MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 100,000 Max Cl/Cd: 48.48 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mb253515sm-il-100000.txt Download as CSV file: xf-mb253515sm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MB253515 15.0% smoothed
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3987 0.09842 0.09383 -0.0461 1.0000 0.1731
-9.750 -0.3776 0.09537 0.09078 -0.0434 1.0000 0.1796
-9.500 -0.4294 0.09201 0.08766 -0.0475 1.0000 0.1884
-9.250 -0.3839 0.08968 0.08525 -0.0424 1.0000 0.1967
-9.000 -0.4558 0.08680 0.08270 -0.0448 1.0000 0.2031
-8.750 -0.4049 0.08477 0.08057 -0.0398 1.0000 0.2132
-8.500 -0.4604 0.08415 0.08021 -0.0356 1.0000 0.2166
-8.250 -0.5072 0.08367 0.07990 -0.0306 1.0000 0.2167
-8.000 -0.5492 0.08269 0.07904 -0.0262 1.0000 0.2165
-7.000 -0.5886 0.05022 0.04484 -0.0459 0.9560 0.1482
-6.750 -0.5804 0.04123 0.03412 -0.0413 0.9465 0.0843
-6.500 -0.5497 0.03803 0.03040 -0.0424 0.9415 0.0825
-6.250 -0.5311 0.03585 0.02781 -0.0409 0.9332 0.0819
-6.000 -0.4969 0.03344 0.02487 -0.0419 0.9280 0.0799
-5.750 -0.4662 0.03179 0.02295 -0.0424 0.9221 0.0813
-5.500 -0.4363 0.03045 0.02139 -0.0429 0.9155 0.0838
-5.250 -0.3917 0.02884 0.01958 -0.0457 0.9119 0.0854
-5.000 -0.3652 0.02801 0.01859 -0.0454 0.9046 0.0877
-4.750 -0.3302 0.02655 0.01726 -0.0469 0.8995 0.0923
-4.500 -0.2882 0.02539 0.01615 -0.0496 0.8961 0.0973
-4.250 -0.2763 0.02507 0.01577 -0.0468 0.8868 0.1008
-4.000 -0.2437 0.02415 0.01487 -0.0479 0.8821 0.1107
-3.750 -0.2292 0.02378 0.01452 -0.0457 0.8741 0.1218
-3.500 -0.2074 0.02266 0.01389 -0.0449 0.8679 0.1855
-3.250 -0.2105 0.02110 0.01398 -0.0396 0.8604 0.5000
-3.000 -0.2010 0.02100 0.01463 -0.0345 0.8533 0.6809
-2.750 -0.1648 0.02132 0.01503 -0.0337 0.8499 0.7644
-2.500 -0.1586 0.02192 0.01562 -0.0291 0.8403 0.7994
-2.250 -0.1095 0.02259 0.01618 -0.0305 0.8369 0.8421
-2.000 -0.0117 0.02393 0.01729 -0.0394 0.8367 0.8810
-1.750 0.0602 0.02396 0.01708 -0.0469 0.8346 0.8938
-1.500 0.1242 0.02423 0.01717 -0.0538 0.8283 0.9023
-1.250 0.1823 0.02407 0.01686 -0.0593 0.8229 0.9130
-0.750 0.2866 0.02367 0.01620 -0.0684 0.8090 0.9343
-0.500 0.3412 0.02315 0.01554 -0.0732 0.8037 0.9438
-0.250 0.3767 0.02318 0.01553 -0.0754 0.7939 0.9560
0.000 0.4319 0.02261 0.01485 -0.0806 0.7883 0.9648
0.250 0.4726 0.02250 0.01472 -0.0839 0.7786 0.9754
0.500 0.5212 0.02195 0.01408 -0.0881 0.7727 0.9847
0.750 0.5636 0.02172 0.01386 -0.0919 0.7623 0.9947
1.000 0.6003 0.02136 0.01346 -0.0942 0.7547 1.0000
1.250 0.6148 0.02141 0.01351 -0.0924 0.7453 1.0000
1.500 0.6283 0.02154 0.01364 -0.0905 0.7360 1.0000
1.750 0.6478 0.02137 0.01343 -0.0891 0.7283 1.0000
2.000 0.6590 0.02160 0.01369 -0.0868 0.7179 1.0000
2.250 0.6801 0.02139 0.01344 -0.0856 0.7106 1.0000
2.500 0.6925 0.02154 0.01361 -0.0833 0.7000 1.0000
2.750 0.7063 0.02164 0.01374 -0.0811 0.6900 1.0000
3.000 0.7292 0.02137 0.01342 -0.0800 0.6824 1.0000
3.250 0.7400 0.02158 0.01370 -0.0773 0.6709 1.0000
3.500 0.7561 0.02161 0.01374 -0.0753 0.6612 1.0000
3.750 0.7784 0.02140 0.01349 -0.0741 0.6525 1.0000
4.000 0.7899 0.02161 0.01375 -0.0713 0.6409 1.0000
4.250 0.8063 0.02165 0.01383 -0.0693 0.6304 1.0000
4.500 0.8320 0.02139 0.01353 -0.0685 0.6218 1.0000
4.750 0.8433 0.02162 0.01383 -0.0656 0.6096 1.0000
5.000 0.8581 0.02179 0.01403 -0.0633 0.5982 1.0000
5.250 0.8809 0.02173 0.01398 -0.0621 0.5886 1.0000
5.500 0.9003 0.02180 0.01407 -0.0605 0.5780 1.0000
5.750 0.9134 0.02211 0.01445 -0.0580 0.5663 1.0000
6.000 0.9316 0.02232 0.01469 -0.0562 0.5559 1.0000
6.250 0.9590 0.02227 0.01464 -0.0558 0.5469 1.0000
6.500 0.9701 0.02277 0.01526 -0.0530 0.5356 1.0000
6.750 0.9872 0.02313 0.01569 -0.0511 0.5256 1.0000
7.000 1.0158 0.02316 0.01571 -0.0510 0.5171 1.0000
7.250 1.0287 0.02346 0.01614 -0.0483 0.5048 1.0000
7.500 1.0518 0.02291 0.01552 -0.0467 0.4880 1.0000
7.750 1.0627 0.02264 0.01526 -0.0432 0.4684 1.0000
8.000 1.0731 0.02250 0.01513 -0.0397 0.4492 1.0000
8.250 1.0843 0.02244 0.01504 -0.0364 0.4305 1.0000
8.500 1.0927 0.02254 0.01516 -0.0328 0.4120 1.0000
8.750 1.0912 0.02280 0.01547 -0.0276 0.3900 1.0000
9.000 1.0862 0.02312 0.01576 -0.0219 0.3648 1.0000
9.250 1.0715 0.02368 0.01622 -0.0148 0.3367 1.0000
9.500 1.0532 0.02470 0.01714 -0.0080 0.2999 1.0000
9.750 1.0312 0.02649 0.01864 -0.0020 0.2393 1.0000
10.000 1.0078 0.02914 0.02072 0.0027 0.1569 1.0000
10.250 0.9831 0.03256 0.02354 0.0066 0.1018 1.0000
10.500 0.9688 0.03560 0.02639 0.0094 0.0845 1.0000
10.750 0.9589 0.03845 0.02921 0.0115 0.0781 1.0000
11.000 0.9531 0.04111 0.03198 0.0131 0.0721 1.0000
11.250 0.9437 0.04417 0.03508 0.0145 0.0682 1.0000
11.500 0.9363 0.04714 0.03811 0.0157 0.0654 1.0000
11.750 0.9360 0.04949 0.04058 0.0168 0.0629 1.0000
12.000 0.9388 0.05155 0.04270 0.0181 0.0605 1.0000
12.250 0.9459 0.05313 0.04420 0.0195 0.0571 1.0000
12.500 0.9744 0.05308 0.04400 0.0219 0.0537 1.0000
12.750 1.0064 0.05349 0.04446 0.0234 0.0509 1.0000
13.000 1.0496 0.05405 0.04507 0.0245 0.0493 1.0000
13.250 1.0875 0.05560 0.04673 0.0250 0.0476 1.0000
13.500 1.1547 0.05961 0.05075 0.0233 0.0448 1.0000
13.750 1.1658 0.06259 0.05400 0.0241 0.0448 1.0000
14.000 1.1666 0.06534 0.05702 0.0256 0.0450 1.0000
14.250 1.1589 0.06768 0.05964 0.0272 0.0455 1.0000
14.500 1.1498 0.07065 0.06292 0.0285 0.0460 1.0000
14.750 1.1316 0.07409 0.06669 0.0296 0.0467 1.0000
15.000 1.1050 0.07834 0.07131 0.0300 0.0475 1.0000
15.250 1.0806 0.08308 0.07637 0.0297 0.0483 1.0000
15.500 1.0561 0.08842 0.08199 0.0288 0.0491 1.0000
15.750 1.0321 0.09409 0.08792 0.0272 0.0498 1.0000
16.000 1.0076 0.10032 0.09437 0.0249 0.0507 1.0000
16.250 0.9828 0.10702 0.10126 0.0220 0.0514 1.0000
16.500 0.9564 0.11458 0.10899 0.0182 0.0522 1.0000
16.750 0.9307 0.12269 0.11724 0.0138 0.0529 1.0000
17.000 0.9117 0.13071 0.12534 0.0099 0.0540 1.0000
17.250 0.9017 0.13751 0.13226 0.0065 0.0560 1.0000
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Polar data table (+)
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