S8055 (12%) (s8055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.99 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8055-il-1000000.txt Download as CSV file: xf-s8055-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5519 0.05151 0.04944 -0.0735 0.9657 0.0131
-9.250 -0.6926 0.02420 0.01982 -0.0583 0.8820 0.0079
-9.000 -0.6739 0.02317 0.01864 -0.0573 0.8778 0.0079
-8.750 -0.6561 0.02179 0.01707 -0.0561 0.8736 0.0078
-8.500 -0.6384 0.02020 0.01527 -0.0548 0.8696 0.0078
-8.250 -0.6175 0.01917 0.01409 -0.0540 0.8660 0.0078
-8.000 -0.6001 0.01702 0.01171 -0.0526 0.8625 0.0079
-7.750 -0.5797 0.01570 0.01026 -0.0517 0.8590 0.0080
-7.500 -0.5581 0.01472 0.00918 -0.0508 0.8558 0.0082
-7.250 -0.5348 0.01407 0.00847 -0.0501 0.8526 0.0085
-7.000 -0.5108 0.01348 0.00782 -0.0496 0.8496 0.0087
-6.750 -0.4858 0.01301 0.00731 -0.0492 0.8466 0.0091
-6.500 -0.4609 0.01254 0.00678 -0.0487 0.8434 0.0094
-6.250 -0.4362 0.01204 0.00622 -0.0482 0.8404 0.0096
-6.000 -0.4108 0.01165 0.00577 -0.0477 0.8374 0.0099
-5.750 -0.3849 0.01131 0.00537 -0.0474 0.8344 0.0102
-5.500 -0.3596 0.01083 0.00485 -0.0469 0.8316 0.0105
-5.250 -0.3343 0.01036 0.00434 -0.0465 0.8286 0.0110
-5.000 -0.3080 0.01003 0.00399 -0.0462 0.8255 0.0117
-4.750 -0.2813 0.00979 0.00371 -0.0460 0.8226 0.0127
-4.500 -0.2548 0.00952 0.00339 -0.0457 0.8193 0.0141
-4.250 -0.2278 0.00923 0.00311 -0.0455 0.8162 0.0168
-4.000 -0.2018 0.00883 0.00279 -0.0451 0.8128 0.0313
-3.750 -0.1758 0.00847 0.00256 -0.0448 0.8095 0.0587
-3.500 -0.1495 0.00817 0.00237 -0.0446 0.8064 0.0893
-3.250 -0.1231 0.00790 0.00222 -0.0444 0.8031 0.1257
-3.000 -0.0970 0.00754 0.00207 -0.0442 0.7998 0.1785
-2.750 -0.0712 0.00715 0.00192 -0.0440 0.7960 0.2441
-2.500 -0.0459 0.00674 0.00178 -0.0436 0.7920 0.3241
-2.250 -0.0207 0.00637 0.00167 -0.0433 0.7877 0.4077
-2.000 0.0046 0.00596 0.00156 -0.0429 0.7833 0.4959
-1.750 0.0297 0.00558 0.00147 -0.0424 0.7787 0.5835
-1.500 0.0554 0.00534 0.00143 -0.0419 0.7742 0.6568
-1.250 0.0823 0.00521 0.00141 -0.0416 0.7688 0.7001
-1.000 0.1098 0.00513 0.00139 -0.0414 0.7625 0.7281
-0.750 0.1376 0.00511 0.00136 -0.0412 0.7566 0.7486
-0.500 0.1657 0.00507 0.00135 -0.0411 0.7498 0.7644
-0.250 0.1936 0.00505 0.00132 -0.0410 0.7425 0.7779
0.000 0.2218 0.00503 0.00131 -0.0409 0.7344 0.7897
0.250 0.2499 0.00504 0.00129 -0.0409 0.7263 0.8001
0.500 0.2778 0.00502 0.00129 -0.0408 0.7156 0.8095
0.750 0.3056 0.00503 0.00128 -0.0406 0.7026 0.8190
1.000 0.3331 0.00506 0.00127 -0.0405 0.6880 0.8274
1.250 0.3605 0.00510 0.00128 -0.0403 0.6725 0.8354
1.500 0.3877 0.00516 0.00130 -0.0400 0.6565 0.8441
1.750 0.4145 0.00524 0.00134 -0.0398 0.6381 0.8517
2.000 0.4410 0.00535 0.00138 -0.0395 0.6175 0.8599
2.250 0.4673 0.00546 0.00144 -0.0391 0.5955 0.8683
2.750 0.5189 0.00573 0.00159 -0.0382 0.5497 0.8854
3.000 0.5440 0.00591 0.00169 -0.0377 0.5224 0.8953
3.250 0.5683 0.00608 0.00180 -0.0369 0.4948 0.9057
3.500 0.5924 0.00629 0.00192 -0.0362 0.4656 0.9159
3.750 0.6159 0.00654 0.00205 -0.0354 0.4296 0.9267
4.000 0.6391 0.00681 0.00221 -0.0345 0.3931 0.9384
4.250 0.6639 0.00710 0.00238 -0.0340 0.3605 0.9509
4.500 0.6923 0.00739 0.00257 -0.0344 0.3302 0.9627
4.750 0.7232 0.00772 0.00277 -0.0353 0.3007 0.9730
5.000 0.7556 0.00806 0.00298 -0.0366 0.2725 0.9815
5.250 0.7892 0.00839 0.00320 -0.0382 0.2481 0.9876
5.500 0.8226 0.00872 0.00342 -0.0398 0.2247 0.9933
5.750 0.8572 0.00907 0.00366 -0.0416 0.2039 0.9972
6.000 0.8891 0.00936 0.00388 -0.0429 0.1874 1.0000
6.250 0.9073 0.00962 0.00407 -0.0412 0.1748 1.0000
6.500 0.9274 0.00987 0.00427 -0.0398 0.1635 1.0000
6.750 0.9483 0.01011 0.00448 -0.0386 0.1545 1.0000
7.000 0.9691 0.01038 0.00471 -0.0374 0.1451 1.0000
7.250 0.9907 0.01064 0.00494 -0.0364 0.1368 1.0000
7.500 1.0124 0.01091 0.00519 -0.0354 0.1285 1.0000
7.750 1.0334 0.01124 0.00547 -0.0343 0.1187 1.0000
8.000 1.0555 0.01150 0.00572 -0.0335 0.1114 1.0000
8.250 1.0766 0.01183 0.00602 -0.0324 0.1028 1.0000
8.500 1.0971 0.01220 0.00633 -0.0313 0.0939 1.0000
8.750 1.1179 0.01253 0.00666 -0.0303 0.0866 1.0000
9.000 1.1375 0.01293 0.00702 -0.0291 0.0788 1.0000
9.250 1.1567 0.01333 0.00739 -0.0278 0.0722 1.0000
9.500 1.1757 0.01372 0.00777 -0.0265 0.0662 1.0000
9.750 1.1917 0.01416 0.00819 -0.0247 0.0608 1.0000
10.000 1.2081 0.01455 0.00860 -0.0229 0.0566 1.0000
10.250 1.2238 0.01499 0.00904 -0.0211 0.0529 1.0000
10.500 1.2380 0.01554 0.00957 -0.0191 0.0484 1.0000
10.750 1.2553 0.01594 0.01000 -0.0177 0.0461 1.0000
11.000 1.2705 0.01647 0.01054 -0.0160 0.0433 1.0000
11.250 1.2833 0.01715 0.01122 -0.0141 0.0402 1.0000
11.500 1.3002 0.01761 0.01174 -0.0128 0.0391 1.0000
11.750 1.3159 0.01815 0.01232 -0.0114 0.0378 1.0000
12.000 1.3304 0.01878 0.01298 -0.0099 0.0363 1.0000
12.250 1.3431 0.01953 0.01375 -0.0083 0.0344 1.0000
12.500 1.3551 0.02034 0.01460 -0.0066 0.0327 1.0000
12.750 1.3707 0.02094 0.01526 -0.0055 0.0319 1.0000
13.000 1.3854 0.02160 0.01597 -0.0043 0.0308 1.0000
13.250 1.3984 0.02240 0.01679 -0.0030 0.0294 1.0000
13.500 1.4096 0.02332 0.01775 -0.0015 0.0285 1.0000
13.750 1.4179 0.02448 0.01894 0.0000 0.0268 1.0000
14.000 1.4319 0.02525 0.01979 0.0010 0.0262 1.0000
14.250 1.4449 0.02611 0.02071 0.0021 0.0253 1.0000
14.500 1.4561 0.02712 0.02177 0.0032 0.0243 1.0000
14.750 1.4656 0.02828 0.02296 0.0043 0.0229 1.0000
15.000 1.4714 0.02976 0.02448 0.0056 0.0217 1.0000
15.250 1.4841 0.03072 0.02551 0.0064 0.0206 1.0000
15.500 1.4928 0.03202 0.02685 0.0072 0.0191 1.0000
15.750 1.4972 0.03371 0.02858 0.0083 0.0174 1.0000
16.000 1.5042 0.03525 0.03019 0.0090 0.0156 1.0000
16.250 1.5055 0.03736 0.03231 0.0099 0.0130 1.0000
16.500 1.5032 0.03989 0.03488 0.0106 0.0108 1.0000
16.750 1.5015 0.04253 0.03759 0.0110 0.0095 1.0000
17.000 1.4948 0.04584 0.04098 0.0112 0.0081 1.0000
17.250 1.4948 0.04856 0.04380 0.0111 0.0081 1.0000
17.500 1.4893 0.05207 0.04741 0.0107 0.0075 1.0000
17.750 1.4847 0.05564 0.05108 0.0100 0.0073 1.0000
18.000 1.4723 0.06042 0.05597 0.0087 0.0068 1.0000
18.250 1.4602 0.06540 0.06108 0.0071 0.0066 1.0000
18.500 1.4485 0.07057 0.06638 0.0051 0.0064 1.0000
18.750 1.4368 0.07591 0.07186 0.0029 0.0063 1.0000
19.000 1.4208 0.08215 0.07823 0.0000 0.0063 1.0000
19.250 1.4052 0.08857 0.08479 -0.0031 0.0063 1.0000
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Polar data table (+)
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