MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.13 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh27-il-1000000.txt Download as CSV file: xf-mh27-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3420 0.08448 0.08273 -0.0886 0.9840 0.0076
-10.500 -0.3411 0.07879 0.07705 -0.0930 0.9835 0.0075
-10.250 -0.3533 0.07369 0.07197 -0.0942 0.9801 0.0075
-10.000 -0.3664 0.06402 0.06224 -0.1033 0.9779 0.0075
-9.750 -0.3794 0.05819 0.05630 -0.1070 0.9760 0.0075
-9.500 -0.3929 0.05318 0.05115 -0.1082 0.9744 0.0075
-9.250 -0.3985 0.04955 0.04737 -0.1081 0.9732 0.0075
-9.000 -0.4029 0.04584 0.04347 -0.1070 0.9720 0.0075
-8.750 -0.4309 0.04523 0.04281 -0.0978 0.9657 0.0075
-8.500 -0.4390 0.04276 0.04015 -0.0934 0.9626 0.0076
-8.250 -0.4394 0.03973 0.03689 -0.0906 0.9608 0.0076
-8.000 -0.4334 0.03688 0.03379 -0.0886 0.9596 0.0076
-6.250 -0.4023 0.01728 0.01208 -0.0598 0.9427 0.0050
-5.500 -0.3531 0.01504 0.00956 -0.0526 0.9351 0.0043
-5.250 -0.3278 0.01389 0.00828 -0.0522 0.9343 0.0042
-5.000 -0.3001 0.01322 0.00753 -0.0524 0.9336 0.0042
-4.750 -0.2724 0.01258 0.00681 -0.0524 0.9330 0.0043
-4.500 -0.2426 0.01210 0.00627 -0.0530 0.9324 0.0045
-4.250 -0.2132 0.01150 0.00556 -0.0534 0.9318 0.0052
-4.000 -0.2204 0.01151 0.00555 -0.0457 0.9240 0.0071
-3.750 -0.1936 0.01092 0.00507 -0.0456 0.9227 0.0338
-3.500 -0.1649 0.01045 0.00477 -0.0460 0.9217 0.0754
-3.250 -0.1381 0.00977 0.00445 -0.0462 0.9207 0.1655
-3.000 -0.1184 0.00870 0.00408 -0.0451 0.9195 0.3484
-2.750 -0.1007 0.00780 0.00378 -0.0433 0.9182 0.5118
-2.500 -0.1078 0.00759 0.00378 -0.0356 0.9104 0.5746
-2.250 -0.0960 0.00689 0.00347 -0.0320 0.9079 0.6864
-2.000 -0.0801 0.00622 0.00333 -0.0291 0.9064 0.8236
-1.750 -0.0441 0.00612 0.00332 -0.0307 0.9058 0.8714
-1.500 -0.0094 0.00605 0.00323 -0.0321 0.9049 0.8868
-1.250 0.0072 0.00614 0.00332 -0.0294 0.8997 0.8980
-1.000 0.0368 0.00610 0.00326 -0.0297 0.8970 0.9056
-0.750 0.0730 0.00611 0.00325 -0.0315 0.8954 0.9118
-0.500 0.1073 0.00612 0.00324 -0.0327 0.8937 0.9183
-0.250 0.1563 0.00626 0.00336 -0.0373 0.8926 0.9210
0.000 0.2010 0.00630 0.00337 -0.0410 0.8911 0.9225
0.250 0.2004 0.00630 0.00337 -0.0345 0.8832 0.9304
0.500 0.2410 0.00629 0.00334 -0.0374 0.8803 0.9310
0.750 0.2822 0.00630 0.00334 -0.0403 0.8769 0.9315
1.000 0.3143 0.00641 0.00347 -0.0413 0.8697 0.9326
1.250 0.3598 0.00644 0.00347 -0.0453 0.8645 0.9329
1.500 0.3956 0.00656 0.00360 -0.0471 0.8540 0.9339
1.750 0.4327 0.00662 0.00365 -0.0491 0.8406 0.9351
2.000 0.4678 0.00666 0.00364 -0.0508 0.8193 0.9363
2.250 0.4958 0.00678 0.00362 -0.0508 0.7852 0.9384
2.500 0.4990 0.00694 0.00363 -0.0452 0.7482 0.9445
2.750 0.5235 0.00726 0.00376 -0.0446 0.7043 0.9457
3.000 0.5425 0.00762 0.00393 -0.0427 0.6558 0.9476
3.250 0.5588 0.00794 0.00409 -0.0404 0.6141 0.9501
3.500 0.5466 0.00807 0.00413 -0.0315 0.5873 0.9578
3.750 0.5682 0.00840 0.00427 -0.0304 0.5383 0.9591
4.000 0.5899 0.00872 0.00442 -0.0295 0.4938 0.9605
4.250 0.6116 0.00903 0.00457 -0.0285 0.4513 0.9621
4.500 0.6302 0.00933 0.00473 -0.0269 0.4106 0.9644
4.750 0.6255 0.00952 0.00484 -0.0200 0.3856 0.9706
5.000 0.6513 0.00988 0.00499 -0.0201 0.3379 0.9714
5.250 0.6762 0.01025 0.00517 -0.0201 0.2902 0.9722
5.500 0.7008 0.01060 0.00536 -0.0199 0.2498 0.9731
5.750 0.7248 0.01098 0.00558 -0.0197 0.2115 0.9741
6.000 0.7490 0.01134 0.00581 -0.0195 0.1784 0.9753
6.250 0.7716 0.01170 0.00605 -0.0189 0.1498 0.9768
6.500 0.7907 0.01207 0.00630 -0.0176 0.1230 0.9787
6.750 0.7954 0.01238 0.00656 -0.0130 0.1077 0.9829
7.000 0.8221 0.01274 0.00681 -0.0134 0.0844 0.9836
7.250 0.8482 0.01313 0.00711 -0.0137 0.0646 0.9842
7.500 0.8732 0.01353 0.00746 -0.0138 0.0482 0.9850
7.750 0.8966 0.01404 0.00788 -0.0135 0.0315 0.9858
8.000 0.9195 0.01452 0.00830 -0.0132 0.0215 0.9868
8.250 0.9437 0.01483 0.00864 -0.0130 0.0189 0.9879
8.500 0.9646 0.01535 0.00915 -0.0123 0.0143 0.9892
8.750 0.9876 0.01563 0.00946 -0.0119 0.0130 0.9905
9.000 1.0086 0.01600 0.00985 -0.0111 0.0113 0.9920
9.250 1.0263 0.01653 0.01039 -0.0097 0.0092 0.9938
9.500 1.0506 0.01686 0.01079 -0.0098 0.0076 0.9945
9.750 1.0721 0.01749 0.01141 -0.0093 0.0049 0.9953
10.000 1.0940 0.01802 0.01198 -0.0090 0.0037 0.9962
10.250 1.1102 0.01905 0.01312 -0.0076 0.0027 0.9973
10.500 1.1301 0.01968 0.01383 -0.0069 0.0025 0.9984
10.750 1.1495 0.02036 0.01459 -0.0062 0.0023 0.9993
11.000 1.1678 0.02107 0.01538 -0.0054 0.0021 1.0000
11.250 1.1751 0.02155 0.01591 -0.0021 0.0019 1.0000
11.500 1.1789 0.02226 0.01670 0.0016 0.0018 1.0000
11.750 1.1830 0.02296 0.01750 0.0053 0.0018 1.0000
12.000 1.1846 0.02384 0.01847 0.0093 0.0017 1.0000
12.250 1.1703 0.02571 0.02053 0.0155 0.0013 1.0000
12.500 1.1695 0.02676 0.02170 0.0195 0.0014 1.0000
12.750 1.1670 0.02799 0.02304 0.0236 0.0013 1.0000
13.000 1.1705 0.02887 0.02400 0.0267 0.0012 1.0000
13.250 1.1695 0.03006 0.02529 0.0302 0.0012 1.0000
13.500 1.1663 0.03147 0.02683 0.0338 0.0011 1.0000
13.750 1.1641 0.03287 0.02834 0.0370 0.0011 1.0000
14.000 1.1580 0.03464 0.03023 0.0403 0.0011 1.0000
14.250 1.1484 0.03683 0.03258 0.0436 0.0010 1.0000
14.500 1.1408 0.03902 0.03490 0.0462 0.0011 1.0000
14.750 1.1354 0.04124 0.03724 0.0483 0.0011 1.0000
15.000 1.1250 0.04418 0.04033 0.0501 0.0009 1.0000
15.250 1.1125 0.04763 0.04393 0.0513 0.0010 1.0000
15.500 1.0996 0.05148 0.04794 0.0517 0.0010 1.0000
15.750 1.0880 0.05557 0.05217 0.0515 0.0010 1.0000
16.000 1.0684 0.06113 0.05791 0.0504 0.0010 1.0000
16.250 1.0549 0.06632 0.06324 0.0487 0.0009 1.0000
16.500 1.0345 0.07299 0.07007 0.0461 0.0010 1.0000
16.750 1.0252 0.07815 0.07533 0.0437 0.0010 1.0000
17.000 0.9972 0.08691 0.08426 0.0397 0.0011 1.0000
17.250 0.9730 0.09541 0.09291 0.0356 0.0010 1.0000
17.500 0.9499 0.10389 0.10151 0.0316 0.0010 1.0000
17.750 0.9248 0.11297 0.11072 0.0274 0.0010 1.0000
18.000 0.9084 0.12045 0.11826 0.0240 0.0010 1.0000
18.250 0.8808 0.13050 0.12843 0.0194 0.0011 1.0000
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Polar data table (+)
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