MUE 139 (mue139-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MUE 139 (mue139-il) Reynolds number: 100,000 Max Cl/Cd: 35.33 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mue139-il-100000.txt Download as CSV file: xf-mue139-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2126 0.09742 0.09278 -0.0251 1.0000 0.1229
-8.000 -0.2123 0.09529 0.09074 -0.0251 1.0000 0.1260
-7.750 -0.2314 0.09431 0.08993 -0.0263 1.0000 0.1295
-7.500 -0.2729 0.09519 0.09109 -0.0238 1.0000 0.1302
-7.250 -0.2766 0.09143 0.08740 -0.0318 0.9843 0.1317
-7.000 -0.2306 0.08676 0.08274 -0.0295 0.9812 0.1339
-6.750 -0.1923 0.08257 0.07854 -0.0343 0.9671 0.1385
-6.500 -0.1777 0.07649 0.07233 -0.0555 0.9394 0.1474
-6.250 -0.1346 0.07276 0.06866 -0.0528 0.9287 0.1507
-5.750 -0.0780 0.06433 0.06002 -0.0672 0.8860 0.1663
-5.500 -0.0481 0.06160 0.05721 -0.0681 0.8640 0.1718
-5.250 -0.0416 0.05834 0.05372 -0.0736 0.8385 0.1828
-5.000 -0.0205 0.05621 0.05156 -0.0715 0.8153 0.1867
-4.750 -0.0116 0.05384 0.04893 -0.0741 0.7939 0.2007
-4.500 0.0072 0.05203 0.04709 -0.0712 0.7725 0.2060
-4.250 0.0191 0.05000 0.04487 -0.0716 0.7528 0.2205
-4.000 0.0329 0.04843 0.04310 -0.0716 0.7338 0.2370
-3.750 0.0504 0.04662 0.04127 -0.0691 0.7150 0.2430
-3.500 0.0656 0.04496 0.03948 -0.0682 0.6975 0.2593
-3.250 0.0936 0.03377 0.02654 -0.0765 0.6900 0.1493
-3.000 0.1163 0.03155 0.02389 -0.0755 0.6750 0.1423
-2.750 0.1379 0.02966 0.02165 -0.0743 0.6593 0.1404
-2.500 0.1609 0.02834 0.01996 -0.0731 0.6446 0.1421
-2.250 0.1853 0.02715 0.01837 -0.0720 0.6316 0.1437
-2.000 0.2107 0.02618 0.01697 -0.0709 0.6191 0.1455
-1.750 0.2345 0.02510 0.01573 -0.0700 0.6056 0.1492
-1.500 0.2600 0.02439 0.01492 -0.0692 0.5938 0.1536
-1.250 0.2864 0.02376 0.01404 -0.0683 0.5825 0.1580
-1.000 0.3120 0.02343 0.01346 -0.0673 0.5702 0.1634
-0.750 0.3387 0.02262 0.01261 -0.0667 0.5603 0.1691
-0.500 0.3645 0.02228 0.01220 -0.0659 0.5489 0.1765
-0.250 0.3910 0.02187 0.01172 -0.0652 0.5393 0.1842
0.000 0.4172 0.02156 0.01139 -0.0645 0.5294 0.1934
0.250 0.4428 0.02130 0.01117 -0.0637 0.5198 0.2045
0.500 0.4691 0.02106 0.01090 -0.0629 0.5106 0.2185
0.750 0.4939 0.02095 0.01091 -0.0621 0.5013 0.2377
1.000 0.5206 0.02080 0.01085 -0.0614 0.4928 0.2714
1.250 0.6092 0.01886 0.01080 -0.0727 0.4798 1.0000
1.500 0.6348 0.01923 0.01084 -0.0719 0.4730 1.0000
1.750 0.6572 0.01973 0.01125 -0.0707 0.4652 1.0000
2.000 0.6810 0.02013 0.01149 -0.0697 0.4579 1.0000
2.250 0.7065 0.02061 0.01173 -0.0690 0.4520 1.0000
2.500 0.7274 0.02117 0.01231 -0.0677 0.4446 1.0000
2.750 0.7516 0.02164 0.01266 -0.0668 0.4390 1.0000
3.000 0.7774 0.02223 0.01304 -0.0662 0.4342 1.0000
3.250 0.7969 0.02291 0.01383 -0.0648 0.4279 1.0000
3.500 0.8200 0.02345 0.01431 -0.0639 0.4223 1.0000
3.750 0.8461 0.02395 0.01463 -0.0633 0.4178 1.0000
4.000 0.8658 0.02478 0.01552 -0.0620 0.4127 1.0000
4.250 0.8862 0.02556 0.01636 -0.0608 0.4076 1.0000
4.500 0.9096 0.02616 0.01691 -0.0600 0.4031 1.0000
4.750 0.9359 0.02673 0.01732 -0.0595 0.3992 1.0000
5.000 0.9523 0.02776 0.01851 -0.0580 0.3943 1.0000
5.250 0.9705 0.02871 0.01954 -0.0566 0.3895 1.0000
5.500 0.9934 0.02936 0.02016 -0.0558 0.3853 1.0000
5.750 1.0203 0.02987 0.02054 -0.0554 0.3816 1.0000
6.000 1.0344 0.03111 0.02193 -0.0537 0.3768 1.0000
6.250 1.0485 0.03226 0.02322 -0.0520 0.3717 1.0000
6.500 1.0722 0.03276 0.02369 -0.0513 0.3672 1.0000
6.750 1.1018 0.03305 0.02381 -0.0511 0.3635 1.0000
7.000 1.1081 0.03474 0.02574 -0.0488 0.3585 1.0000
7.250 1.1195 0.03601 0.02714 -0.0469 0.3532 1.0000
7.500 1.1454 0.03633 0.02740 -0.0464 0.3490 1.0000
7.750 1.1787 0.03642 0.02731 -0.0466 0.3455 1.0000
8.000 1.1683 0.03908 0.03035 -0.0429 0.3400 1.0000
8.250 1.1761 0.04054 0.03193 -0.0408 0.3350 1.0000
8.500 1.2087 0.04033 0.03162 -0.0408 0.3310 1.0000
8.750 1.2442 0.04030 0.03142 -0.0412 0.3274 1.0000
9.000 1.1963 0.04518 0.03682 -0.0348 0.3213 1.0000
9.250 1.2033 0.04654 0.03825 -0.0329 0.3167 1.0000
9.500 1.2603 0.04473 0.03625 -0.0345 0.3130 1.0000
9.750 1.2491 0.04741 0.03908 -0.0313 0.3086 1.0000
10.000 0.7796 0.10606 0.09846 -0.0433 0.2833 1.0000
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Polar data table (+)
Polar graphs
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