MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 500,000 Max Cl/Cd: 83.63 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mb253515sm-il-500000-n5.txt Download as CSV file: xf-mb253515sm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7670 0.07431 0.07166 -0.0596 1.0000 0.0079
-15.000 -0.8087 0.06289 0.06001 -0.0671 1.0000 0.0078
-14.750 -0.8373 0.05499 0.05189 -0.0720 1.0000 0.0078
-14.500 -0.8591 0.04903 0.04573 -0.0749 1.0000 0.0078
-14.250 -0.8725 0.04473 0.04124 -0.0764 1.0000 0.0078
-14.000 -0.8843 0.04101 0.03733 -0.0769 1.0000 0.0079
-13.750 -0.8913 0.03807 0.03421 -0.0766 1.0000 0.0081
-13.500 -0.9006 0.03519 0.03112 -0.0756 1.0000 0.0082
-13.250 -0.9025 0.03317 0.02893 -0.0742 1.0000 0.0083
-13.000 -0.9040 0.03133 0.02694 -0.0724 1.0000 0.0084
-12.750 -0.9079 0.02956 0.02505 -0.0700 1.0000 0.0087
-12.500 -0.9062 0.02836 0.02376 -0.0675 1.0000 0.0088
-12.250 -0.9040 0.02738 0.02271 -0.0647 1.0000 0.0091
-12.000 -0.8998 0.02639 0.02163 -0.0621 0.9993 0.0092
-11.500 -0.8504 0.02440 0.01944 -0.0641 0.9718 0.0100
-11.250 -0.8155 0.02358 0.01852 -0.0669 0.9603 0.0107
-11.000 -0.7808 0.02220 0.01691 -0.0699 0.9468 0.0113
-10.750 -0.7445 0.02106 0.01563 -0.0730 0.9315 0.0121
-10.500 -0.7111 0.02053 0.01501 -0.0751 0.9129 0.0126
-10.250 -0.6876 0.02002 0.01436 -0.0750 0.8932 0.0131
-10.000 -0.6687 0.01971 0.01393 -0.0738 0.8759 0.0137
-9.750 -0.6516 0.01923 0.01331 -0.0722 0.8609 0.0144
-9.500 -0.6332 0.01880 0.01272 -0.0709 0.8477 0.0152
-9.250 -0.6152 0.01831 0.01209 -0.0694 0.8361 0.0159
-9.000 -0.5968 0.01794 0.01164 -0.0680 0.8255 0.0165
-8.750 -0.5769 0.01766 0.01129 -0.0668 0.8150 0.0171
-8.500 -0.5557 0.01748 0.01105 -0.0658 0.8059 0.0179
-8.000 -0.5144 0.01673 0.01008 -0.0636 0.7889 0.0197
-7.750 -0.4928 0.01644 0.00967 -0.0627 0.7810 0.0206
-7.500 -0.4702 0.01618 0.00932 -0.0618 0.7734 0.0211
-7.250 -0.4522 0.01546 0.00853 -0.0604 0.7665 0.0221
-7.000 -0.4305 0.01512 0.00816 -0.0595 0.7592 0.0231
-6.500 -0.3860 0.01450 0.00741 -0.0577 0.7459 0.0250
-6.250 -0.3641 0.01415 0.00699 -0.0568 0.7396 0.0258
-6.000 -0.3415 0.01383 0.00660 -0.0559 0.7337 0.0267
-5.750 -0.3183 0.01357 0.00627 -0.0552 0.7272 0.0275
-5.500 -0.2954 0.01330 0.00592 -0.0544 0.7217 0.0279
-5.250 -0.2739 0.01286 0.00542 -0.0533 0.7160 0.0286
-5.000 -0.2527 0.01243 0.00493 -0.0522 0.7102 0.0298
-4.750 -0.2296 0.01215 0.00460 -0.0514 0.7049 0.0310
-4.500 -0.2058 0.01190 0.00431 -0.0508 0.6993 0.0320
-4.250 -0.1817 0.01168 0.00402 -0.0501 0.6941 0.0327
-4.000 -0.1572 0.01147 0.00377 -0.0496 0.6890 0.0336
-3.750 -0.1324 0.01129 0.00354 -0.0491 0.6836 0.0345
-3.500 -0.1075 0.01113 0.00332 -0.0486 0.6785 0.0355
-3.250 -0.0822 0.01099 0.00313 -0.0482 0.6737 0.0365
-3.000 -0.0571 0.01082 0.00294 -0.0477 0.6684 0.0398
-2.750 -0.0319 0.01068 0.00278 -0.0472 0.6634 0.0443
-2.500 -0.0071 0.01051 0.00262 -0.0467 0.6572 0.0574
-2.250 0.0074 0.00957 0.00229 -0.0447 0.6494 0.2294
-2.000 0.0275 0.00910 0.00213 -0.0434 0.6412 0.3212
-1.750 0.0477 0.00870 0.00199 -0.0421 0.6335 0.4055
-1.500 0.0686 0.00835 0.00191 -0.0409 0.6275 0.4825
-1.250 0.0894 0.00806 0.00186 -0.0396 0.6219 0.5553
-1.000 0.1129 0.00795 0.00183 -0.0388 0.6168 0.5960
-0.750 0.1370 0.00783 0.00182 -0.0380 0.6113 0.6323
-0.500 0.1608 0.00774 0.00183 -0.0372 0.6057 0.6696
-0.250 0.1853 0.00769 0.00184 -0.0365 0.6001 0.6972
0.000 0.2102 0.00765 0.00186 -0.0359 0.5942 0.7231
0.250 0.2351 0.00764 0.00188 -0.0353 0.5886 0.7465
0.500 0.2610 0.00763 0.00189 -0.0349 0.5823 0.7617
0.750 0.2869 0.00764 0.00191 -0.0346 0.5758 0.7741
1.000 0.3129 0.00766 0.00194 -0.0342 0.5697 0.7862
1.250 0.3389 0.00768 0.00197 -0.0339 0.5629 0.7983
1.500 0.3646 0.00772 0.00201 -0.0335 0.5562 0.8104
1.750 0.3905 0.00775 0.00206 -0.0332 0.5484 0.8225
2.000 0.4162 0.00779 0.00211 -0.0328 0.5411 0.8350
2.250 0.4421 0.00783 0.00218 -0.0324 0.5330 0.8481
2.500 0.4679 0.00788 0.00225 -0.0321 0.5247 0.8606
2.750 0.4935 0.00796 0.00232 -0.0317 0.5151 0.8722
3.000 0.5200 0.00803 0.00241 -0.0315 0.5055 0.8835
3.250 0.5469 0.00812 0.00251 -0.0314 0.4957 0.8941
3.750 0.6017 0.00837 0.00274 -0.0316 0.4713 0.9161
4.000 0.6329 0.00853 0.00289 -0.0325 0.4585 0.9251
4.250 0.6634 0.00870 0.00305 -0.0334 0.4453 0.9341
4.500 0.6956 0.00892 0.00323 -0.0346 0.4304 0.9419
4.750 0.7269 0.00915 0.00343 -0.0357 0.4157 0.9491
5.000 0.7600 0.00939 0.00365 -0.0372 0.4023 0.9548
5.250 0.7901 0.00963 0.00386 -0.0380 0.3901 0.9617
5.500 0.8238 0.00989 0.00411 -0.0397 0.3777 0.9656
5.750 0.8523 0.01020 0.00437 -0.0403 0.3618 0.9721
6.000 0.8823 0.01055 0.00466 -0.0413 0.3442 0.9768
6.250 0.9104 0.01093 0.00498 -0.0419 0.3253 0.9826
6.500 0.9394 0.01133 0.00531 -0.0428 0.3065 0.9875
6.750 0.9687 0.01173 0.00564 -0.0437 0.2850 0.9923
7.000 0.9974 0.01221 0.00602 -0.0447 0.2606 0.9972
7.250 1.0171 0.01289 0.00651 -0.0440 0.2208 1.0000
7.500 1.0175 0.01350 0.00694 -0.0392 0.1869 1.0000
7.750 0.9989 0.01451 0.00762 -0.0309 0.1299 1.0000
8.000 0.9752 0.01593 0.00866 -0.0222 0.0631 1.0000
8.250 0.9758 0.01679 0.00942 -0.0181 0.0398 1.0000
8.500 0.9829 0.01749 0.01009 -0.0151 0.0294 1.0000
8.750 0.9918 0.01818 0.01078 -0.0126 0.0230 1.0000
9.000 1.0011 0.01892 0.01152 -0.0103 0.0185 1.0000
9.250 1.0122 0.01963 0.01228 -0.0084 0.0164 1.0000
9.500 1.0228 0.02043 0.01311 -0.0066 0.0148 1.0000
9.750 1.0326 0.02132 0.01404 -0.0047 0.0137 1.0000
10.000 1.0412 0.02235 0.01512 -0.0029 0.0124 1.0000
10.250 1.0515 0.02333 0.01616 -0.0014 0.0120 1.0000
10.500 1.0605 0.02443 0.01733 0.0000 0.0114 1.0000
10.750 1.0706 0.02551 0.01847 0.0013 0.0107 1.0000
11.000 1.0784 0.02681 0.01982 0.0026 0.0101 1.0000
11.250 1.0848 0.02826 0.02134 0.0039 0.0097 1.0000
11.500 1.0873 0.03008 0.02324 0.0053 0.0092 1.0000
11.750 1.0905 0.03191 0.02514 0.0064 0.0090 1.0000
12.000 1.0961 0.03360 0.02691 0.0074 0.0088 1.0000
12.250 1.1007 0.03543 0.02883 0.0082 0.0085 1.0000
12.500 1.1050 0.03733 0.03081 0.0090 0.0083 1.0000
12.750 1.1069 0.03952 0.03309 0.0097 0.0081 1.0000
13.000 1.1097 0.04170 0.03535 0.0102 0.0080 1.0000
13.250 1.1129 0.04389 0.03762 0.0106 0.0076 1.0000
13.500 1.1166 0.04609 0.03990 0.0109 0.0074 1.0000
13.750 1.1179 0.04861 0.04250 0.0111 0.0071 1.0000
14.000 1.1220 0.05089 0.04483 0.0112 0.0068 1.0000
14.250 1.1230 0.05356 0.04757 0.0112 0.0067 1.0000
14.500 1.1208 0.05664 0.05074 0.0112 0.0066 1.0000
14.750 1.1180 0.05987 0.05405 0.0110 0.0065 1.0000
15.000 1.1126 0.06343 0.05768 0.0108 0.0063 1.0000
15.250 1.1127 0.06643 0.06076 0.0105 0.0062 1.0000
15.500 1.1095 0.06983 0.06426 0.0102 0.0062 1.0000
15.750 1.1107 0.07279 0.06731 0.0097 0.0061 1.0000
16.000 1.1113 0.07584 0.07046 0.0093 0.0060 1.0000
16.250 1.1121 0.07892 0.07363 0.0087 0.0058 1.0000
16.500 1.1116 0.08218 0.07700 0.0081 0.0057 1.0000
16.750 1.1103 0.08550 0.08040 0.0076 0.0058 1.0000
17.000 1.1103 0.08877 0.08377 0.0068 0.0056 1.0000
17.250 1.1091 0.09218 0.08727 0.0061 0.0055 1.0000
17.500 1.1094 0.09554 0.09073 0.0051 0.0053 1.0000
17.750 1.1076 0.09905 0.09433 0.0043 0.0053 1.0000
18.000 1.1065 0.10265 0.09802 0.0032 0.0052 1.0000
18.250 1.1046 0.10636 0.10183 0.0021 0.0051 1.0000
18.500 1.1037 0.11003 0.10559 0.0007 0.0050 1.0000
18.750 1.1012 0.11387 0.10952 -0.0006 0.0050 1.0000
19.000 1.0983 0.11786 0.11361 -0.0021 0.0049 1.0000
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Polar data table (+)
Polar graphs
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