MUE 139 (mue139-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MUE 139 (mue139-il) Reynolds number: 500,000 Max Cl/Cd: 89.2 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mue139-il-500000.txt Download as CSV file: xf-mue139-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2503 0.09267 0.09045 -0.0267 1.0000 0.0492
-8.750 -0.2431 0.08939 0.08719 -0.0290 0.9988 0.0504
-8.250 -0.4011 0.02432 0.01988 -0.0875 0.8690 0.0464
-8.000 -0.3880 0.02205 0.01704 -0.0859 0.8304 0.0469
-7.750 -0.3700 0.02072 0.01548 -0.0845 0.8025 0.0475
-7.500 -0.3482 0.02012 0.01473 -0.0833 0.7807 0.0479
-7.250 -0.3255 0.01961 0.01408 -0.0822 0.7635 0.0485
-7.000 -0.3028 0.01904 0.01335 -0.0812 0.7483 0.0491
-6.750 -0.2797 0.01842 0.01257 -0.0801 0.7340 0.0498
-6.500 -0.2567 0.01768 0.01164 -0.0791 0.7208 0.0506
-6.250 -0.2331 0.01706 0.01080 -0.0780 0.7074 0.0515
-5.750 -0.1856 0.01568 0.00909 -0.0760 0.6791 0.0534
-5.500 -0.1602 0.01533 0.00869 -0.0752 0.6659 0.0542
-5.250 -0.1347 0.01504 0.00832 -0.0744 0.6528 0.0551
-5.000 -0.1091 0.01470 0.00788 -0.0736 0.6391 0.0562
-4.750 -0.0833 0.01435 0.00741 -0.0729 0.6245 0.0574
-4.500 -0.0574 0.01408 0.00699 -0.0721 0.6086 0.0585
-4.250 -0.0326 0.01352 0.00636 -0.0712 0.5913 0.0600
-4.000 -0.0067 0.01339 0.00617 -0.0705 0.5724 0.0614
-3.750 0.0192 0.01326 0.00596 -0.0697 0.5531 0.0630
-3.500 0.0452 0.01312 0.00568 -0.0689 0.5342 0.0648
-3.250 0.0707 0.01284 0.00527 -0.0681 0.5167 0.0664
-3.000 0.0963 0.01265 0.00504 -0.0674 0.5012 0.0681
-2.750 0.1224 0.01260 0.00491 -0.0667 0.4876 0.0700
-2.500 0.1489 0.01253 0.00476 -0.0660 0.4757 0.0722
-2.250 0.1751 0.01236 0.00452 -0.0654 0.4653 0.0745
-2.000 0.2010 0.01226 0.00439 -0.0647 0.4554 0.0768
-1.750 0.2278 0.01220 0.00430 -0.0641 0.4468 0.0793
-1.500 0.2545 0.01219 0.00421 -0.0635 0.4386 0.0817
-1.250 0.2803 0.01199 0.00400 -0.0628 0.4316 0.0848
-1.000 0.3071 0.01194 0.00395 -0.0623 0.4244 0.0878
-0.750 0.3334 0.01196 0.00390 -0.0616 0.4174 0.0909
-0.500 0.3599 0.01180 0.00375 -0.0610 0.4112 0.0945
-0.250 0.3863 0.01174 0.00370 -0.0604 0.4046 0.0983
0.000 0.4124 0.01179 0.00368 -0.0598 0.3979 0.1021
0.250 0.4391 0.01165 0.00357 -0.0592 0.3918 0.1068
0.500 0.4654 0.01162 0.00354 -0.0586 0.3851 0.1118
0.750 0.4917 0.01167 0.00354 -0.0580 0.3787 0.1163
1.000 0.5180 0.01155 0.00347 -0.0574 0.3725 0.1235
1.250 0.5442 0.01158 0.00347 -0.0568 0.3662 0.1301
1.500 0.5699 0.01155 0.00346 -0.0561 0.3603 0.1398
1.750 0.5962 0.01150 0.00346 -0.0555 0.3544 0.1540
2.000 0.6210 0.01140 0.00349 -0.0547 0.3485 0.2015
2.250 0.6435 0.01110 0.00363 -0.0537 0.3432 0.3668
2.500 0.7513 0.00987 0.00391 -0.0706 0.3326 1.0000
2.750 0.7748 0.01008 0.00401 -0.0695 0.3273 1.0000
3.000 0.7997 0.01018 0.00410 -0.0687 0.3230 1.0000
3.250 0.8241 0.01033 0.00420 -0.0677 0.3186 1.0000
3.500 0.8479 0.01052 0.00431 -0.0667 0.3144 1.0000
3.750 0.8714 0.01076 0.00447 -0.0657 0.3102 1.0000
4.000 0.8963 0.01088 0.00460 -0.0648 0.3068 1.0000
4.250 0.9207 0.01103 0.00472 -0.0640 0.3030 1.0000
4.500 0.9447 0.01123 0.00487 -0.0630 0.2995 1.0000
4.750 0.9678 0.01150 0.00505 -0.0620 0.2955 1.0000
5.000 0.9922 0.01165 0.00521 -0.0611 0.2917 1.0000
5.250 1.0167 0.01179 0.00534 -0.0603 0.2878 1.0000
5.500 1.0407 0.01197 0.00550 -0.0594 0.2842 1.0000
5.750 1.0639 0.01222 0.00569 -0.0584 0.2809 1.0000
6.000 1.0867 0.01253 0.00595 -0.0573 0.2775 1.0000
6.250 1.1112 0.01269 0.00614 -0.0565 0.2753 1.0000
6.500 1.1352 0.01287 0.00634 -0.0557 0.2727 1.0000
6.750 1.1589 0.01306 0.00653 -0.0548 0.2697 1.0000
7.000 1.1820 0.01330 0.00675 -0.0539 0.2668 1.0000
7.250 1.2043 0.01361 0.00701 -0.0528 0.2637 1.0000
7.500 1.2268 0.01393 0.00732 -0.0518 0.2609 1.0000
7.750 1.2503 0.01411 0.00755 -0.0509 0.2588 1.0000
8.000 1.2734 0.01431 0.00778 -0.0500 0.2562 1.0000
8.250 1.2961 0.01453 0.00802 -0.0490 0.2534 1.0000
8.500 1.3179 0.01479 0.00827 -0.0480 0.2503 1.0000
8.750 1.3386 0.01515 0.00859 -0.0468 0.2471 1.0000
9.000 1.3601 0.01547 0.00893 -0.0457 0.2445 1.0000
9.250 1.3821 0.01567 0.00919 -0.0446 0.2420 1.0000
9.500 1.4035 0.01589 0.00946 -0.0435 0.2391 1.0000
9.750 1.4239 0.01614 0.00973 -0.0423 0.2360 1.0000
10.000 1.4426 0.01649 0.01005 -0.0408 0.2325 1.0000
10.250 1.4608 0.01690 0.01046 -0.0393 0.2292 1.0000
10.500 1.4802 0.01711 0.01075 -0.0379 0.2265 1.0000
10.750 1.4974 0.01735 0.01105 -0.0362 0.2230 1.0000
11.000 1.5126 0.01767 0.01138 -0.0341 0.2194 1.0000
11.250 1.5251 0.01816 0.01183 -0.0319 0.2154 1.0000
11.500 1.5422 0.01847 0.01222 -0.0303 0.2119 1.0000
11.750 1.5587 0.01881 0.01263 -0.0288 0.2076 1.0000
12.000 1.5724 0.01931 0.01313 -0.0270 0.2032 1.0000
12.250 1.5848 0.01993 0.01376 -0.0252 0.1988 1.0000
12.500 1.6006 0.02042 0.01432 -0.0239 0.1940 1.0000
12.750 1.6122 0.02116 0.01508 -0.0223 0.1891 1.0000
13.000 1.6223 0.02206 0.01599 -0.0208 0.1844 1.0000
13.250 1.6349 0.02288 0.01687 -0.0196 0.1794 1.0000
13.500 1.6422 0.02410 0.01809 -0.0183 0.1744 1.0000
13.750 1.6502 0.02538 0.01941 -0.0172 0.1700 1.0000
14.000 1.6585 0.02672 0.02081 -0.0163 0.1654 1.0000
14.250 1.6617 0.02856 0.02266 -0.0155 0.1610 1.0000
14.500 1.6653 0.03045 0.02460 -0.0148 0.1572 1.0000
14.750 1.6706 0.03228 0.02649 -0.0143 0.1534 1.0000
15.000 1.6715 0.03455 0.02880 -0.0140 0.1501 1.0000
15.250 1.6667 0.03743 0.03170 -0.0137 0.1468 1.0000
15.500 1.6675 0.03982 0.03417 -0.0134 0.1442 1.0000
15.750 1.6682 0.04227 0.03672 -0.0133 0.1416 1.0000
16.000 1.6648 0.04518 0.03970 -0.0134 0.1392 1.0000
16.250 1.6574 0.04859 0.04315 -0.0136 0.1367 1.0000
16.500 1.6473 0.05237 0.04695 -0.0139 0.1343 1.0000
16.750 1.6426 0.05567 0.05035 -0.0144 0.1319 1.0000
17.000 1.6394 0.05891 0.05369 -0.0149 0.1302 1.0000
17.250 1.6326 0.06270 0.05757 -0.0157 0.1275 1.0000
17.500 1.6241 0.06665 0.06157 -0.0165 0.1255 1.0000
17.750 1.6144 0.07076 0.06571 -0.0174 0.1234 1.0000
18.000 1.6065 0.07459 0.06957 -0.0182 0.1208 1.0000
18.250 1.6003 0.07851 0.07361 -0.0193 0.1191 1.0000
18.500 1.5940 0.08240 0.07760 -0.0203 0.1175 1.0000
18.750 1.5850 0.08672 0.08199 -0.0216 0.1153 1.0000
19.000 1.5774 0.09076 0.08608 -0.0228 0.1133 1.0000
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