01485 0.00601 -0.0700 0.6208 1.0000
3.500 0.7417 0.01502 0.00616 -0.0692 0.6092 1.0000
3.750 0.7659 0.01519 0.00634 -0.0684 0.5975 1.0000
4.000 0.7901 0.01537 0.00650 -0.0676 0.5858 1.0000
4.250 0.8143 0.01556 0.00666 -0.0669 0.5739 1.0000
4.500 0.8379 0.01578 0.00689 -0.0660 0.5609 1.0000
4.750 0.8613 0.01600 0.00715 -0.0652 0.5475 1.0000
5.000 0.8847 0.01624 0.00740 -0.0643 0.5339 1.0000
5.250 0.9078 0.01649 0.00768 -0.0634 0.5201 1.0000
5.500 0.9308 0.01676 0.00797 -0.0625 0.5063 1.0000
5.750 0.9535 0.01705 0.00829 -0.0616 0.4922 1.0000
6.000 0.9759 0.01735 0.00866 -0.0606 0.4777 1.0000
6.250 0.9980 0.01767 0.00901 -0.0596 0.4628 1.0000
6.500 1.0196 0.01802 0.00938 -0.0585 0.4475 1.0000
6.750 1.0406 0.01839 0.00979 -0.0574 0.4313 1.0000
7.000 1.0610 0.01879 0.01025 -0.0562 0.4145 1.0000
7.250 1.0809 0.01921 0.01076 -0.0549 0.3973 1.0000
7.500 1.1001 0.01966 0.01125 -0.0535 0.3797 1.0000
7.750 1.1183 0.02016 0.01176 -0.0520 0.3617 1.0000
8.000 1.1356 0.02068 0.01235 -0.0504 0.3421 1.0000
8.250 1.1518 0.02127 0.01296 -0.0487 0.3227 1.0000
8.500 1.1669 0.02190 0.01366 -0.0468 0.3026 1.0000
8.750 1.1806 0.02259 0.01438 -0.0448 0.2820 1.0000
9.000 1.1926 0.02335 0.01515 -0.0427 0.2615 1.0000
9.250 1.2027 0.02418 0.01600 -0.0403 0.2400 1.0000
9.500 1.2095 0.02509 0.01689 -0.0375 0.2191 1.0000
9.750 1.2149 0.02611 0.01790 -0.0346 0.1981 1.0000
10.000 1.2194 0.02728 0.01905 -0.0319 0.1774 1.0000
10.250 1.2231 0.02859 0.02033 -0.0294 0.1575 1.0000
10.500 1.2258 0.03006 0.02183 -0.0270 0.1377 1.0000
10.750 1.2277 0.03169 0.02345 -0.0248 0.1191 1.0000
11.000 1.2270 0.03362 0.02532 -0.0227 0.1017 1.0000
11.250 1.2269 0.03564 0.02732 -0.0210 0.0842 1.0000
11.500 1.2239 0.03801 0.02961 -0.0193 0.0677 1.0000
11.750 1.2197 0.04063 0.03215 -0.0179 0.0539 1.0000
12.000 1.2154 0.04340 0.03490 -0.0168 0.0430 1.0000
12.250 1.2126 0.04616 0.03777 -0.0159 0.0363 1.0000
12.500 1.2055 0.04950 0.04112 -0.0153 0.0310 1.0000
12.750 1.1998 0.05287 0.04465 -0.0149 0.0270 1.0000
13.000 1.1893 0.05694 0.04879 -0.0149 0.0243 1.0000
13.250 1.1815 0.06087 0.05285 -0.0151 0.0228 1.0000
13.500 1.1755 0.06475 0.05692 -0.0155 0.0214 1.0000
13.750 1.1687 0.06890 0.06123 -0.0162 0.0198 1.0000
14.000 1.1626 0.07309 0.06557 -0.0171 0.0190 1.0000
14.250 1.1553 0.07763 0.07023 -0.0184 0.0179 1.0000
14.500 1.1464 0.08252 0.07524 -0.0199 0.0171 1.0000
14.750 1.1390 0.08731 0.08013 -0.0214 0.0163 1.0000
15.000 1.1349 0.09171 0.08472 -0.0227 0.0157 1.0000
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Polar data table (+)
Polar graphs
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