MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 500,000 Max Cl/Cd: 73.37 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh27-il-500000.txt Download as CSV file: xf-mh27-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 27 11.99%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3923 0.08730 0.08526 -0.0494 0.9885 0.0149
-9.750 -0.3996 0.08177 0.07974 -0.0517 0.9876 0.0150
-9.500 -0.4100 0.07512 0.07310 -0.0551 0.9867 0.0150
-9.250 -0.4396 0.06294 0.06088 -0.0649 0.9854 0.0143
-9.000 -0.4673 0.05530 0.05311 -0.0685 0.9841 0.0141
-8.750 -0.5662 0.06299 0.06042 -0.0608 0.9834 0.0132
-8.500 -0.5915 0.06106 0.05842 -0.0540 0.9780 0.0132
-8.250 -0.6046 0.05678 0.05398 -0.0513 0.9745 0.0135
-8.000 -0.6019 0.05326 0.05028 -0.0505 0.9722 0.0138
-7.750 -0.6068 0.05113 0.04805 -0.0466 0.9681 0.0140
-7.500 -0.6086 0.04886 0.04566 -0.0431 0.9638 0.0143
-7.250 -0.6003 0.04645 0.04309 -0.0414 0.9613 0.0147
-7.000 -0.5878 0.04356 0.03998 -0.0403 0.9594 0.0154
-6.750 -0.5840 0.04131 0.03754 -0.0366 0.9555 0.0161
-6.500 -0.5812 0.03904 0.03505 -0.0324 0.9505 0.0169
-6.250 -0.5647 0.03672 0.03244 -0.0303 0.9480 0.0185
-5.250 -0.5029 0.02247 0.01625 -0.0171 0.9370 0.0080
-5.000 -0.4739 0.02175 0.01542 -0.0173 0.9352 0.0078
-4.750 -0.4435 0.02045 0.01395 -0.0177 0.9340 0.0076
-4.500 -0.4141 0.01902 0.01239 -0.0180 0.9330 0.0075
-4.250 -0.3841 0.01805 0.01132 -0.0185 0.9321 0.0075
-4.000 -0.3815 0.01696 0.01010 -0.0130 0.9253 0.0085
-3.750 -0.3565 0.01636 0.00943 -0.0124 0.9226 0.0095
-3.500 -0.3262 0.01594 0.00896 -0.0130 0.9209 0.0110
-3.250 -0.2984 0.01501 0.00826 -0.0130 0.9194 0.0615
-3.000 -0.2706 0.01408 0.00792 -0.0135 0.9183 0.1966
-2.750 -0.2737 0.01319 0.00770 -0.0074 0.9099 0.3549
-2.500 -0.2581 0.01215 0.00739 -0.0051 0.9071 0.5370
-2.250 -0.2395 0.01097 0.00753 -0.0025 0.9058 0.8387
-2.000 -0.1886 0.01138 0.00797 -0.0070 0.9059 0.8956
-1.750 -0.1524 0.01169 0.00819 -0.0082 0.9050 0.9167
-1.500 -0.0929 0.01219 0.00861 -0.0148 0.9053 0.9216
-1.250 -0.0583 0.01239 0.00875 -0.0159 0.9035 0.9303
-1.000 0.0130 0.01282 0.00910 -0.0252 0.9052 0.9317
-0.750 0.0795 0.01322 0.00944 -0.0334 0.9058 0.9342
-0.500 0.0964 0.01333 0.00953 -0.0308 0.8995 0.9432
-0.250 0.1468 0.01326 0.00942 -0.0357 0.8985 0.9441
0.000 0.1984 0.01314 0.00928 -0.0409 0.8980 0.9448
0.250 0.2496 0.01294 0.00906 -0.0459 0.8972 0.9456
0.500 0.3028 0.01271 0.00883 -0.0515 0.8969 0.9464
0.750 0.3553 0.01244 0.00857 -0.0568 0.8963 0.9472
1.000 0.4052 0.01208 0.00823 -0.0616 0.8950 0.9481
1.250 0.4532 0.01169 0.00785 -0.0660 0.8934 0.9491
1.750 0.5090 0.01124 0.00745 -0.0658 0.8814 0.9574
2.000 0.5525 0.01081 0.00705 -0.0692 0.8765 0.9580
2.250 0.5858 0.01048 0.00675 -0.0703 0.8653 0.9598
2.500 0.6168 0.01024 0.00654 -0.0710 0.8516 0.9621
2.750 0.6456 0.01002 0.00635 -0.0712 0.8303 0.9651
3.000 0.6899 0.00970 0.00592 -0.0747 0.7928 0.9654
3.250 0.7190 0.00980 0.00575 -0.0749 0.7350 0.9676
3.500 0.7347 0.01013 0.00582 -0.0723 0.6754 0.9714
3.750 0.7559 0.01043 0.00583 -0.0711 0.6120 0.9737
4.000 0.7725 0.01082 0.00596 -0.0690 0.5514 0.9771
4.250 0.7843 0.01126 0.00619 -0.0658 0.5009 0.9814
4.500 0.8011 0.01163 0.00632 -0.0639 0.4440 0.9842
4.750 0.8233 0.01200 0.00643 -0.0633 0.3842 0.9863
5.000 0.8443 0.01241 0.00662 -0.0624 0.3305 0.9886
5.250 0.8635 0.01289 0.00685 -0.0612 0.2750 0.9912
5.500 0.8816 0.01340 0.00714 -0.0597 0.2282 0.9937
5.750 0.9062 0.01379 0.00734 -0.0597 0.1865 0.9953
6.000 0.9301 0.01418 0.00759 -0.0596 0.1506 0.9969
6.250 0.9520 0.01465 0.00790 -0.0590 0.1178 0.9985
6.500 0.9751 0.01513 0.00824 -0.0587 0.0870 1.0000
6.750 0.9827 0.01559 0.00864 -0.0549 0.0681 1.0000
7.000 0.9893 0.01605 0.00904 -0.0509 0.0525 1.0000
7.250 0.9952 0.01656 0.00952 -0.0467 0.0410 1.0000
7.500 1.0006 0.01712 0.01006 -0.0425 0.0328 1.0000
7.750 1.0078 0.01757 0.01060 -0.0386 0.0288 1.0000
8.000 1.0163 0.01797 0.01100 -0.0351 0.0250 1.0000
8.250 1.0175 0.01880 0.01190 -0.0302 0.0215 1.0000
8.500 1.0260 0.01920 0.01239 -0.0267 0.0206 1.0000
8.750 1.0365 0.01951 0.01275 -0.0237 0.0182 1.0000
9.000 1.0436 0.02004 0.01329 -0.0202 0.0155 1.0000
9.250 1.0431 0.02099 0.01435 -0.0153 0.0136 1.0000
9.500 1.0548 0.02127 0.01471 -0.0125 0.0113 1.0000
9.750 1.0548 0.02225 0.01573 -0.0079 0.0092 1.0000
10.000 1.0535 0.02336 0.01697 -0.0030 0.0081 1.0000
10.250 1.0604 0.02395 0.01764 0.0004 0.0071 1.0000
10.500 1.0669 0.02455 0.01829 0.0037 0.0062 1.0000
10.750 1.0707 0.02532 0.01909 0.0072 0.0054 1.0000
11.000 1.0612 0.02710 0.02104 0.0128 0.0050 1.0000
11.250 1.0670 0.02782 0.02184 0.0160 0.0048 1.0000
11.500 1.0684 0.02891 0.02306 0.0197 0.0045 1.0000
11.750 1.0675 0.03024 0.02453 0.0236 0.0045 1.0000
12.000 1.0657 0.03168 0.02612 0.0274 0.0044 1.0000
12.250 1.0690 0.03262 0.02715 0.0304 0.0039 1.0000
12.500 1.0620 0.03467 0.02939 0.0345 0.0039 1.0000
12.750 1.0606 0.03613 0.03098 0.0376 0.0038 1.0000
13.000 1.0601 0.03749 0.03243 0.0403 0.0035 1.0000
13.250 1.0544 0.03953 0.03466 0.0433 0.0035 1.0000
13.500 1.0548 0.04087 0.03605 0.0453 0.0032 1.0000
13.750 1.0489 0.04306 0.03834 0.0475 0.0031 1.0000
14.000 1.0392 0.04588 0.04133 0.0495 0.0030 1.0000
14.250 1.0186 0.05011 0.04577 0.0512 0.0029 1.0000
14.500 1.0158 0.05273 0.04855 0.0521 0.0031 1.0000
14.750 1.0048 0.05648 0.05247 0.0524 0.0031 1.0000
15.000 0.9660 0.06438 0.06064 0.0511 0.0028 1.0000
15.250 0.9645 0.06762 0.06397 0.0502 0.0029 1.0000
15.500 0.9490 0.07327 0.06978 0.0482 0.0029 1.0000
15.750 0.9380 0.07867 0.07539 0.0461 0.0031 1.0000
16.000 0.9220 0.08508 0.08190 0.0429 0.0030 1.0000
16.250 0.8964 0.09378 0.09075 0.0386 0.0028 1.0000
16.500 0.8628 0.10510 0.10240 0.0332 0.0033 1.0000
16.750 0.8470 0.11276 0.11015 0.0293 0.0034 1.0000
17.000 0.7687 0.13679 0.13445 0.0182 0.0043 1.0000
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Polar data table (+)
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