S8055 (12%) (s8055-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 500,000 Max Cl/Cd: 86.21 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8055-il-500000.txt Download as CSV file: xf-s8055-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4343 0.08905 0.08682 -0.0419 1.0000 0.0230
-10.000 -0.4415 0.08307 0.08088 -0.0454 1.0000 0.0237
-8.250 -0.5761 0.02539 0.02021 -0.0632 0.9177 0.0134
-8.000 -0.5589 0.02386 0.01837 -0.0616 0.9131 0.0132
-7.750 -0.5388 0.02241 0.01672 -0.0606 0.9083 0.0132
-7.500 -0.5184 0.02082 0.01490 -0.0595 0.9039 0.0132
-7.250 -0.4982 0.01887 0.01276 -0.0584 0.9001 0.0134
-7.000 -0.4760 0.01767 0.01145 -0.0576 0.8966 0.0136
-6.750 -0.4529 0.01675 0.01050 -0.0570 0.8927 0.0140
-6.500 -0.4295 0.01602 0.00970 -0.0563 0.8887 0.0145
-6.250 -0.4063 0.01529 0.00888 -0.0554 0.8852 0.0148
-6.000 -0.3830 0.01469 0.00821 -0.0546 0.8819 0.0153
-5.750 -0.3579 0.01424 0.00771 -0.0542 0.8781 0.0162
-5.500 -0.3352 0.01351 0.00693 -0.0533 0.8742 0.0170
-5.250 -0.3117 0.01296 0.00635 -0.0526 0.8706 0.0179
-5.000 -0.2873 0.01253 0.00587 -0.0518 0.8675 0.0192
-4.750 -0.2627 0.01205 0.00534 -0.0512 0.8639 0.0211
-4.500 -0.2375 0.01163 0.00491 -0.0507 0.8599 0.0244
-4.250 -0.2134 0.01107 0.00440 -0.0500 0.8562 0.0390
-4.000 -0.1896 0.01053 0.00405 -0.0493 0.8528 0.0792
-3.750 -0.1654 0.01007 0.00382 -0.0488 0.8492 0.1317
-3.500 -0.1409 0.00964 0.00362 -0.0484 0.8448 0.1902
-3.250 -0.1169 0.00916 0.00343 -0.0478 0.8407 0.2666
-3.000 -0.0939 0.00861 0.00325 -0.0471 0.8371 0.3690
-2.750 -0.0710 0.00812 0.00312 -0.0463 0.8332 0.4685
-2.500 -0.0481 0.00768 0.00302 -0.0454 0.8287 0.5639
-2.250 -0.0247 0.00735 0.00299 -0.0444 0.8245 0.6528
-2.000 0.0007 0.00723 0.00297 -0.0436 0.8208 0.7072
-1.750 0.0268 0.00718 0.00299 -0.0429 0.8160 0.7411
-1.500 0.0535 0.00715 0.00297 -0.0424 0.8106 0.7656
-1.250 0.0806 0.00712 0.00291 -0.0420 0.8060 0.7846
-1.000 0.1075 0.00712 0.00290 -0.0415 0.8011 0.8004
-0.750 0.1344 0.00708 0.00288 -0.0411 0.7952 0.8145
-0.500 0.1614 0.00704 0.00281 -0.0405 0.7896 0.8269
-0.250 0.1882 0.00700 0.00278 -0.0401 0.7827 0.8378
0.000 0.2152 0.00696 0.00272 -0.0396 0.7760 0.8490
0.250 0.2419 0.00693 0.00268 -0.0391 0.7692 0.8594
0.500 0.2686 0.00687 0.00263 -0.0386 0.7610 0.8684
0.750 0.2953 0.00685 0.00258 -0.0381 0.7535 0.8786
1.000 0.3217 0.00680 0.00254 -0.0376 0.7447 0.8874
1.250 0.3482 0.00676 0.00250 -0.0371 0.7348 0.8967
1.500 0.3742 0.00673 0.00246 -0.0364 0.7243 0.9062
1.750 0.4003 0.00670 0.00242 -0.0358 0.7120 0.9153
2.000 0.4260 0.00669 0.00241 -0.0351 0.6985 0.9254
2.250 0.4529 0.00670 0.00241 -0.0347 0.6842 0.9342
2.500 0.4799 0.00675 0.00242 -0.0343 0.6681 0.9440
2.750 0.5091 0.00684 0.00245 -0.0344 0.6491 0.9520
3.000 0.5395 0.00695 0.00250 -0.0349 0.6269 0.9592
3.250 0.5720 0.00712 0.00258 -0.0359 0.6038 0.9646
3.500 0.6024 0.00731 0.00267 -0.0366 0.5764 0.9716
3.750 0.6375 0.00755 0.00279 -0.0383 0.5451 0.9752
4.000 0.6715 0.00784 0.00294 -0.0398 0.5109 0.9798
4.250 0.7041 0.00820 0.00311 -0.0412 0.4685 0.9851
4.500 0.7388 0.00857 0.00331 -0.0431 0.4267 0.9893
4.750 0.7719 0.00900 0.00355 -0.0447 0.3838 0.9945
5.000 0.8072 0.00942 0.00379 -0.0468 0.3450 0.9986
5.250 0.8265 0.00976 0.00400 -0.0457 0.3155 1.0000
5.500 0.8387 0.01008 0.00420 -0.0430 0.2910 1.0000
5.750 0.8543 0.01043 0.00443 -0.0409 0.2682 1.0000
6.000 0.8716 0.01079 0.00469 -0.0390 0.2474 1.0000
6.250 0.8901 0.01114 0.00496 -0.0375 0.2285 1.0000
6.500 0.9091 0.01149 0.00523 -0.0360 0.2116 1.0000
6.750 0.9288 0.01185 0.00552 -0.0347 0.1965 1.0000
7.000 0.9489 0.01220 0.00583 -0.0335 0.1838 1.0000
7.250 0.9690 0.01257 0.00615 -0.0323 0.1718 1.0000
7.500 0.9887 0.01296 0.00649 -0.0310 0.1605 1.0000
7.750 1.0097 0.01328 0.00681 -0.0300 0.1508 1.0000
8.000 1.0297 0.01365 0.00717 -0.0288 0.1416 1.0000
8.250 1.0484 0.01410 0.00756 -0.0274 0.1318 1.0000
8.500 1.0684 0.01446 0.00792 -0.0263 0.1226 1.0000
8.750 1.0871 0.01487 0.00833 -0.0249 0.1136 1.0000
9.000 1.1027 0.01536 0.00878 -0.0231 0.1047 1.0000
9.250 1.1196 0.01577 0.00920 -0.0214 0.0971 1.0000
9.500 1.1346 0.01630 0.00972 -0.0195 0.0898 1.0000
9.750 1.1492 0.01686 0.01026 -0.0177 0.0829 1.0000
10.000 1.1641 0.01743 0.01086 -0.0159 0.0770 1.0000
10.250 1.1774 0.01812 0.01152 -0.0141 0.0712 1.0000
10.500 1.1909 0.01882 0.01226 -0.0123 0.0669 1.0000
10.750 1.2057 0.01946 0.01294 -0.0108 0.0631 1.0000
11.000 1.2156 0.02041 0.01389 -0.0088 0.0592 1.0000
11.250 1.2297 0.02113 0.01467 -0.0073 0.0564 1.0000
11.500 1.2440 0.02185 0.01546 -0.0059 0.0538 1.0000
11.750 1.2560 0.02272 0.01634 -0.0044 0.0512 1.0000
12.000 1.2616 0.02406 0.01770 -0.0023 0.0485 1.0000
12.250 1.2768 0.02477 0.01851 -0.0013 0.0470 1.0000
12.500 1.2891 0.02569 0.01951 0.0000 0.0455 1.0000
12.750 1.3011 0.02664 0.02052 0.0012 0.0436 1.0000
13.000 1.3098 0.02785 0.02175 0.0025 0.0418 1.0000
13.250 1.3122 0.02960 0.02355 0.0043 0.0401 1.0000
13.500 1.3249 0.03057 0.02464 0.0052 0.0391 1.0000
13.750 1.3359 0.03170 0.02585 0.0061 0.0378 1.0000
14.000 1.3449 0.03302 0.02725 0.0070 0.0365 1.0000
14.250 1.3527 0.03447 0.02876 0.0079 0.0354 1.0000
14.500 1.3565 0.03630 0.03065 0.0088 0.0343 1.0000
14.750 1.3528 0.03888 0.03330 0.0099 0.0329 1.0000
15.000 1.3619 0.04039 0.03494 0.0104 0.0322 1.0000
15.250 1.3703 0.04199 0.03666 0.0107 0.0311 1.0000
15.500 1.3761 0.04391 0.03867 0.0109 0.0300 1.0000
15.750 1.3815 0.04596 0.04078 0.0110 0.0286 1.0000
16.000 1.3804 0.04880 0.04369 0.0109 0.0277 1.0000
16.250 1.3752 0.05223 0.04721 0.0106 0.0266 1.0000
16.500 1.3813 0.05450 0.04962 0.0102 0.0256 1.0000
16.750 1.3857 0.05707 0.05231 0.0096 0.0242 1.0000
17.000 1.3855 0.06030 0.05561 0.0086 0.0227 1.0000
17.250 1.3759 0.06491 0.06031 0.0071 0.0220 1.0000
17.500 1.3733 0.06874 0.06429 0.0058 0.0206 1.0000
17.750 1.3688 0.07295 0.06863 0.0041 0.0196 1.0000
18.000 1.3591 0.07815 0.07390 0.0018 0.0181 1.0000
18.250 1.3403 0.08497 0.08084 -0.0014 0.0174 1.0000
18.500 1.3302 0.09058 0.08660 -0.0041 0.0163 1.0000
18.750 1.3150 0.09714 0.09330 -0.0073 0.0159 1.0000
19.000 1.2982 0.10422 0.10051 -0.0110 0.0153 1.0000
19.250 1.2815 0.11138 0.10780 -0.0148 0.0152 1.0000
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Polar data table (+)
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