MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 50,000 Max Cl/Cd: 31.7 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh18-il-50000-n5.txt Download as CSV file: xf-mh18-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 18 11.16%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4063 0.09652 0.09040 -0.0376 1.0000 0.0380
-9.250 -0.4042 0.09211 0.08606 -0.0401 1.0000 0.0378
-9.000 -0.4023 0.08790 0.08192 -0.0425 1.0000 0.0376
-8.750 -0.4006 0.08401 0.07810 -0.0448 1.0000 0.0371
-8.500 -0.4055 0.07945 0.07363 -0.0483 1.0000 0.0369
-8.250 -0.4160 0.07611 0.07039 -0.0493 1.0000 0.0366
-8.000 -0.4368 0.07433 0.06869 -0.0467 1.0000 0.0363
-7.750 -0.4516 0.07201 0.06639 -0.0454 0.9953 0.0361
-7.500 -0.4444 0.06654 0.06074 -0.0502 0.9822 0.0356
-7.250 -0.4366 0.06130 0.05525 -0.0539 0.9709 0.0352
-7.000 -0.4277 0.05652 0.05015 -0.0563 0.9607 0.0350
-6.750 -0.4174 0.05206 0.04529 -0.0577 0.9514 0.0349
-6.500 -0.4041 0.04775 0.04040 -0.0585 0.9434 0.0350
-6.250 -0.3929 0.04428 0.03643 -0.0577 0.9341 0.0354
-6.000 -0.3765 0.04087 0.03241 -0.0571 0.9269 0.0361
-5.750 -0.3584 0.03809 0.02892 -0.0559 0.9195 0.0378
-5.500 -0.3387 0.03605 0.02673 -0.0555 0.9132 0.0417
-5.250 -0.3170 0.03418 0.02447 -0.0547 0.9065 0.0464
-5.000 -0.2866 0.03177 0.02151 -0.0546 0.9023 0.0511
-4.750 -0.2674 0.03064 0.02023 -0.0534 0.8951 0.0615
-4.500 -0.2379 0.02903 0.01845 -0.0535 0.8906 0.0742
-4.250 -0.2140 0.02796 0.01735 -0.0530 0.8848 0.0958
-4.000 -0.1867 0.02687 0.01613 -0.0529 0.8795 0.1302
-3.750 -0.1571 0.02581 0.01523 -0.0536 0.8754 0.1841
-3.500 -0.1387 0.02507 0.01474 -0.0524 0.8687 0.2456
-3.250 -0.1176 0.02418 0.01427 -0.0515 0.8637 0.3426
-3.000 -0.1028 0.02331 0.01410 -0.0492 0.8581 0.4876
-2.750 0.0264 0.02232 0.01380 -0.0642 0.8628 0.8936
-2.500 0.0961 0.02256 0.01351 -0.0715 0.8613 0.9656
-2.250 0.1642 0.02239 0.01289 -0.0801 0.8586 1.0000
-2.000 0.1813 0.02257 0.01280 -0.0789 0.8513 1.0000
-1.750 0.1996 0.02277 0.01277 -0.0779 0.8448 1.0000
-1.500 0.2177 0.02301 0.01281 -0.0767 0.8378 1.0000
-1.250 0.2376 0.02324 0.01285 -0.0758 0.8316 1.0000
-1.000 0.2553 0.02354 0.01299 -0.0745 0.8244 1.0000
-0.750 0.2760 0.02378 0.01305 -0.0736 0.8183 1.0000
-0.500 0.2932 0.02413 0.01326 -0.0721 0.8108 1.0000
-0.250 0.3146 0.02438 0.01339 -0.0712 0.8048 1.0000
0.000 0.3316 0.02476 0.01367 -0.0697 0.7970 1.0000
0.250 0.3529 0.02503 0.01382 -0.0687 0.7908 1.0000
0.500 0.3704 0.02542 0.01413 -0.0672 0.7829 1.0000
0.750 0.3907 0.02574 0.01437 -0.0660 0.7761 1.0000
1.000 0.4100 0.02608 0.01466 -0.0647 0.7685 1.0000
1.250 0.4285 0.02647 0.01501 -0.0633 0.7607 1.0000
1.500 0.4505 0.02672 0.01522 -0.0623 0.7537 1.0000
1.750 0.4671 0.02718 0.01566 -0.0606 0.7448 1.0000
2.000 0.4923 0.02730 0.01576 -0.0599 0.7386 1.0000
2.250 0.5074 0.02783 0.01629 -0.0581 0.7288 1.0000
2.500 0.5300 0.02805 0.01655 -0.0570 0.7215 1.0000
2.750 0.5498 0.02838 0.01690 -0.0556 0.7127 1.0000
3.000 0.5669 0.02883 0.01738 -0.0540 0.7031 1.0000
3.250 0.5945 0.02878 0.01737 -0.0533 0.6968 1.0000
3.500 0.6097 0.02931 0.01795 -0.0514 0.6858 1.0000
3.750 0.6274 0.02971 0.01847 -0.0498 0.6755 1.0000
4.000 0.6565 0.02953 0.01837 -0.0491 0.6691 1.0000
4.250 0.6722 0.03001 0.01894 -0.0473 0.6574 1.0000
4.500 0.6892 0.03042 0.01944 -0.0455 0.6459 1.0000
4.750 0.7083 0.03070 0.01988 -0.0439 0.6351 1.0000
5.000 0.7359 0.03049 0.01980 -0.0430 0.6269 1.0000
5.250 0.7551 0.03071 0.02015 -0.0413 0.6152 1.0000
5.500 0.7726 0.03100 0.02059 -0.0395 0.6026 1.0000
5.750 0.7907 0.03124 0.02098 -0.0377 0.5898 1.0000
6.250 0.8289 0.03151 0.02164 -0.0342 0.5634 1.0000
6.500 0.8488 0.03153 0.02185 -0.0324 0.5495 1.0000
6.750 0.8696 0.03146 0.02196 -0.0306 0.5351 1.0000
7.000 0.8919 0.03124 0.02194 -0.0289 0.5201 1.0000
7.250 0.9129 0.03108 0.02196 -0.0270 0.5034 1.0000
7.500 0.9292 0.03123 0.02230 -0.0248 0.4843 1.0000
7.750 0.9540 0.03080 0.02211 -0.0230 0.4647 1.0000
8.000 0.9697 0.03100 0.02245 -0.0207 0.4418 1.0000
8.250 0.9865 0.03112 0.02266 -0.0183 0.4165 1.0000
8.500 0.9988 0.03152 0.02309 -0.0156 0.3886 1.0000
8.750 1.0052 0.03220 0.02377 -0.0125 0.3583 1.0000
9.000 1.0063 0.03314 0.02464 -0.0090 0.3278 1.0000
9.250 1.0040 0.03443 0.02586 -0.0057 0.2958 1.0000
9.500 0.9998 0.03607 0.02739 -0.0028 0.2615 1.0000
9.750 0.9950 0.03800 0.02917 -0.0004 0.2264 1.0000
10.000 0.9886 0.04031 0.03128 0.0017 0.1905 1.0000
10.250 0.9818 0.04294 0.03370 0.0035 0.1563 1.0000
10.500 0.9745 0.04588 0.03642 0.0049 0.1275 1.0000
10.750 0.9675 0.04901 0.03935 0.0061 0.1040 1.0000
11.000 0.9630 0.05207 0.04231 0.0071 0.0888 1.0000
11.250 0.9589 0.05524 0.04541 0.0081 0.0762 1.0000
11.500 0.9562 0.05833 0.04858 0.0088 0.0658 1.0000
11.750 0.9540 0.06144 0.05166 0.0094 0.0583 1.0000
12.000 0.9577 0.06412 0.05449 0.0105 0.0523 1.0000
12.250 0.9593 0.06702 0.05736 0.0113 0.0474 1.0000
12.500 0.9621 0.07004 0.06067 0.0118 0.0418 1.0000
12.750 0.9630 0.07308 0.06375 0.0120 0.0384 1.0000
13.000 0.9709 0.07603 0.06692 0.0132 0.0356 1.0000
13.250 0.9718 0.07987 0.07112 0.0133 0.0334 1.0000
13.500 0.9682 0.08406 0.07558 0.0127 0.0319 1.0000
13.750 0.9613 0.08874 0.08048 0.0116 0.0306 1.0000
14.000 0.9528 0.09365 0.08557 0.0099 0.0294 1.0000
14.250 0.9438 0.09892 0.09100 0.0080 0.0286 1.0000
14.500 0.9333 0.10479 0.09708 0.0056 0.0284 1.0000
14.750 0.9208 0.11135 0.10381 0.0025 0.0281 1.0000
15.000 0.9038 0.11954 0.11224 -0.0019 0.0285 1.0000
15.250 0.8736 0.13270 0.12568 -0.0093 0.0319 1.0000
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Polar data table (+)
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