S8055 (12%) (s8055-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 50,000 Max Cl/Cd: 32.73 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8055-il-50000-n5.txt Download as CSV file: xf-s8055-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4366 0.10126 0.09407 -0.0417 1.0000 0.0456
-10.250 -0.4378 0.09682 0.08970 -0.0436 1.0000 0.0453
-10.000 -0.4411 0.09200 0.08495 -0.0459 1.0000 0.0449
-9.750 -0.4475 0.08654 0.07956 -0.0489 1.0000 0.0445
-9.500 -0.4567 0.08067 0.07376 -0.0526 1.0000 0.0439
-9.250 -0.4732 0.07527 0.06841 -0.0557 1.0000 0.0433
-9.000 -0.4951 0.07114 0.06431 -0.0565 1.0000 0.0426
-8.750 -0.5224 0.06832 0.06153 -0.0541 1.0000 0.0422
-8.500 -0.5475 0.06565 0.05883 -0.0510 1.0000 0.0418
-8.250 -0.5700 0.06312 0.05622 -0.0474 1.0000 0.0413
-8.000 -0.5882 0.06057 0.05354 -0.0438 1.0000 0.0414
-7.750 -0.6022 0.05783 0.05060 -0.0404 1.0000 0.0412
-7.500 -0.6114 0.05511 0.04765 -0.0373 1.0000 0.0414
-7.250 -0.6165 0.05226 0.04452 -0.0344 1.0000 0.0415
-7.000 -0.6177 0.04943 0.04136 -0.0317 1.0000 0.0417
-6.750 -0.6151 0.04658 0.03815 -0.0292 1.0000 0.0420
-6.500 -0.6088 0.04388 0.03505 -0.0269 1.0000 0.0424
-6.250 -0.5992 0.04139 0.03217 -0.0248 1.0000 0.0430
-6.000 -0.5866 0.03906 0.02942 -0.0229 1.0000 0.0438
-5.750 -0.5676 0.03679 0.02663 -0.0217 0.9987 0.0458
-5.500 -0.5400 0.03490 0.02455 -0.0225 0.9945 0.0489
-5.250 -0.5119 0.03333 0.02274 -0.0230 0.9902 0.0529
-5.000 -0.4816 0.03172 0.02080 -0.0233 0.9862 0.0571
-4.750 -0.4530 0.03049 0.01954 -0.0239 0.9820 0.0646
-4.500 -0.4251 0.02929 0.01827 -0.0242 0.9773 0.0737
-4.250 -0.3950 0.02820 0.01712 -0.0248 0.9730 0.0898
-4.000 -0.3683 0.02708 0.01607 -0.0251 0.9681 0.1154
-3.750 -0.3414 0.02579 0.01511 -0.0257 0.9630 0.1710
-3.500 -0.3146 0.02443 0.01446 -0.0266 0.9584 0.2902
-3.250 -0.2976 0.02334 0.01419 -0.0251 0.9522 0.4400
-3.000 -0.2774 0.02287 0.01459 -0.0223 0.9468 0.6159
-2.750 -0.2530 0.02315 0.01504 -0.0198 0.9416 0.7386
-2.500 -0.2287 0.02349 0.01528 -0.0177 0.9353 0.8090
-2.250 -0.1895 0.02394 0.01552 -0.0184 0.9309 0.8652
-2.000 -0.1310 0.02446 0.01571 -0.0230 0.9287 0.9080
-1.750 -0.0668 0.02483 0.01574 -0.0296 0.9257 0.9380
-1.500 0.0013 0.02504 0.01563 -0.0375 0.9228 0.9606
-1.250 0.0661 0.02510 0.01542 -0.0452 0.9193 0.9800
-1.000 0.1310 0.02508 0.01518 -0.0531 0.9161 0.9965
-0.750 0.1622 0.02511 0.01508 -0.0548 0.9081 1.0000
-0.500 0.1922 0.02517 0.01501 -0.0561 0.9001 1.0000
-0.250 0.2110 0.02527 0.01503 -0.0553 0.8898 1.0000
0.000 0.2465 0.02533 0.01498 -0.0573 0.8829 1.0000
0.250 0.2606 0.02547 0.01507 -0.0555 0.8711 1.0000
0.500 0.2815 0.02559 0.01513 -0.0547 0.8609 1.0000
0.750 0.3124 0.02563 0.01511 -0.0555 0.8523 1.0000
1.000 0.3272 0.02578 0.01522 -0.0535 0.8399 1.0000
1.250 0.3469 0.02589 0.01530 -0.0523 0.8286 1.0000
1.500 0.3807 0.02583 0.01522 -0.0532 0.8200 1.0000
1.750 0.3953 0.02596 0.01534 -0.0510 0.8066 1.0000
2.000 0.4130 0.02606 0.01542 -0.0491 0.7936 1.0000
2.250 0.4343 0.02608 0.01544 -0.0478 0.7809 1.0000
2.500 0.4604 0.02598 0.01535 -0.0470 0.7689 1.0000
2.750 0.4891 0.02577 0.01516 -0.0465 0.7572 1.0000
3.000 0.5086 0.02571 0.01511 -0.0446 0.7424 1.0000
3.250 0.5295 0.02560 0.01502 -0.0429 0.7274 1.0000
3.500 0.5517 0.02542 0.01489 -0.0412 0.7121 1.0000
3.750 0.5751 0.02518 0.01470 -0.0397 0.6964 1.0000
4.000 0.5957 0.02501 0.01457 -0.0378 0.6788 1.0000
4.250 0.6165 0.02486 0.01447 -0.0360 0.6600 1.0000
4.500 0.6407 0.02459 0.01427 -0.0345 0.6407 1.0000
4.750 0.6686 0.02420 0.01390 -0.0333 0.6207 1.0000
5.000 0.6902 0.02411 0.01384 -0.0316 0.5964 1.0000
5.250 0.7167 0.02389 0.01363 -0.0303 0.5712 1.0000
5.500 0.7415 0.02381 0.01351 -0.0290 0.5432 1.0000
5.750 0.7638 0.02393 0.01356 -0.0274 0.5129 1.0000
6.000 0.7849 0.02417 0.01372 -0.0258 0.4813 1.0000
6.250 0.8042 0.02457 0.01400 -0.0240 0.4500 1.0000
6.500 0.8219 0.02511 0.01442 -0.0222 0.4194 1.0000
6.750 0.8385 0.02575 0.01495 -0.0204 0.3903 1.0000
7.000 0.8548 0.02648 0.01560 -0.0186 0.3636 1.0000
7.250 0.8711 0.02727 0.01627 -0.0170 0.3397 1.0000
7.500 0.8870 0.02812 0.01707 -0.0154 0.3170 1.0000
7.750 0.9031 0.02900 0.01787 -0.0138 0.2968 1.0000
8.000 0.9195 0.02992 0.01875 -0.0124 0.2781 1.0000
8.250 0.9357 0.03087 0.01971 -0.0110 0.2606 1.0000
8.500 0.9527 0.03186 0.02071 -0.0098 0.2447 1.0000
8.750 0.9687 0.03287 0.02176 -0.0084 0.2297 1.0000
9.000 0.9851 0.03392 0.02283 -0.0072 0.2161 1.0000
9.250 1.0010 0.03500 0.02391 -0.0059 0.2035 1.0000
9.500 1.0151 0.03614 0.02513 -0.0044 0.1912 1.0000
9.750 1.0293 0.03739 0.02654 -0.0031 0.1797 1.0000
10.000 1.0425 0.03868 0.02791 -0.0017 0.1692 1.0000
10.250 1.0573 0.03994 0.02912 -0.0005 0.1599 1.0000
10.500 1.0677 0.04146 0.03088 0.0010 0.1507 1.0000
10.750 1.0803 0.04295 0.03245 0.0023 0.1429 1.0000
11.000 1.0911 0.04458 0.03424 0.0036 0.1356 1.0000
11.250 1.1021 0.04629 0.03608 0.0048 0.1292 1.0000
11.500 1.1084 0.04823 0.03825 0.0062 0.1231 1.0000
11.750 1.1228 0.04979 0.03976 0.0071 0.1181 1.0000
12.000 1.1221 0.05250 0.04288 0.0086 0.1137 1.0000
12.250 1.1241 0.05484 0.04544 0.0099 0.1095 1.0000
12.500 1.1364 0.05644 0.04699 0.0106 0.1054 1.0000
12.750 1.1264 0.05992 0.05083 0.0118 0.1027 1.0000
13.000 1.1149 0.06376 0.05502 0.0125 0.1005 1.0000
13.250 1.1022 0.06790 0.05944 0.0128 0.0986 1.0000
13.500 1.0884 0.07233 0.06408 0.0125 0.0969 1.0000
13.750 1.0740 0.07705 0.06899 0.0116 0.0954 1.0000
14.000 1.0901 0.07836 0.07023 0.0122 0.0924 1.0000
14.250 1.0571 0.08577 0.07790 0.0096 0.0922 1.0000
14.500 1.0166 0.09536 0.08770 0.0048 0.0923 1.0000
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Polar data table (+)
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