MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 200,000 Max Cl/Cd: 69.98 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mb253515sm-il-200000.txt Download as CSV file: xf-mb253515sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3108 0.08871 0.08560 -0.0525 1.0000 0.0697
-10.500 -0.3296 0.08252 0.07948 -0.0554 1.0000 0.0723
-10.250 -0.3655 0.07319 0.07023 -0.0613 1.0000 0.0732
-10.000 -0.3905 0.06782 0.06492 -0.0623 1.0000 0.0728
-9.750 -0.4180 0.06463 0.06179 -0.0611 0.9982 0.0721
-9.500 -0.4453 0.05637 0.05340 -0.0681 0.9906 0.0718
-9.250 -0.5998 0.06155 0.05771 -0.0626 0.9811 0.0626
-9.000 -0.5619 0.05770 0.05415 -0.0653 0.9788 0.0658
-8.750 -0.5458 0.05432 0.05055 -0.0682 0.9710 0.0708
-8.500 -0.5473 0.04963 0.04540 -0.0694 0.9593 0.0775
-8.250 -0.5166 0.04649 0.04224 -0.0724 0.9559 0.0825
-7.250 -0.4494 0.02981 0.02279 -0.0671 0.9181 0.0501
-7.000 -0.4193 0.02824 0.02093 -0.0674 0.9114 0.0496
-6.750 -0.3950 0.02531 0.01776 -0.0671 0.9026 0.0505
-6.500 -0.3641 0.02329 0.01564 -0.0680 0.8962 0.0522
-6.250 -0.3383 0.02201 0.01425 -0.0676 0.8873 0.0533
-6.000 -0.3086 0.02086 0.01298 -0.0678 0.8806 0.0547
-5.750 -0.2849 0.02010 0.01215 -0.0670 0.8716 0.0572
-5.500 -0.2570 0.01923 0.01118 -0.0669 0.8651 0.0589
-5.250 -0.2344 0.01856 0.01045 -0.0659 0.8563 0.0602
-5.000 -0.2094 0.01793 0.00973 -0.0652 0.8499 0.0618
-4.750 -0.1930 0.01700 0.00884 -0.0633 0.8414 0.0648
-4.500 -0.1724 0.01641 0.00821 -0.0620 0.8349 0.0677
-4.250 -0.1538 0.01602 0.00777 -0.0603 0.8269 0.0709
-4.000 -0.1317 0.01566 0.00728 -0.0591 0.8206 0.0744
-3.750 -0.1128 0.01520 0.00682 -0.0575 0.8135 0.0831
-3.500 -0.0943 0.01459 0.00635 -0.0558 0.8068 0.1147
-3.250 -0.0976 0.01278 0.00600 -0.0507 0.8002 0.4301
-3.000 -0.0897 0.01218 0.00610 -0.0465 0.7931 0.5925
-2.750 -0.0683 0.01205 0.00612 -0.0446 0.7883 0.6660
-2.500 -0.0487 0.01210 0.00630 -0.0426 0.7811 0.7136
-2.250 -0.0247 0.01215 0.00636 -0.0413 0.7756 0.7490
-2.000 0.0002 0.01227 0.00646 -0.0401 0.7702 0.7781
-1.750 0.0235 0.01240 0.00661 -0.0387 0.7635 0.8036
-1.500 0.0510 0.01253 0.00668 -0.0378 0.7583 0.8272
-1.250 0.0747 0.01270 0.00685 -0.0363 0.7503 0.8482
-1.000 0.1039 0.01274 0.00680 -0.0360 0.7438 0.8630
-0.750 0.1338 0.01285 0.00686 -0.0361 0.7362 0.8737
-0.500 0.1666 0.01292 0.00685 -0.0368 0.7300 0.8835
-0.250 0.1962 0.01301 0.00686 -0.0369 0.7242 0.8946
0.000 0.2336 0.01315 0.00697 -0.0387 0.7173 0.9019
0.250 0.2686 0.01322 0.00692 -0.0399 0.7122 0.9108
0.500 0.3084 0.01338 0.00707 -0.0423 0.7046 0.9166
0.750 0.3426 0.01343 0.00705 -0.0435 0.6986 0.9254
1.000 0.3897 0.01357 0.00715 -0.0475 0.6917 0.9290
1.250 0.4302 0.01364 0.00718 -0.0501 0.6850 0.9354
1.500 0.4682 0.01370 0.00719 -0.0523 0.6782 0.9419
1.750 0.5105 0.01373 0.00720 -0.0554 0.6704 0.9468
2.000 0.5424 0.01377 0.00720 -0.0564 0.6636 0.9551
2.250 0.5854 0.01374 0.00717 -0.0597 0.6550 0.9592
2.500 0.6229 0.01375 0.00716 -0.0620 0.6472 0.9656
2.750 0.6599 0.01372 0.00712 -0.0641 0.6388 0.9717
3.000 0.6991 0.01369 0.00712 -0.0668 0.6293 0.9774
3.250 0.7359 0.01365 0.00702 -0.0689 0.6212 0.9835
3.500 0.7756 0.01356 0.00699 -0.0718 0.6100 0.9889
3.750 0.8133 0.01350 0.00695 -0.0743 0.5992 0.9947
4.000 0.8536 0.01337 0.00683 -0.0773 0.5881 0.9999
4.250 0.8716 0.01337 0.00683 -0.0758 0.5777 1.0000
4.500 0.8876 0.01340 0.00690 -0.0739 0.5662 1.0000
4.750 0.9039 0.01345 0.00696 -0.0720 0.5546 1.0000
5.000 0.9204 0.01350 0.00701 -0.0701 0.5429 1.0000
5.250 0.9371 0.01359 0.00705 -0.0682 0.5313 1.0000
5.500 0.9519 0.01370 0.00720 -0.0660 0.5185 1.0000
5.750 0.9666 0.01386 0.00738 -0.0637 0.5058 1.0000
6.000 0.9812 0.01404 0.00758 -0.0614 0.4929 1.0000
6.250 0.9944 0.01421 0.00773 -0.0587 0.4782 1.0000
6.500 1.0058 0.01438 0.00785 -0.0557 0.4609 1.0000
6.750 1.0162 0.01459 0.00798 -0.0526 0.4429 1.0000
7.000 1.0263 0.01484 0.00822 -0.0494 0.4250 1.0000
7.250 1.0368 0.01513 0.00850 -0.0463 0.4083 1.0000
7.500 1.0468 0.01545 0.00881 -0.0431 0.3919 1.0000
7.750 1.0552 0.01582 0.00914 -0.0397 0.3741 1.0000
8.000 1.0617 0.01623 0.00950 -0.0359 0.3555 1.0000
8.250 1.0649 0.01669 0.00993 -0.0316 0.3322 1.0000
8.500 1.0593 0.01725 0.01040 -0.0257 0.3024 1.0000
8.750 1.0423 0.01819 0.01106 -0.0182 0.2513 1.0000
9.000 1.0166 0.02007 0.01236 -0.0107 0.1637 1.0000
9.500 0.9767 0.02495 0.01646 -0.0001 0.0564 1.0000
9.750 0.9750 0.02668 0.01826 0.0027 0.0486 1.0000
10.000 0.9715 0.02864 0.02029 0.0053 0.0451 1.0000
10.250 0.9720 0.03043 0.02219 0.0072 0.0424 1.0000
10.500 0.9719 0.03236 0.02421 0.0090 0.0396 1.0000
10.750 0.9711 0.03442 0.02634 0.0105 0.0378 1.0000
11.000 0.9649 0.03700 0.02896 0.0122 0.0363 1.0000
11.250 0.9587 0.03966 0.03166 0.0139 0.0352 1.0000
11.500 0.9631 0.04152 0.03360 0.0150 0.0342 1.0000
11.750 0.9679 0.04335 0.03551 0.0162 0.0332 1.0000
12.000 0.9744 0.04506 0.03727 0.0173 0.0322 1.0000
12.250 0.9825 0.04667 0.03892 0.0184 0.0310 1.0000
12.500 0.9914 0.04824 0.04049 0.0193 0.0297 1.0000
12.750 1.0082 0.04927 0.04143 0.0209 0.0283 1.0000
13.000 1.0408 0.04985 0.04202 0.0226 0.0274 1.0000
13.250 1.0572 0.05132 0.04363 0.0235 0.0270 1.0000
13.500 1.0781 0.05289 0.04536 0.0245 0.0267 1.0000
13.750 1.0977 0.05479 0.04744 0.0253 0.0266 1.0000
14.000 1.1078 0.05713 0.04998 0.0262 0.0262 1.0000
14.250 1.1152 0.05965 0.05270 0.0269 0.0261 1.0000
14.500 1.1147 0.06242 0.05569 0.0276 0.0256 1.0000
14.750 1.1157 0.06559 0.05909 0.0283 0.0256 1.0000
15.000 1.1112 0.06898 0.06272 0.0287 0.0255 1.0000
15.250 1.1070 0.07293 0.06688 0.0291 0.0259 1.0000
15.500 1.0976 0.07720 0.07138 0.0291 0.0262 1.0000
15.750 1.0911 0.08203 0.07639 0.0289 0.0269 1.0000
16.000 1.1059 0.08492 0.07941 0.0294 0.0285 1.0000
16.250 1.0434 0.09308 0.08813 0.0264 0.0303 1.0000
16.500 1.0102 0.10101 0.09637 0.0234 0.0317 1.0000
16.750 0.9866 0.10825 0.10378 0.0204 0.0329 1.0000
17.000 0.9675 0.11568 0.11133 0.0177 0.0342 1.0000
17.250 0.8176 0.10881 0.10484 0.0175 0.0291 1.0000
17.500 0.7367 0.12438 0.12087 0.0063 0.0318 1.0000
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Polar data table (+)
Polar graphs
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