S8055 (12%) (s8055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.73 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8055-il-1000000-n5.txt Download as CSV file: xf-s8055-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8491 0.05218 0.04967 -0.0616 1.0000 0.0041
-13.500 -0.8794 0.04364 0.04091 -0.0681 1.0000 0.0041
-13.250 -0.9009 0.03842 0.03548 -0.0703 1.0000 0.0041
-13.000 -0.9097 0.03539 0.03232 -0.0705 1.0000 0.0041
-12.750 -0.9147 0.03307 0.02988 -0.0697 1.0000 0.0041
-12.500 -0.8997 0.03046 0.02705 -0.0728 0.9486 0.0042
-12.250 -0.9069 0.02850 0.02478 -0.0700 0.9145 0.0041
-12.000 -0.9110 0.02713 0.02321 -0.0664 0.8978 0.0042
-11.750 -0.9076 0.02600 0.02192 -0.0635 0.8867 0.0042
-11.500 -0.8992 0.02477 0.02053 -0.0614 0.8787 0.0042
-11.250 -0.8866 0.02373 0.01935 -0.0598 0.8719 0.0043
-11.000 -0.8719 0.02280 0.01829 -0.0583 0.8665 0.0044
-10.750 -0.8564 0.02176 0.01711 -0.0570 0.8615 0.0044
-10.500 -0.8404 0.02069 0.01588 -0.0557 0.8565 0.0044
-10.250 -0.8219 0.01987 0.01493 -0.0546 0.8522 0.0045
-10.000 -0.8017 0.01912 0.01408 -0.0537 0.8486 0.0046
-9.750 -0.7817 0.01829 0.01314 -0.0528 0.8448 0.0047
-9.500 -0.7609 0.01753 0.01226 -0.0519 0.8411 0.0047
-9.250 -0.7392 0.01686 0.01148 -0.0512 0.8377 0.0049
-9.000 -0.7169 0.01622 0.01074 -0.0505 0.8347 0.0050
-8.750 -0.6938 0.01561 0.01005 -0.0499 0.8317 0.0051
-8.500 -0.6701 0.01508 0.00944 -0.0493 0.8287 0.0053
-8.250 -0.6466 0.01452 0.00880 -0.0488 0.8256 0.0053
-8.000 -0.6222 0.01407 0.00827 -0.0483 0.8227 0.0055
-7.750 -0.5977 0.01363 0.00775 -0.0478 0.8200 0.0055
-7.500 -0.5727 0.01318 0.00725 -0.0474 0.8175 0.0056
-7.250 -0.5477 0.01273 0.00676 -0.0471 0.8148 0.0057
-7.000 -0.5232 0.01220 0.00616 -0.0466 0.8118 0.0058
-6.750 -0.4980 0.01177 0.00568 -0.0462 0.8089 0.0061
-6.500 -0.4723 0.01143 0.00530 -0.0459 0.8060 0.0063
-6.250 -0.4463 0.01111 0.00493 -0.0456 0.8032 0.0065
-6.000 -0.4198 0.01081 0.00461 -0.0454 0.8005 0.0067
-5.750 -0.3932 0.01052 0.00430 -0.0452 0.7976 0.0070
-5.500 -0.3665 0.01027 0.00401 -0.0450 0.7947 0.0073
-5.250 -0.3396 0.01004 0.00376 -0.0448 0.7918 0.0076
-5.000 -0.3129 0.00979 0.00346 -0.0446 0.7889 0.0082
-4.750 -0.2859 0.00955 0.00321 -0.0444 0.7861 0.0091
-4.500 -0.2586 0.00934 0.00300 -0.0443 0.7829 0.0099
-4.250 -0.2314 0.00912 0.00278 -0.0442 0.7792 0.0117
-4.000 -0.2043 0.00893 0.00258 -0.0440 0.7756 0.0151
-3.750 -0.1773 0.00871 0.00238 -0.0439 0.7723 0.0236
-3.500 -0.1500 0.00849 0.00222 -0.0438 0.7691 0.0345
-3.250 -0.1226 0.00829 0.00207 -0.0437 0.7655 0.0472
-3.000 -0.0957 0.00804 0.00192 -0.0436 0.7617 0.0709
-2.750 -0.0692 0.00777 0.00177 -0.0434 0.7577 0.1058
-2.500 -0.0427 0.00746 0.00164 -0.0433 0.7530 0.1539
-2.250 -0.0163 0.00716 0.00151 -0.0431 0.7471 0.2054
-2.000 0.0101 0.00689 0.00140 -0.0429 0.7415 0.2595
-1.750 0.0369 0.00663 0.00131 -0.0428 0.7355 0.3118
-1.500 0.0634 0.00638 0.00123 -0.0426 0.7284 0.3686
-1.250 0.0900 0.00614 0.00115 -0.0425 0.7192 0.4243
-1.000 0.1163 0.00592 0.00107 -0.0422 0.7077 0.4838
-0.750 0.1424 0.00571 0.00101 -0.0419 0.6947 0.5454
-0.500 0.1682 0.00554 0.00097 -0.0415 0.6795 0.6066
-0.250 0.1943 0.00545 0.00097 -0.0411 0.6612 0.6563
0.000 0.2207 0.00544 0.00098 -0.0408 0.6414 0.6908
0.250 0.2475 0.00548 0.00100 -0.0405 0.6226 0.7135
0.500 0.2741 0.00556 0.00104 -0.0402 0.5999 0.7315
0.750 0.3003 0.00569 0.00109 -0.0399 0.5722 0.7481
1.000 0.3267 0.00583 0.00115 -0.0396 0.5450 0.7599
1.250 0.3533 0.00597 0.00121 -0.0394 0.5206 0.7709
1.500 0.3799 0.00610 0.00128 -0.0391 0.4982 0.7824
1.750 0.4063 0.00624 0.00136 -0.0388 0.4748 0.7916
2.000 0.4324 0.00643 0.00145 -0.0386 0.4485 0.8006
2.250 0.4582 0.00661 0.00155 -0.0382 0.4213 0.8103
2.500 0.4842 0.00678 0.00165 -0.0379 0.3976 0.8189
2.750 0.5098 0.00698 0.00176 -0.0375 0.3729 0.8281
3.000 0.5351 0.00718 0.00189 -0.0371 0.3462 0.8377
3.500 0.5855 0.00758 0.00216 -0.0362 0.2997 0.8564
4.000 0.6347 0.00809 0.00247 -0.0352 0.2491 0.8709
4.250 0.6599 0.00830 0.00262 -0.0348 0.2312 0.8785
4.500 0.6847 0.00848 0.00278 -0.0343 0.2163 0.8868
4.750 0.7096 0.00868 0.00293 -0.0338 0.2030 0.8960
5.000 0.7338 0.00887 0.00311 -0.0332 0.1893 0.9070
5.250 0.7581 0.00905 0.00328 -0.0325 0.1774 0.9196
5.500 0.7828 0.00923 0.00346 -0.0320 0.1664 0.9349
5.750 0.8104 0.00947 0.00368 -0.0321 0.1541 0.9522
6.000 0.8429 0.00974 0.00391 -0.0334 0.1427 0.9676
6.250 0.8758 0.01004 0.00415 -0.0349 0.1315 0.9812
6.500 0.9077 0.01032 0.00439 -0.0361 0.1216 0.9922
6.750 0.9396 0.01059 0.00463 -0.0373 0.1139 0.9997
7.000 0.9612 0.01086 0.00487 -0.0363 0.1060 1.0000
7.250 0.9833 0.01110 0.00509 -0.0353 0.0996 1.0000
7.500 1.0045 0.01141 0.00535 -0.0343 0.0913 1.0000
7.750 1.0258 0.01172 0.00563 -0.0333 0.0833 1.0000
8.000 1.0473 0.01202 0.00591 -0.0323 0.0771 1.0000
8.250 1.0682 0.01236 0.00622 -0.0313 0.0712 1.0000
8.500 1.0896 0.01266 0.00652 -0.0303 0.0667 1.0000
8.750 1.1104 0.01299 0.00685 -0.0293 0.0622 1.0000
9.000 1.1304 0.01336 0.00719 -0.0281 0.0574 1.0000
9.250 1.1505 0.01370 0.00754 -0.0270 0.0533 1.0000
9.500 1.1680 0.01412 0.00793 -0.0255 0.0482 1.0000
9.750 1.1855 0.01446 0.00829 -0.0238 0.0454 1.0000
10.000 1.2014 0.01489 0.00871 -0.0220 0.0420 1.0000
10.250 1.2178 0.01530 0.00913 -0.0203 0.0396 1.0000
10.500 1.2347 0.01571 0.00956 -0.0188 0.0376 1.0000
10.750 1.2504 0.01620 0.01006 -0.0172 0.0350 1.0000
11.000 1.2660 0.01672 0.01059 -0.0156 0.0327 1.0000
11.250 1.2825 0.01719 0.01109 -0.0142 0.0315 1.0000
11.500 1.2985 0.01771 0.01164 -0.0128 0.0302 1.0000
11.750 1.3136 0.01828 0.01224 -0.0113 0.0289 1.0000
12.000 1.3281 0.01891 0.01290 -0.0098 0.0276 1.0000
12.250 1.3428 0.01954 0.01357 -0.0084 0.0264 1.0000
12.500 1.3577 0.02017 0.01424 -0.0071 0.0253 1.0000
12.750 1.3716 0.02087 0.01498 -0.0058 0.0240 1.0000
13.000 1.3846 0.02165 0.01578 -0.0044 0.0227 1.0000
13.250 1.3969 0.02249 0.01665 -0.0031 0.0214 1.0000
13.500 1.4102 0.02328 0.01750 -0.0018 0.0209 1.0000
13.750 1.4221 0.02417 0.01843 -0.0006 0.0193 1.0000
14.000 1.4329 0.02517 0.01947 0.0007 0.0181 1.0000
14.250 1.4432 0.02622 0.02056 0.0020 0.0170 1.0000
14.500 1.4536 0.02728 0.02168 0.0031 0.0159 1.0000
14.750 1.4606 0.02863 0.02305 0.0044 0.0139 1.0000
15.000 1.4690 0.02991 0.02439 0.0056 0.0127 1.0000
15.250 1.4730 0.03159 0.02609 0.0068 0.0103 1.0000
15.500 1.4760 0.03339 0.02794 0.0079 0.0086 1.0000
15.750 1.4787 0.03528 0.02989 0.0089 0.0074 1.0000
16.000 1.4801 0.03739 0.03208 0.0097 0.0065 1.0000
16.250 1.4812 0.03961 0.03437 0.0104 0.0059 1.0000
16.500 1.4811 0.04204 0.03689 0.0108 0.0054 1.0000
16.750 1.4802 0.04470 0.03964 0.0111 0.0051 1.0000
17.000 1.4778 0.04766 0.04270 0.0110 0.0046 1.0000
17.250 1.4780 0.05044 0.04557 0.0108 0.0047 1.0000
17.500 1.4744 0.05382 0.04906 0.0102 0.0045 1.0000
17.750 1.4712 0.05728 0.05263 0.0095 0.0044 1.0000
18.000 1.4630 0.06157 0.05703 0.0082 0.0042 1.0000
18.250 1.4540 0.06615 0.06173 0.0067 0.0041 1.0000
18.500 1.4435 0.07116 0.06687 0.0047 0.0040 1.0000
18.750 1.4320 0.07651 0.07234 0.0025 0.0039 1.0000
19.000 1.4159 0.08278 0.07874 -0.0004 0.0038 1.0000
19.250 1.4011 0.08907 0.08517 -0.0034 0.0039 1.0000
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Polar data table (+)
Polar graphs
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