MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.78 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mb253515sm-il-1000000-n5.txt Download as CSV file: xf-mb253515sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8828 0.09441 0.09221 -0.0464 1.0000 0.0049
-17.500 -0.9460 0.07864 0.07619 -0.0555 1.0000 0.0048
-17.250 -0.9922 0.06686 0.06417 -0.0628 1.0000 0.0047
-17.000 -1.0097 0.06049 0.05766 -0.0666 1.0000 0.0048
-16.750 -1.0298 0.05413 0.05114 -0.0703 1.0000 0.0047
-16.500 -1.0437 0.04909 0.04595 -0.0728 1.0000 0.0047
-16.250 -1.0542 0.04485 0.04157 -0.0746 1.0000 0.0048
-16.000 -1.0551 0.04200 0.03865 -0.0755 1.0000 0.0049
-15.750 -1.0623 0.03866 0.03517 -0.0762 1.0000 0.0050
-15.500 -1.0650 0.03599 0.03239 -0.0764 1.0000 0.0050
-15.250 -1.0656 0.03372 0.03001 -0.0761 1.0000 0.0051
-15.000 -1.0634 0.03184 0.02802 -0.0755 1.0000 0.0052
-14.750 -1.0607 0.03012 0.02620 -0.0746 1.0000 0.0053
-14.500 -1.0574 0.02856 0.02455 -0.0733 1.0000 0.0053
-14.250 -1.0509 0.02734 0.02325 -0.0720 1.0000 0.0055
-14.000 -1.0464 0.02607 0.02189 -0.0703 1.0000 0.0056
-13.750 -1.0405 0.02498 0.02071 -0.0684 1.0000 0.0057
-13.500 -1.0360 0.02392 0.01956 -0.0660 1.0000 0.0058
-13.250 -1.0288 0.02313 0.01869 -0.0637 1.0000 0.0059
-13.000 -1.0191 0.02213 0.01760 -0.0619 0.9954 0.0059
-12.750 -0.9989 0.02107 0.01645 -0.0621 0.9791 0.0064
-12.500 -0.9634 0.02002 0.01531 -0.0652 0.9659 0.0066
-12.250 -0.9194 0.01898 0.01419 -0.0701 0.9541 0.0071
-12.000 -0.8735 0.01801 0.01311 -0.0752 0.9374 0.0074
-11.750 -0.8389 0.01734 0.01228 -0.0777 0.9104 0.0079
-11.500 -0.8229 0.01686 0.01163 -0.0761 0.8843 0.0081
-11.250 -0.8093 0.01649 0.01113 -0.0738 0.8645 0.0083
-11.000 -0.7969 0.01607 0.01059 -0.0712 0.8485 0.0086
-10.750 -0.7839 0.01568 0.01011 -0.0688 0.8342 0.0092
-10.500 -0.7672 0.01535 0.00971 -0.0670 0.8225 0.0097
-10.250 -0.7495 0.01501 0.00929 -0.0654 0.8117 0.0102
-10.000 -0.7304 0.01469 0.00891 -0.0640 0.8016 0.0109
-9.750 -0.7112 0.01436 0.00849 -0.0626 0.7923 0.0114
-9.500 -0.6913 0.01406 0.00812 -0.0614 0.7835 0.0121
-9.250 -0.6691 0.01384 0.00789 -0.0605 0.7755 0.0131
-8.750 -0.6249 0.01339 0.00735 -0.0588 0.7601 0.0145
-8.500 -0.6022 0.01320 0.00709 -0.0579 0.7527 0.0153
-8.250 -0.5790 0.01299 0.00683 -0.0573 0.7462 0.0158
-8.000 -0.5570 0.01271 0.00651 -0.0563 0.7393 0.0167
-7.750 -0.5326 0.01257 0.00635 -0.0558 0.7329 0.0175
-7.500 -0.5086 0.01240 0.00615 -0.0553 0.7263 0.0183
-7.250 -0.4845 0.01224 0.00595 -0.0547 0.7207 0.0191
-7.000 -0.4605 0.01203 0.00570 -0.0541 0.7147 0.0198
-6.750 -0.4361 0.01189 0.00550 -0.0536 0.7086 0.0204
-6.500 -0.4112 0.01174 0.00531 -0.0531 0.7032 0.0209
-6.250 -0.3860 0.01161 0.00513 -0.0527 0.6977 0.0212
-5.750 -0.3412 0.01092 0.00435 -0.0509 0.6871 0.0230
-5.500 -0.3168 0.01072 0.00412 -0.0504 0.6815 0.0238
-5.250 -0.2923 0.01055 0.00390 -0.0499 0.6766 0.0245
-5.000 -0.2671 0.01036 0.00368 -0.0494 0.6716 0.0252
-4.750 -0.2421 0.01019 0.00347 -0.0490 0.6662 0.0258
-4.500 -0.2171 0.01004 0.00327 -0.0485 0.6615 0.0265
-4.250 -0.1913 0.00989 0.00310 -0.0482 0.6568 0.0271
-4.000 -0.1658 0.00974 0.00291 -0.0478 0.6517 0.0274
-3.750 -0.1404 0.00963 0.00275 -0.0474 0.6469 0.0277
-3.500 -0.1144 0.00950 0.00259 -0.0471 0.6415 0.0280
-3.250 -0.0890 0.00938 0.00242 -0.0467 0.6340 0.0285
-3.000 -0.0635 0.00926 0.00226 -0.0463 0.6252 0.0295
-2.750 -0.0382 0.00917 0.00212 -0.0459 0.6162 0.0311
-2.500 -0.0122 0.00906 0.00201 -0.0456 0.6093 0.0333
-2.250 0.0137 0.00899 0.00191 -0.0453 0.6033 0.0358
-2.000 0.0398 0.00888 0.00182 -0.0450 0.5988 0.0434
-1.750 0.0630 0.00856 0.00167 -0.0443 0.5930 0.1036
-1.250 0.1023 0.00749 0.00138 -0.0417 0.5824 0.3388
-1.000 0.1244 0.00716 0.00130 -0.0407 0.5770 0.4169
-0.750 0.1480 0.00697 0.00126 -0.0400 0.5716 0.4695
-0.500 0.1722 0.00679 0.00123 -0.0394 0.5652 0.5187
-0.250 0.1962 0.00667 0.00121 -0.0387 0.5590 0.5618
0.000 0.2210 0.00657 0.00121 -0.0382 0.5534 0.5990
0.250 0.2456 0.00649 0.00122 -0.0376 0.5467 0.6339
0.500 0.2700 0.00642 0.00123 -0.0370 0.5404 0.6680
0.750 0.2944 0.00637 0.00126 -0.0363 0.5324 0.7018
1.000 0.3198 0.00637 0.00129 -0.0359 0.5255 0.7199
1.250 0.3461 0.00640 0.00132 -0.0356 0.5177 0.7322
1.500 0.3717 0.00643 0.00136 -0.0353 0.5094 0.7447
1.750 0.3972 0.00648 0.00140 -0.0349 0.4996 0.7568
2.000 0.4230 0.00651 0.00145 -0.0345 0.4906 0.7689
2.250 0.4484 0.00657 0.00151 -0.0341 0.4812 0.7806
2.500 0.4733 0.00665 0.00158 -0.0337 0.4694 0.7926
2.750 0.4980 0.00672 0.00165 -0.0331 0.4570 0.8057
3.000 0.5223 0.00680 0.00173 -0.0325 0.4443 0.8197
3.250 0.5466 0.00689 0.00183 -0.0319 0.4322 0.8331
3.500 0.5707 0.00700 0.00193 -0.0312 0.4191 0.8452
3.750 0.5944 0.00714 0.00204 -0.0306 0.4043 0.8568
4.000 0.6182 0.00726 0.00217 -0.0299 0.3919 0.8690
4.250 0.6420 0.00739 0.00230 -0.0292 0.3803 0.8812
4.500 0.6667 0.00751 0.00243 -0.0287 0.3699 0.8938
4.750 0.6919 0.00765 0.00258 -0.0284 0.3599 0.9070
5.250 0.7480 0.00796 0.00291 -0.0290 0.3416 0.9332
5.500 0.7794 0.00822 0.00314 -0.0302 0.3258 0.9446
5.750 0.8134 0.00851 0.00338 -0.0320 0.3096 0.9527
6.000 0.8458 0.00879 0.00361 -0.0334 0.2946 0.9608
6.250 0.8807 0.00910 0.00387 -0.0355 0.2786 0.9653
6.500 0.9119 0.00949 0.00416 -0.0368 0.2538 0.9707
6.750 0.9390 0.01006 0.00454 -0.0374 0.2199 0.9763
7.000 0.9595 0.01084 0.00508 -0.0368 0.1729 0.9843
7.250 0.9642 0.01297 0.00654 -0.0343 0.0494 0.9953
7.500 0.9899 0.01363 0.00711 -0.0348 0.0286 0.9997
7.750 0.9967 0.01397 0.00742 -0.0311 0.0223 1.0000
8.000 1.0029 0.01432 0.00776 -0.0272 0.0177 1.0000
8.250 1.0122 0.01469 0.00813 -0.0241 0.0150 1.0000
8.500 1.0230 0.01511 0.00855 -0.0214 0.0128 1.0000
8.750 1.0359 0.01552 0.00899 -0.0192 0.0119 1.0000
9.000 1.0483 0.01601 0.00950 -0.0170 0.0109 1.0000
9.250 1.0606 0.01655 0.01006 -0.0149 0.0100 1.0000
9.500 1.0723 0.01718 0.01072 -0.0129 0.0092 1.0000
9.750 1.0854 0.01778 0.01136 -0.0112 0.0087 1.0000
10.000 1.0988 0.01842 0.01203 -0.0097 0.0083 1.0000
10.250 1.1116 0.01913 0.01278 -0.0081 0.0080 1.0000
10.500 1.1236 0.01992 0.01362 -0.0067 0.0077 1.0000
10.750 1.1361 0.02073 0.01446 -0.0053 0.0072 1.0000
11.000 1.1467 0.02171 0.01548 -0.0039 0.0069 1.0000
11.250 1.1556 0.02284 0.01666 -0.0025 0.0064 1.0000
11.500 1.1641 0.02407 0.01794 -0.0012 0.0062 1.0000
11.750 1.1765 0.02504 0.01895 -0.0003 0.0061 1.0000
12.000 1.1865 0.02623 0.02019 0.0007 0.0059 1.0000
12.250 1.1957 0.02752 0.02154 0.0017 0.0057 1.0000
12.500 1.2038 0.02893 0.02302 0.0027 0.0056 1.0000
12.750 1.2114 0.03042 0.02457 0.0035 0.0054 1.0000
13.000 1.2190 0.03194 0.02615 0.0043 0.0053 1.0000
13.250 1.2262 0.03354 0.02779 0.0050 0.0050 1.0000
13.500 1.2312 0.03536 0.02968 0.0057 0.0050 1.0000
13.750 1.2363 0.03723 0.03160 0.0063 0.0047 1.0000
14.000 1.2408 0.03922 0.03364 0.0068 0.0046 1.0000
14.250 1.2427 0.04152 0.03602 0.0072 0.0045 1.0000
14.500 1.2432 0.04403 0.03860 0.0076 0.0045 1.0000
14.750 1.2395 0.04705 0.04172 0.0079 0.0043 1.0000
15.000 1.2430 0.04940 0.04415 0.0080 0.0042 1.0000
15.250 1.2432 0.05215 0.04698 0.0080 0.0042 1.0000
15.500 1.2416 0.05517 0.05008 0.0079 0.0041 1.0000
15.750 1.2445 0.05774 0.05272 0.0077 0.0041 1.0000
16.000 1.2400 0.06125 0.05632 0.0074 0.0041 1.0000
16.250 1.2409 0.06413 0.05929 0.0070 0.0040 1.0000
16.500 1.2390 0.06743 0.06266 0.0066 0.0039 1.0000
16.750 1.2415 0.07021 0.06551 0.0060 0.0038 1.0000
17.000 1.2375 0.07390 0.06929 0.0054 0.0038 1.0000
17.250 1.2287 0.07825 0.07374 0.0045 0.0038 1.0000
17.500 1.2316 0.08110 0.07665 0.0038 0.0036 1.0000
17.750 1.2287 0.08478 0.08041 0.0029 0.0036 1.0000
18.000 1.2191 0.08942 0.08515 0.0017 0.0036 1.0000
18.250 1.2159 0.09324 0.08905 0.0006 0.0035 1.0000
18.500 1.2193 0.09615 0.09202 -0.0004 0.0034 1.0000
18.750 1.2114 0.10065 0.09661 -0.0017 0.0034 1.0000
19.000 1.2064 0.10481 0.10085 -0.0030 0.0033 1.0000
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Polar data table (+)
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