MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 50,000 Max Cl/Cd: 25.36 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mb253515sm-il-50000-n5.txt Download as CSV file: xf-mb253515sm-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4184 0.10046 0.09353 -0.0545 1.0000 0.0582
-11.000 -0.4266 0.09463 0.08777 -0.0573 1.0000 0.0579
-10.750 -0.4406 0.08828 0.08148 -0.0608 1.0000 0.0575
-10.500 -0.4570 0.08263 0.07587 -0.0637 1.0000 0.0567
-10.250 -0.4785 0.07754 0.07082 -0.0657 1.0000 0.0559
-10.000 -0.5044 0.07339 0.06667 -0.0661 1.0000 0.0554
-9.750 -0.5314 0.07031 0.06365 -0.0643 1.0000 0.0548
-9.500 -0.5601 0.06825 0.06161 -0.0603 1.0000 0.0543
-9.250 -0.5885 0.06656 0.05992 -0.0552 1.0000 0.0541
-9.000 -0.6142 0.06496 0.05829 -0.0500 1.0000 0.0539
-8.750 -0.6376 0.06339 0.05664 -0.0449 1.0000 0.0538
-8.500 -0.6582 0.06166 0.05478 -0.0400 1.0000 0.0540
-8.250 -0.6526 0.05769 0.05037 -0.0407 0.9901 0.0546
-8.000 -0.6415 0.05377 0.04596 -0.0414 0.9798 0.0551
-7.750 -0.6264 0.05030 0.04193 -0.0418 0.9703 0.0558
-7.500 -0.6068 0.04727 0.03829 -0.0423 0.9619 0.0577
-7.250 -0.5898 0.04508 0.03541 -0.0417 0.9520 0.0599
-7.000 -0.5631 0.04209 0.03217 -0.0427 0.9456 0.0616
-6.750 -0.5359 0.03983 0.02967 -0.0433 0.9381 0.0633
-6.500 -0.5013 0.03792 0.02752 -0.0452 0.9331 0.0674
-6.250 -0.4753 0.03651 0.02580 -0.0451 0.9249 0.0709
-6.000 -0.4361 0.03497 0.02389 -0.0470 0.9200 0.0733
-5.750 -0.4016 0.03348 0.02237 -0.0482 0.9143 0.0759
-5.500 -0.3716 0.03239 0.02124 -0.0489 0.9077 0.0810
-5.250 -0.3342 0.03139 0.01997 -0.0508 0.9032 0.0875
-5.000 -0.3154 0.03053 0.01906 -0.0497 0.8942 0.0913
-4.750 -0.2849 0.02960 0.01799 -0.0506 0.8888 0.0977
-4.500 -0.2679 0.02893 0.01727 -0.0492 0.8798 0.1052
-4.250 -0.2408 0.02787 0.01632 -0.0496 0.8741 0.1268
-4.000 -0.2336 0.02643 0.01577 -0.0472 0.8649 0.2484
-3.750 -0.2221 0.02509 0.01574 -0.0442 0.8589 0.4933
-3.500 -0.2091 0.02512 0.01615 -0.0404 0.8503 0.6013
-3.250 -0.1815 0.02535 0.01646 -0.0388 0.8449 0.6818
-3.000 -0.1580 0.02614 0.01733 -0.0355 0.8384 0.7603
-2.750 -0.1217 0.02696 0.01799 -0.0346 0.8328 0.8099
-2.500 -0.0748 0.02712 0.01784 -0.0376 0.8289 0.8281
-2.250 -0.0420 0.02738 0.01788 -0.0384 0.8216 0.8454
-2.000 0.0012 0.02752 0.01776 -0.0411 0.8162 0.8615
-1.750 0.0515 0.02753 0.01750 -0.0451 0.8125 0.8759
-1.500 0.0854 0.02779 0.01761 -0.0467 0.8042 0.8907
-1.250 0.1337 0.02776 0.01736 -0.0507 0.7994 0.9036
-1.000 0.1723 0.02788 0.01734 -0.0532 0.7924 0.9171
-0.750 0.2194 0.02786 0.01717 -0.0572 0.7862 0.9284
-0.500 0.2676 0.02771 0.01687 -0.0613 0.7808 0.9390
-0.250 0.3040 0.02778 0.01686 -0.0637 0.7720 0.9513
0.000 0.3473 0.02757 0.01653 -0.0670 0.7657 0.9619
0.250 0.3851 0.02754 0.01644 -0.0696 0.7562 0.9728
0.500 0.4271 0.02734 0.01617 -0.0729 0.7480 0.9822
0.750 0.4689 0.02709 0.01587 -0.0761 0.7396 0.9914
1.000 0.5048 0.02702 0.01579 -0.0785 0.7300 1.0000
1.250 0.5251 0.02688 0.01559 -0.0774 0.7225 1.0000
1.500 0.5312 0.02722 0.01593 -0.0744 0.7116 1.0000
1.750 0.5446 0.02733 0.01601 -0.0722 0.7028 1.0000
2.000 0.5599 0.02738 0.01606 -0.0703 0.6941 1.0000
2.250 0.5666 0.02773 0.01641 -0.0672 0.6837 1.0000
2.500 0.5903 0.02754 0.01619 -0.0663 0.6770 1.0000
2.750 0.5931 0.02805 0.01672 -0.0626 0.6658 1.0000
3.000 0.6030 0.02833 0.01701 -0.0598 0.6560 1.0000
3.250 0.6238 0.02828 0.01696 -0.0584 0.6483 1.0000
3.500 0.6282 0.02879 0.01749 -0.0548 0.6372 1.0000
3.750 0.6440 0.02894 0.01767 -0.0528 0.6284 1.0000
4.000 0.6608 0.02907 0.01781 -0.0509 0.6193 1.0000
4.250 0.6676 0.02958 0.01835 -0.0476 0.6083 1.0000
4.500 0.6900 0.02957 0.01837 -0.0465 0.6003 1.0000
5.000 0.7108 0.03047 0.01936 -0.0410 0.5789 1.0000
5.250 0.7374 0.03037 0.01931 -0.0404 0.5714 1.0000
5.500 0.7467 0.03092 0.01991 -0.0376 0.5604 1.0000
5.750 0.7552 0.03154 0.02059 -0.0348 0.5496 1.0000
6.000 0.7880 0.03126 0.02041 -0.0350 0.5430 1.0000
6.250 0.7906 0.03218 0.02140 -0.0315 0.5313 1.0000
6.500 0.7999 0.03289 0.02219 -0.0289 0.5211 1.0000
6.750 0.8306 0.03275 0.02214 -0.0288 0.5141 1.0000
7.000 0.8316 0.03388 0.02339 -0.0254 0.5032 1.0000
7.250 0.8487 0.03439 0.02400 -0.0239 0.4948 1.0000
7.500 0.8661 0.03489 0.02462 -0.0224 0.4864 1.0000
7.750 0.8679 0.03609 0.02592 -0.0193 0.4772 1.0000
8.000 0.8975 0.03614 0.02613 -0.0192 0.4706 1.0000
8.250 0.8901 0.03786 0.02794 -0.0153 0.4608 1.0000
8.500 0.9256 0.03767 0.02798 -0.0158 0.4552 1.0000
8.750 0.9098 0.04006 0.03046 -0.0116 0.4453 1.0000
9.000 0.9477 0.03971 0.03035 -0.0121 0.4403 1.0000
9.250 0.9246 0.04285 0.03357 -0.0080 0.4302 1.0000
9.500 0.9563 0.04242 0.03337 -0.0075 0.4229 1.0000
9.750 0.9663 0.04224 0.03331 -0.0047 0.4061 1.0000
10.000 0.9837 0.04033 0.03140 -0.0013 0.3780 1.0000
10.250 0.9794 0.04137 0.03247 0.0018 0.3576 1.0000
10.500 0.9777 0.04220 0.03329 0.0046 0.3333 1.0000
10.750 0.9706 0.04407 0.03523 0.0068 0.3107 1.0000
11.000 0.9615 0.04638 0.03761 0.0087 0.2845 1.0000
11.250 0.9501 0.04917 0.04043 0.0101 0.2508 1.0000
11.500 0.9371 0.05229 0.04329 0.0114 0.1843 1.0000
11.750 0.9176 0.05626 0.04650 0.0124 0.1174 1.0000
12.000 0.8980 0.06106 0.05094 0.0126 0.0942 1.0000
12.250 0.8832 0.06568 0.05543 0.0124 0.0832 1.0000
12.500 0.8710 0.07019 0.05989 0.0121 0.0766 1.0000
12.750 0.8621 0.07443 0.06414 0.0117 0.0711 1.0000
13.000 0.8549 0.07850 0.06825 0.0112 0.0666 1.0000
13.250 0.8479 0.08258 0.07226 0.0107 0.0627 1.0000
13.500 0.8475 0.08581 0.07562 0.0104 0.0585 1.0000
13.750 0.8476 0.08898 0.07882 0.0102 0.0550 1.0000
14.000 0.8485 0.09184 0.08164 0.0102 0.0522 1.0000
14.250 0.8567 0.09377 0.08372 0.0109 0.0500 1.0000
14.500 0.8658 0.09568 0.08580 0.0114 0.0472 1.0000
14.750 0.8747 0.09764 0.08787 0.0119 0.0447 1.0000
15.000 0.8851 0.09929 0.08953 0.0126 0.0422 1.0000
15.250 0.9013 0.10031 0.09062 0.0140 0.0402 1.0000
15.500 0.9129 0.10249 0.09311 0.0146 0.0392 1.0000
15.750 0.9200 0.10545 0.09634 0.0145 0.0384 1.0000
16.000 0.9211 0.10934 0.10050 0.0135 0.0376 1.0000
16.250 0.9185 0.11388 0.10529 0.0120 0.0369 1.0000
16.500 0.9121 0.11911 0.11075 0.0099 0.0364 1.0000
16.750 0.9034 0.12497 0.11683 0.0071 0.0364 1.0000
17.000 0.8913 0.13168 0.12374 0.0037 0.0361 1.0000
17.250 0.8763 0.13942 0.13168 -0.0006 0.0362 1.0000
17.500 0.8585 0.14844 0.14087 -0.0057 0.0369 1.0000
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Polar data table (+)
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