MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 500,000 Max Cl/Cd: 92.16 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mb253515sm-il-500000.txt Download as CSV file: xf-mb253515sm-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3184 0.09344 0.09137 -0.0517 1.0000 0.0268
-11.500 -0.5450 0.06339 0.06088 -0.0715 1.0000 0.0185
-11.250 -0.5697 0.05837 0.05577 -0.0735 1.0000 0.0184
-11.000 -0.5943 0.05442 0.05170 -0.0735 1.0000 0.0184
-10.750 -0.6158 0.05155 0.04874 -0.0716 1.0000 0.0183
-10.500 -0.6488 0.04899 0.04606 -0.0665 1.0000 0.0184
-10.250 -0.6589 0.04423 0.04101 -0.0667 0.9855 0.0183
-10.000 -0.6577 0.03878 0.03511 -0.0676 0.9711 0.0184
-9.750 -0.6474 0.03403 0.02979 -0.0684 0.9585 0.0187
-9.500 -0.6336 0.02920 0.02443 -0.0694 0.9450 0.0195
-9.250 -0.6057 0.02738 0.02245 -0.0710 0.9320 0.0200
-9.000 -0.5775 0.02692 0.02195 -0.0721 0.9172 0.0208
-8.750 -0.5578 0.02565 0.02046 -0.0714 0.9016 0.0215
-8.500 -0.5397 0.02471 0.01927 -0.0699 0.8873 0.0228
-8.250 -0.5220 0.02381 0.01808 -0.0682 0.8744 0.0237
-8.000 -0.5050 0.02216 0.01611 -0.0665 0.8632 0.0245
-7.750 -0.4829 0.02024 0.01407 -0.0660 0.8531 0.0254
-7.500 -0.4615 0.01959 0.01335 -0.0652 0.8435 0.0264
-7.250 -0.4392 0.01913 0.01281 -0.0644 0.8346 0.0277
-7.000 -0.4166 0.01847 0.01203 -0.0635 0.8255 0.0289
-6.750 -0.3929 0.01786 0.01127 -0.0628 0.8179 0.0299
-6.500 -0.3696 0.01741 0.01070 -0.0619 0.8095 0.0305
-6.250 -0.3463 0.01574 0.00895 -0.0615 0.8028 0.0322
-6.000 -0.3244 0.01513 0.00835 -0.0606 0.7948 0.0336
-5.750 -0.3018 0.01463 0.00777 -0.0597 0.7883 0.0348
-5.500 -0.2798 0.01413 0.00723 -0.0587 0.7810 0.0359
-5.250 -0.2576 0.01371 0.00673 -0.0577 0.7744 0.0371
-5.000 -0.2346 0.01339 0.00636 -0.0568 0.7678 0.0383
-4.750 -0.2114 0.01309 0.00599 -0.0560 0.7615 0.0390
-4.500 -0.1931 0.01241 0.00521 -0.0543 0.7557 0.0404
-4.250 -0.1722 0.01195 0.00472 -0.0531 0.7492 0.0422
-4.000 -0.1488 0.01168 0.00440 -0.0523 0.7436 0.0444
-3.750 -0.1250 0.01143 0.00411 -0.0515 0.7378 0.0465
-3.500 -0.1008 0.01122 0.00383 -0.0509 0.7319 0.0484
-3.250 -0.0764 0.01100 0.00352 -0.0502 0.7267 0.0515
-3.000 -0.0526 0.01073 0.00327 -0.0495 0.7208 0.0592
-2.750 -0.0409 0.00956 0.00283 -0.0469 0.7154 0.2494
-2.500 -0.0309 0.00850 0.00259 -0.0439 0.7097 0.4583
-2.250 -0.0139 0.00804 0.00250 -0.0417 0.7024 0.5597
-2.000 0.0074 0.00785 0.00244 -0.0403 0.6955 0.6190
-1.750 0.0297 0.00770 0.00242 -0.0391 0.6883 0.6637
-1.500 0.0536 0.00764 0.00240 -0.0382 0.6829 0.6980
-1.250 0.0775 0.00759 0.00242 -0.0373 0.6774 0.7307
-1.000 0.1027 0.00756 0.00242 -0.0366 0.6716 0.7515
-0.750 0.1285 0.00758 0.00240 -0.0362 0.6666 0.7694
-0.500 0.1538 0.00756 0.00243 -0.0356 0.6607 0.7874
-0.250 0.1794 0.00755 0.00245 -0.0350 0.6553 0.8051
0.000 0.2055 0.00759 0.00247 -0.0345 0.6504 0.8210
0.250 0.2313 0.00758 0.00249 -0.0341 0.6443 0.8337
0.500 0.2574 0.00760 0.00249 -0.0337 0.6386 0.8455
0.750 0.2845 0.00762 0.00252 -0.0335 0.6331 0.8560
1.000 0.3111 0.00763 0.00255 -0.0332 0.6270 0.8670
1.250 0.3373 0.00769 0.00256 -0.0329 0.6215 0.8786
1.500 0.3645 0.00770 0.00262 -0.0327 0.6149 0.8892
1.750 0.3925 0.00774 0.00266 -0.0327 0.6087 0.8994
2.000 0.4196 0.00779 0.00272 -0.0326 0.6025 0.9107
2.250 0.4485 0.00785 0.00279 -0.0328 0.5953 0.9212
2.500 0.4802 0.00795 0.00288 -0.0337 0.5883 0.9295
2.750 0.5080 0.00802 0.00295 -0.0337 0.5808 0.9396
3.000 0.5446 0.00814 0.00306 -0.0357 0.5731 0.9441
3.250 0.5783 0.00825 0.00317 -0.0370 0.5642 0.9502
3.500 0.6106 0.00836 0.00328 -0.0381 0.5552 0.9563
3.750 0.6490 0.00851 0.00340 -0.0406 0.5459 0.9590
4.000 0.6861 0.00864 0.00354 -0.0428 0.5347 0.9624
4.250 0.7170 0.00878 0.00367 -0.0436 0.5234 0.9686
4.500 0.7540 0.00893 0.00381 -0.0459 0.5110 0.9713
4.750 0.7910 0.00910 0.00396 -0.0481 0.4973 0.9741
5.000 0.8255 0.00928 0.00412 -0.0499 0.4819 0.9782
5.250 0.8571 0.00949 0.00431 -0.0510 0.4660 0.9833
5.500 0.8931 0.00974 0.00449 -0.0532 0.4445 0.9862
5.750 0.9263 0.01008 0.00471 -0.0549 0.4157 0.9903
6.000 0.9587 0.01043 0.00498 -0.0565 0.3910 0.9944
6.250 0.9935 0.01078 0.00524 -0.0586 0.3697 0.9978
6.500 1.0215 0.01110 0.00550 -0.0593 0.3494 1.0000
6.750 1.0312 0.01134 0.00570 -0.0561 0.3355 1.0000
7.000 1.0403 0.01161 0.00594 -0.0528 0.3198 1.0000
7.250 1.0489 0.01192 0.00619 -0.0493 0.3024 1.0000
7.500 1.0553 0.01231 0.00649 -0.0455 0.2810 1.0000
7.750 1.0567 0.01288 0.00688 -0.0408 0.2427 1.0000
8.000 1.0386 0.01395 0.00753 -0.0326 0.1770 1.0000
8.250 1.0082 0.01548 0.00858 -0.0227 0.0975 1.0000
8.500 0.9920 0.01702 0.00982 -0.0160 0.0455 1.0000
8.750 0.9932 0.01805 0.01081 -0.0122 0.0320 1.0000
9.000 0.9975 0.01905 0.01184 -0.0092 0.0273 1.0000
9.250 1.0069 0.01986 0.01271 -0.0070 0.0251 1.0000
9.500 1.0146 0.02083 0.01373 -0.0048 0.0234 1.0000
9.750 1.0138 0.02241 0.01537 -0.0019 0.0215 1.0000
10.000 1.0259 0.02326 0.01628 -0.0006 0.0205 1.0000
10.250 1.0334 0.02446 0.01755 0.0011 0.0196 1.0000
10.500 1.0387 0.02589 0.01904 0.0028 0.0188 1.0000
10.750 1.0454 0.02727 0.02047 0.0041 0.0180 1.0000
11.000 1.0470 0.02910 0.02238 0.0057 0.0175 1.0000
11.250 1.0420 0.03155 0.02491 0.0075 0.0169 1.0000
11.500 1.0415 0.03373 0.02718 0.0089 0.0164 1.0000
11.750 1.0452 0.03563 0.02915 0.0099 0.0161 1.0000
12.000 1.0499 0.03747 0.03107 0.0107 0.0157 1.0000
12.250 1.0525 0.03954 0.03321 0.0116 0.0154 1.0000
12.500 1.0558 0.04160 0.03534 0.0123 0.0151 1.0000
12.750 1.0595 0.04367 0.03748 0.0130 0.0146 1.0000
13.000 1.0626 0.04580 0.03968 0.0137 0.0144 1.0000
13.250 1.0671 0.04787 0.04179 0.0141 0.0139 1.0000
13.500 1.0703 0.05008 0.04402 0.0146 0.0134 1.0000
13.750 1.0728 0.05219 0.04616 0.0155 0.0131 1.0000
14.000 1.0777 0.05397 0.04799 0.0171 0.0127 1.0000
14.250 1.0861 0.05563 0.04972 0.0178 0.0127 1.0000
14.500 1.0920 0.05776 0.05197 0.0179 0.0124 1.0000
14.750 1.0999 0.05952 0.05383 0.0187 0.0122 1.0000
15.000 1.1058 0.06163 0.05604 0.0191 0.0120 1.0000
15.250 1.1131 0.06355 0.05807 0.0199 0.0118 1.0000
15.500 1.1178 0.06588 0.06052 0.0202 0.0115 1.0000
15.750 1.1230 0.06814 0.06292 0.0209 0.0115 1.0000
16.000 1.1252 0.07087 0.06578 0.0212 0.0114 1.0000
16.250 1.1255 0.07389 0.06896 0.0213 0.0114 1.0000
16.500 1.1235 0.07725 0.07245 0.0209 0.0111 1.0000
16.750 1.1204 0.08077 0.07611 0.0203 0.0110 1.0000
17.000 1.1174 0.08435 0.07980 0.0195 0.0107 1.0000
17.250 1.1011 0.09023 0.08600 0.0189 0.0112 1.0000
17.500 1.0928 0.09480 0.09071 0.0173 0.0110 1.0000
17.750 1.1075 0.09556 0.09131 0.0161 0.0103 1.0000
18.000 1.0965 0.10068 0.09660 0.0145 0.0103 1.0000
18.250 1.0851 0.10603 0.10212 0.0124 0.0103 1.0000
18.500 1.0454 0.11697 0.11348 0.0078 0.0107 1.0000
18.750 1.0054 0.12868 0.12552 0.0022 0.0111 1.0000
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Polar data table (+)
Polar graphs
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