S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 100,000 Max Cl/Cd: 54.29 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7055-il-100000.txt Download as CSV file: xf-s7055-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3315 0.10372 0.09896 -0.0376 1.0000 0.0804
-9.000 -0.3236 0.10063 0.09590 -0.0370 1.0000 0.0835
-8.750 -0.3227 0.09789 0.09322 -0.0376 1.0000 0.0866
-8.500 -0.3287 0.09553 0.09096 -0.0389 1.0000 0.0893
-8.250 -0.3495 0.09424 0.08984 -0.0406 1.0000 0.0909
-8.000 -0.3723 0.09331 0.08907 -0.0393 1.0000 0.0911
-7.750 -0.3986 0.09256 0.08844 -0.0369 1.0000 0.0913
-7.500 -0.4239 0.09138 0.08737 -0.0363 1.0000 0.0915
-7.250 -0.4464 0.08988 0.08586 -0.0364 1.0000 0.0917
-7.000 -0.4202 0.08507 0.08116 -0.0275 1.0000 0.0948
-6.750 -0.4282 0.08325 0.07940 -0.0249 1.0000 0.0966
-6.500 -0.4008 0.07384 0.07029 -0.0314 0.9937 0.1055
-6.250 -0.3789 0.06886 0.06538 -0.0283 0.9900 0.1096
-6.000 -0.3709 0.06307 0.05938 -0.0405 0.9804 0.1197
-5.750 -0.4367 0.07105 0.06720 -0.0299 0.9945 0.1102
-5.500 -0.4097 0.06557 0.06148 -0.0390 0.9860 0.1222
-5.250 -0.3838 0.06150 0.05723 -0.0440 0.9786 0.1362
-5.000 -0.3553 0.05762 0.05322 -0.0480 0.9717 0.1508
-4.750 -0.3309 0.05419 0.04968 -0.0505 0.9640 0.1655
-4.500 -0.3010 0.05082 0.04624 -0.0529 0.9577 0.1819
-4.250 -0.2592 0.03926 0.03306 -0.0590 0.9503 0.0940
-4.000 -0.2238 0.03504 0.02829 -0.0607 0.9445 0.0842
-3.750 -0.1896 0.03208 0.02422 -0.0609 0.9374 0.0780
-3.500 -0.1549 0.02907 0.02076 -0.0622 0.9312 0.0788
-3.250 -0.1189 0.02744 0.01901 -0.0639 0.9250 0.0871
-3.000 -0.0846 0.02586 0.01700 -0.0646 0.9175 0.0931
-2.750 -0.0387 0.02451 0.01548 -0.0678 0.9133 0.1072
-2.500 -0.0133 0.02380 0.01473 -0.0673 0.9035 0.1194
-2.250 0.0325 0.02251 0.01353 -0.0704 0.8994 0.1362
-2.000 0.0557 0.02191 0.01309 -0.0696 0.8894 0.1581
-1.750 0.1947 0.01771 0.01179 -0.0889 0.9002 1.0000
-1.500 0.2200 0.01783 0.01161 -0.0886 0.8892 1.0000
-1.250 0.2535 0.01785 0.01137 -0.0897 0.8806 1.0000
-1.000 0.2890 0.01780 0.01110 -0.0910 0.8725 1.0000
-0.750 0.3127 0.01794 0.01106 -0.0901 0.8616 1.0000
-0.500 0.3476 0.01786 0.01081 -0.0911 0.8543 1.0000
-0.250 0.3730 0.01793 0.01074 -0.0904 0.8440 1.0000
0.000 0.3952 0.01809 0.01078 -0.0892 0.8331 1.0000
0.250 0.4259 0.01802 0.01057 -0.0893 0.8253 1.0000
0.500 0.4503 0.01808 0.01054 -0.0883 0.8151 1.0000
0.750 0.4718 0.01825 0.01062 -0.0869 0.8042 1.0000
1.000 0.4988 0.01823 0.01051 -0.0862 0.7954 1.0000
1.250 0.5251 0.01820 0.01041 -0.0854 0.7861 1.0000
1.500 0.5467 0.01836 0.01052 -0.0840 0.7749 1.0000
1.750 0.5718 0.01839 0.01049 -0.0831 0.7652 1.0000
2.000 0.6004 0.01823 0.01027 -0.0825 0.7568 1.0000
2.250 0.6224 0.01838 0.01039 -0.0811 0.7451 1.0000
2.500 0.6463 0.01846 0.01044 -0.0800 0.7343 1.0000
2.750 0.6745 0.01832 0.01027 -0.0794 0.7254 1.0000
3.000 0.6998 0.01832 0.01024 -0.0784 0.7147 1.0000
3.250 0.7231 0.01845 0.01037 -0.0773 0.7027 1.0000
3.500 0.7475 0.01853 0.01045 -0.0763 0.6912 1.0000
3.750 0.7736 0.01854 0.01046 -0.0755 0.6803 1.0000
4.000 0.8025 0.01841 0.01029 -0.0749 0.6704 1.0000
4.250 0.8261 0.01855 0.01045 -0.0739 0.6574 1.0000
4.500 0.8502 0.01867 0.01058 -0.0728 0.6443 1.0000
4.750 0.8746 0.01879 0.01074 -0.0719 0.6311 1.0000
5.000 0.8992 0.01891 0.01088 -0.0709 0.6178 1.0000
5.250 0.9238 0.01905 0.01104 -0.0700 0.6042 1.0000
5.500 0.9484 0.01919 0.01121 -0.0690 0.5902 1.0000
5.750 0.9728 0.01935 0.01143 -0.0681 0.5759 1.0000
6.000 0.9971 0.01952 0.01162 -0.0671 0.5611 1.0000
6.250 1.0213 0.01969 0.01182 -0.0661 0.5458 1.0000
6.500 1.0454 0.01987 0.01201 -0.0652 0.5300 1.0000
6.750 1.0698 0.02006 0.01223 -0.0642 0.5138 1.0000
7.000 1.0910 0.02037 0.01261 -0.0628 0.4961 1.0000
7.250 1.1120 0.02067 0.01297 -0.0615 0.4776 1.0000
7.500 1.1340 0.02094 0.01325 -0.0602 0.4590 1.0000
7.750 1.1547 0.02127 0.01363 -0.0588 0.4396 1.0000
8.000 1.1731 0.02165 0.01408 -0.0571 0.4187 1.0000
8.250 1.1926 0.02204 0.01445 -0.0555 0.3980 1.0000
8.500 1.2081 0.02252 0.01502 -0.0534 0.3755 1.0000
8.750 1.2235 0.02303 0.01553 -0.0513 0.3530 1.0000
9.000 1.2368 0.02359 0.01609 -0.0490 0.3293 1.0000
9.250 1.2467 0.02425 0.01683 -0.0463 0.3043 1.0000
9.500 1.2546 0.02501 0.01759 -0.0433 0.2793 1.0000
9.750 1.2598 0.02589 0.01843 -0.0401 0.2545 1.0000
10.000 1.2615 0.02692 0.01938 -0.0365 0.2303 1.0000
10.250 1.2588 0.02807 0.02053 -0.0325 0.2063 1.0000
10.500 1.2551 0.02952 0.02191 -0.0288 0.1828 1.0000
10.750 1.2493 0.03130 0.02352 -0.0254 0.1606 1.0000
11.000 1.2428 0.03334 0.02554 -0.0224 0.1374 1.0000
11.250 1.2349 0.03576 0.02784 -0.0197 0.1162 1.0000
11.500 1.2271 0.03837 0.03037 -0.0175 0.0984 1.0000
11.750 1.2186 0.04132 0.03316 -0.0156 0.0835 1.0000
12.000 1.2120 0.04436 0.03611 -0.0140 0.0707 1.0000
12.250 1.2086 0.04727 0.03913 -0.0127 0.0608 1.0000
12.500 1.2078 0.05018 0.04213 -0.0114 0.0526 1.0000
12.750 1.2119 0.05301 0.04487 -0.0101 0.0466 1.0000
13.000 1.2200 0.05561 0.04769 -0.0088 0.0427 1.0000
13.250 1.2292 0.05820 0.05031 -0.0078 0.0396 1.0000
13.500 1.2435 0.06157 0.05376 -0.0066 0.0369 1.0000
13.750 1.2426 0.06490 0.05741 -0.0060 0.0360 1.0000
14.000 1.2361 0.06858 0.06139 -0.0058 0.0346 1.0000
14.250 1.2298 0.07263 0.06571 -0.0059 0.0337 1.0000
14.500 1.2213 0.07701 0.07034 -0.0063 0.0332 1.0000
14.750 1.2094 0.08191 0.07550 -0.0072 0.0328 1.0000
15.000 1.1943 0.08741 0.08128 -0.0087 0.0330 1.0000
15.250 1.1760 0.09355 0.08769 -0.0110 0.0330 1.0000
15.500 1.1554 0.10039 0.09478 -0.0142 0.0331 1.0000
15.750 1.1332 0.10798 0.10260 -0.0182 0.0335 1.0000
16.000 1.1091 0.11651 0.11135 -0.0232 0.0341 1.0000
16.250 1.0838 0.12604 0.12106 -0.0290 0.0351 1.0000
16.500 1.0596 0.13607 0.13123 -0.0354 0.0360 1.0000
16.750 1.0378 0.14635 0.14158 -0.0416 0.0369 1.0000
17.000 1.0220 0.15575 0.15100 -0.0469 0.0376 1.0000
17.250 0.9666 0.18434 0.17949 -0.0628 0.0474 1.0000
17.500 0.7421 0.19522 0.19093 -0.0634 0.1078 1.0000
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Polar data table (+)
Polar graphs
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