MUE 139 (mue139-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MUE 139 (mue139-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.53 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mue139-il-1000000.txt Download as CSV file: xf-mue139-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MUE 139
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.3746 0.15382 0.15200 -0.0046 1.0000 0.0263
-14.000 -0.2602 0.14156 0.13988 -0.0177 1.0000 0.0290
-13.750 -0.9532 0.03517 0.03238 -0.0842 1.0000 0.0318
-13.500 -0.9623 0.03247 0.02950 -0.0826 1.0000 0.0320
-13.250 -0.9574 0.03086 0.02777 -0.0810 1.0000 0.0322
-13.000 -0.9541 0.02905 0.02581 -0.0790 1.0000 0.0323
-12.750 -0.9383 0.02839 0.02507 -0.0776 1.0000 0.0325
-12.500 -0.9419 0.02570 0.02214 -0.0749 1.0000 0.0328
-12.250 -0.9332 0.02425 0.02060 -0.0727 1.0000 0.0333
-12.000 -0.9189 0.02335 0.01964 -0.0708 1.0000 0.0335
-11.750 -0.9026 0.02265 0.01892 -0.0690 1.0000 0.0337
-11.500 -0.8824 0.02191 0.01813 -0.0679 0.9996 0.0340
-11.250 -0.8455 0.02107 0.01722 -0.0701 0.9971 0.0343
-11.000 -0.8088 0.02024 0.01631 -0.0723 0.9933 0.0347
-10.750 -0.7775 0.01941 0.01540 -0.0732 0.9874 0.0350
-10.500 -0.7446 0.01863 0.01453 -0.0745 0.9801 0.0354
-10.000 -0.6730 0.01705 0.01275 -0.0779 0.9535 0.0362
-9.750 -0.6134 0.01622 0.01177 -0.0845 0.9343 0.0366
-9.500 -0.5694 0.01574 0.01106 -0.0877 0.8875 0.0369
-9.250 -0.5507 0.01485 0.00990 -0.0861 0.8369 0.0375
-9.000 -0.5294 0.01452 0.00940 -0.0845 0.8002 0.0380
-8.750 -0.5064 0.01428 0.00903 -0.0833 0.7740 0.0384
-8.500 -0.4826 0.01402 0.00866 -0.0822 0.7536 0.0388
-8.250 -0.4580 0.01375 0.00830 -0.0813 0.7383 0.0392
-8.000 -0.4330 0.01347 0.00793 -0.0804 0.7256 0.0397
-7.750 -0.4079 0.01320 0.00756 -0.0796 0.7134 0.0402
-7.500 -0.3823 0.01291 0.00719 -0.0788 0.7024 0.0407
-7.250 -0.3566 0.01267 0.00685 -0.0780 0.6911 0.0412
-7.000 -0.3304 0.01246 0.00656 -0.0773 0.6789 0.0415
-6.750 -0.3064 0.01193 0.00595 -0.0763 0.6657 0.0424
-6.500 -0.2809 0.01166 0.00563 -0.0755 0.6523 0.0430
-6.250 -0.2545 0.01149 0.00540 -0.0748 0.6397 0.0437
-6.000 -0.2277 0.01133 0.00520 -0.0742 0.6283 0.0446
-5.750 -0.2012 0.01119 0.00499 -0.0735 0.6151 0.0454
-5.500 -0.1746 0.01105 0.00476 -0.0729 0.5997 0.0462
-5.250 -0.1478 0.01095 0.00457 -0.0722 0.5828 0.0467
-5.000 -0.1228 0.01059 0.00416 -0.0714 0.5652 0.0481
-4.750 -0.0965 0.01049 0.00398 -0.0707 0.5459 0.0491
-4.500 -0.0700 0.01043 0.00384 -0.0700 0.5256 0.0502
-4.250 -0.0434 0.01038 0.00370 -0.0694 0.5058 0.0514
-4.000 -0.0167 0.01036 0.00358 -0.0687 0.4881 0.0523
-3.750 0.0091 0.01016 0.00332 -0.0680 0.4732 0.0540
-3.500 0.0361 0.01010 0.00323 -0.0674 0.4611 0.0556
-3.250 0.0631 0.01008 0.00316 -0.0669 0.4500 0.0572
-3.000 0.0903 0.01006 0.00308 -0.0664 0.4402 0.0584
-2.750 0.1168 0.00991 0.00290 -0.0657 0.4320 0.0605
-2.500 0.1441 0.00986 0.00284 -0.0652 0.4248 0.0623
-2.250 0.1711 0.00985 0.00279 -0.0647 0.4171 0.0642
-2.000 0.1989 0.00982 0.00273 -0.0643 0.4117 0.0656
-1.750 0.2257 0.00970 0.00261 -0.0637 0.4055 0.0683
-1.500 0.2528 0.00972 0.00260 -0.0632 0.3987 0.0707
-1.250 0.2807 0.00969 0.00256 -0.0628 0.3940 0.0728
-1.000 0.3078 0.00961 0.00248 -0.0623 0.3883 0.0756
-0.750 0.3347 0.00962 0.00246 -0.0618 0.3815 0.0785
-0.500 0.3624 0.00961 0.00245 -0.0614 0.3765 0.0813
-0.250 0.3896 0.00956 0.00239 -0.0609 0.3704 0.0844
0.000 0.4164 0.00957 0.00239 -0.0604 0.3638 0.0881
0.250 0.4441 0.00957 0.00238 -0.0600 0.3588 0.0914
0.500 0.4712 0.00954 0.00235 -0.0595 0.3529 0.0956
0.750 0.4979 0.00957 0.00236 -0.0590 0.3461 0.1001
1.000 0.5255 0.00959 0.00237 -0.0586 0.3409 0.1036
1.250 0.5523 0.00957 0.00236 -0.0581 0.3347 0.1100
1.500 0.5788 0.00964 0.00240 -0.0575 0.3276 0.1154
1.750 0.6059 0.00962 0.00241 -0.0571 0.3226 0.1238
2.000 0.6325 0.00965 0.00244 -0.0566 0.3161 0.1334
2.250 0.6584 0.00966 0.00249 -0.0559 0.3098 0.1555
2.500 0.6827 0.00941 0.00258 -0.0551 0.3054 0.2861
2.750 0.7081 0.00937 0.00266 -0.0544 0.3003 0.3483
3.000 0.7284 0.00901 0.00280 -0.0529 0.2950 0.5513
3.250 0.8468 0.00830 0.00308 -0.0723 0.2879 1.0000
3.500 0.8712 0.00844 0.00317 -0.0714 0.2839 1.0000
3.750 0.8949 0.00862 0.00329 -0.0703 0.2792 1.0000
4.000 0.9197 0.00874 0.00339 -0.0695 0.2761 1.0000
4.250 0.9447 0.00884 0.00347 -0.0687 0.2727 1.0000
4.500 0.9692 0.00899 0.00358 -0.0678 0.2686 1.0000
4.750 0.9931 0.00917 0.00371 -0.0668 0.2647 1.0000
5.000 1.0168 0.00937 0.00387 -0.0658 0.2613 1.0000
5.250 1.0420 0.00947 0.00398 -0.0651 0.2597 1.0000
5.500 1.0670 0.00959 0.00410 -0.0643 0.2576 1.0000
5.750 1.0916 0.00973 0.00423 -0.0635 0.2551 1.0000
6.000 1.1158 0.00989 0.00437 -0.0627 0.2525 1.0000
6.250 1.1396 0.01008 0.00454 -0.0618 0.2497 1.0000
6.500 1.1625 0.01032 0.00475 -0.0607 0.2465 1.0000
6.750 1.1868 0.01048 0.00491 -0.0599 0.2448 1.0000
7.000 1.2117 0.01060 0.00505 -0.0592 0.2432 1.0000
7.250 1.2364 0.01074 0.00519 -0.0585 0.2410 1.0000
7.500 1.2605 0.01090 0.00535 -0.0577 0.2385 1.0000
7.750 1.2842 0.01109 0.00553 -0.0568 0.2360 1.0000
8.000 1.3071 0.01132 0.00574 -0.0558 0.2331 1.0000
8.250 1.3289 0.01160 0.00601 -0.0547 0.2298 1.0000
8.500 1.3536 0.01172 0.00616 -0.0540 0.2284 1.0000
8.750 1.3780 0.01186 0.00632 -0.0533 0.2262 1.0000
9.000 1.4018 0.01203 0.00650 -0.0525 0.2235 1.0000
9.250 1.4246 0.01224 0.00671 -0.0516 0.2205 1.0000
9.500 1.4463 0.01250 0.00696 -0.0506 0.2171 1.0000
9.750 1.4681 0.01276 0.00722 -0.0495 0.2139 1.0000
10.000 1.4918 0.01290 0.00740 -0.0488 0.2113 1.0000
10.250 1.5143 0.01310 0.00761 -0.0479 0.2075 1.0000
10.500 1.5350 0.01339 0.00787 -0.0467 0.2031 1.0000
10.750 1.5554 0.01368 0.00816 -0.0455 0.1989 1.0000
11.000 1.5770 0.01390 0.00840 -0.0445 0.1949 1.0000
11.250 1.5963 0.01422 0.00871 -0.0431 0.1899 1.0000
11.500 1.6130 0.01459 0.00907 -0.0413 0.1849 1.0000
11.750 1.6298 0.01488 0.00938 -0.0396 0.1801 1.0000
12.000 1.6434 0.01533 0.00980 -0.0373 0.1741 1.0000
12.250 1.6582 0.01575 0.01023 -0.0354 0.1688 1.0000
12.500 1.6714 0.01628 0.01074 -0.0333 0.1626 1.0000
12.750 1.6837 0.01688 0.01134 -0.0313 0.1569 1.0000
13.000 1.6965 0.01749 0.01195 -0.0295 0.1518 1.0000
13.250 1.7056 0.01832 0.01277 -0.0274 0.1464 1.0000
13.500 1.7183 0.01902 0.01350 -0.0258 0.1430 1.0000
13.750 1.7289 0.01988 0.01438 -0.0243 0.1394 1.0000
14.000 1.7358 0.02103 0.01554 -0.0226 0.1353 1.0000
14.250 1.7450 0.02213 0.01668 -0.0213 0.1321 1.0000
14.500 1.7548 0.02326 0.01785 -0.0203 0.1291 1.0000
14.750 1.7613 0.02471 0.01933 -0.0193 0.1261 1.0000
15.000 1.7658 0.02644 0.02110 -0.0184 0.1236 1.0000
15.250 1.7690 0.02836 0.02306 -0.0177 0.1207 1.0000
15.500 1.7774 0.02989 0.02466 -0.0173 0.1186 1.0000
15.750 1.7822 0.03180 0.02663 -0.0169 0.1168 1.0000
16.000 1.7824 0.03417 0.02905 -0.0166 0.1143 1.0000
16.250 1.7780 0.03709 0.03201 -0.0164 0.1117 1.0000
16.500 1.7720 0.04021 0.03521 -0.0163 0.1101 1.0000
16.750 1.7727 0.04271 0.03779 -0.0163 0.1086 1.0000
17.000 1.7713 0.04547 0.04063 -0.0164 0.1071 1.0000
17.250 1.7666 0.04865 0.04390 -0.0167 0.1059 1.0000
17.500 1.7570 0.05254 0.04785 -0.0172 0.1039 1.0000
17.750 1.7445 0.05685 0.05225 -0.0179 0.1025 1.0000
18.000 1.7259 0.06205 0.05752 -0.0190 0.1005 1.0000
18.250 1.7064 0.06744 0.06300 -0.0203 0.0989 1.0000
18.500 1.7002 0.07119 0.06684 -0.0211 0.0979 1.0000
18.750 1.6906 0.07541 0.07115 -0.0221 0.0966 1.0000
19.000 1.6779 0.08007 0.07589 -0.0233 0.0952 1.0000
19.250 1.6648 0.08480 0.08070 -0.0246 0.0940 1.0000
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Polar data table (+)
Polar graphs
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