MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 200,000 Max Cl/Cd: 63.5 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh102-il-200000.txt Download as CSV file: xf-mh102-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 102 16.99%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6527 0.11497 0.11053 -0.0425 1.0000 0.0269
-16.500 -0.6734 0.10690 0.10235 -0.0471 1.0000 0.0266
-16.250 -0.7014 0.09778 0.09304 -0.0527 1.0000 0.0265
-16.000 -0.7226 0.09033 0.08542 -0.0573 1.0000 0.0263
-15.750 -0.7387 0.08409 0.07903 -0.0611 1.0000 0.0261
-15.500 -0.7553 0.07805 0.07282 -0.0647 1.0000 0.0261
-15.250 -0.7660 0.07318 0.06780 -0.0674 1.0000 0.0260
-15.000 -0.7807 0.06791 0.06235 -0.0704 1.0000 0.0262
-14.750 -0.7912 0.06338 0.05764 -0.0728 1.0000 0.0264
-14.500 -0.7944 0.05994 0.05408 -0.0742 1.0000 0.0264
-14.250 -0.8021 0.05600 0.04996 -0.0760 1.0000 0.0267
-14.000 -0.8059 0.05268 0.04647 -0.0773 1.0000 0.0269
-13.750 -0.8000 0.05057 0.04437 -0.0769 1.0000 0.0275
-13.500 -0.7931 0.04871 0.04255 -0.0765 1.0000 0.0280
-13.250 -0.7900 0.04644 0.04025 -0.0767 1.0000 0.0286
-13.000 -0.7873 0.04417 0.03792 -0.0768 1.0000 0.0291
-12.750 -0.7864 0.04177 0.03545 -0.0769 1.0000 0.0298
-12.500 -0.7855 0.03948 0.03306 -0.0769 1.0000 0.0305
-12.250 -0.7855 0.03728 0.03082 -0.0764 1.0000 0.0313
-12.000 -0.7861 0.03526 0.02886 -0.0758 1.0000 0.0321
-11.750 -0.7893 0.03328 0.02686 -0.0748 1.0000 0.0330
-11.500 -0.7948 0.03155 0.02507 -0.0730 1.0000 0.0341
-11.250 -0.8021 0.03018 0.02361 -0.0700 1.0000 0.0349
-11.000 -0.8155 0.02910 0.02252 -0.0652 1.0000 0.0354
-10.750 -0.8286 0.02807 0.02156 -0.0603 1.0000 0.0368
-10.500 -0.8386 0.02729 0.02078 -0.0554 1.0000 0.0379
-10.250 -0.8510 0.02670 0.02012 -0.0500 1.0000 0.0396
-10.000 -0.8286 0.02518 0.01862 -0.0515 0.9943 0.0433
-9.750 -0.7951 0.02342 0.01682 -0.0547 0.9854 0.0510
-9.500 -0.7627 0.02161 0.01505 -0.0575 0.9763 0.0637
-9.250 -0.7301 0.01966 0.01330 -0.0605 0.9679 0.0904
-9.000 -0.6979 0.01853 0.01238 -0.0625 0.9574 0.1291
-8.750 -0.6549 0.01815 0.01198 -0.0657 0.9515 0.1568
-8.500 -0.6169 0.01799 0.01167 -0.0677 0.9416 0.1741
-8.250 -0.5790 0.01786 0.01148 -0.0697 0.9325 0.1880
-8.000 -0.5415 0.01773 0.01133 -0.0715 0.9226 0.1998
-7.750 -0.5091 0.01756 0.01107 -0.0723 0.9098 0.2098
-7.500 -0.4770 0.01750 0.01087 -0.0729 0.8971 0.2195
-7.000 -0.4206 0.01726 0.01046 -0.0725 0.8692 0.2362
-6.750 -0.3950 0.01707 0.01022 -0.0718 0.8544 0.2436
-6.500 -0.3691 0.01701 0.01007 -0.0712 0.8407 0.2512
-6.250 -0.3432 0.01677 0.00965 -0.0706 0.8279 0.2579
-6.000 -0.3177 0.01657 0.00945 -0.0699 0.8138 0.2639
-5.750 -0.2922 0.01643 0.00916 -0.0692 0.8004 0.2704
-5.500 -0.2660 0.01614 0.00874 -0.0686 0.7888 0.2762
-5.250 -0.2400 0.01593 0.00851 -0.0680 0.7759 0.2819
-5.000 -0.2141 0.01579 0.00824 -0.0674 0.7634 0.2884
-4.750 -0.1875 0.01553 0.00787 -0.0669 0.7525 0.2944
-4.500 -0.1615 0.01535 0.00767 -0.0664 0.7398 0.3005
-4.250 -0.1350 0.01525 0.00742 -0.0659 0.7288 0.3076
-4.000 -0.1085 0.01500 0.00714 -0.0655 0.7180 0.3141
-3.750 -0.0821 0.01486 0.00697 -0.0650 0.7063 0.3212
-3.500 -0.0551 0.01475 0.00669 -0.0646 0.6965 0.3289
-3.250 -0.0291 0.01457 0.00657 -0.0641 0.6849 0.3366
-3.000 -0.0020 0.01452 0.00638 -0.0637 0.6754 0.3455
-2.750 0.0243 0.01432 0.00623 -0.0633 0.6649 0.3537
-2.500 0.0512 0.01429 0.00609 -0.0629 0.6553 0.3641
-2.250 0.0776 0.01412 0.00597 -0.0625 0.6454 0.3739
-2.000 0.1044 0.01407 0.00586 -0.0621 0.6362 0.3854
-1.750 0.1309 0.01397 0.00578 -0.0617 0.6272 0.3971
-1.500 0.1575 0.01390 0.00571 -0.0613 0.6188 0.4100
-1.250 0.1840 0.01383 0.00565 -0.0609 0.6097 0.4248
-1.000 0.2109 0.01381 0.00560 -0.0606 0.6020 0.4411
-0.750 0.2369 0.01373 0.00559 -0.0601 0.5933 0.4579
-0.500 0.2639 0.01370 0.00555 -0.0598 0.5865 0.4774
-0.250 0.2894 0.01363 0.00560 -0.0593 0.5781 0.4990
0.000 0.3155 0.01356 0.00560 -0.0588 0.5709 0.5228
0.250 0.3413 0.01354 0.00567 -0.0582 0.5641 0.5505
0.500 0.3665 0.01347 0.00574 -0.0576 0.5566 0.5823
0.750 0.3923 0.01345 0.00579 -0.0569 0.5505 0.6200
1.000 0.4163 0.01340 0.00595 -0.0560 0.5435 0.6623
1.250 0.4406 0.01335 0.00605 -0.0549 0.5369 0.7094
1.750 0.4883 0.01337 0.00638 -0.0524 0.5247 0.8105
2.000 0.5143 0.01341 0.00651 -0.0514 0.5184 0.8607
2.250 0.5485 0.01358 0.00664 -0.0521 0.5128 0.9044
2.500 0.5890 0.01371 0.00686 -0.0543 0.5053 0.9385
2.750 0.6360 0.01388 0.00694 -0.0579 0.4985 0.9630
3.000 0.6852 0.01410 0.00711 -0.0621 0.4917 0.9806
3.250 0.7373 0.01423 0.00722 -0.0671 0.4841 0.9945
3.500 0.7723 0.01440 0.00725 -0.0688 0.4785 1.0000
3.750 0.7891 0.01458 0.00746 -0.0670 0.4728 1.0000
4.000 0.8081 0.01474 0.00760 -0.0655 0.4668 1.0000
4.250 0.8300 0.01493 0.00769 -0.0644 0.4617 1.0000
4.500 0.8505 0.01517 0.00794 -0.0631 0.4560 1.0000
4.750 0.8712 0.01535 0.00813 -0.0618 0.4498 1.0000
5.000 0.8945 0.01555 0.00824 -0.0609 0.4444 1.0000
5.250 0.9162 0.01581 0.00851 -0.0598 0.4386 1.0000
5.500 0.9375 0.01601 0.00873 -0.0586 0.4321 1.0000
5.750 0.9617 0.01621 0.00885 -0.0579 0.4265 1.0000
6.000 0.9835 0.01648 0.00916 -0.0569 0.4203 1.0000
6.250 1.0055 0.01669 0.00938 -0.0558 0.4137 1.0000
6.500 1.0307 0.01692 0.00952 -0.0553 0.4079 1.0000
6.750 1.0510 0.01719 0.00987 -0.0540 0.4011 1.0000
7.000 1.0736 0.01739 0.01007 -0.0531 0.3944 1.0000
7.250 1.0980 0.01768 0.01030 -0.0525 0.3884 1.0000
7.500 1.1172 0.01791 0.01064 -0.0511 0.3809 1.0000
7.750 1.1406 0.01814 0.01081 -0.0503 0.3745 1.0000
8.000 1.1607 0.01845 0.01118 -0.0491 0.3675 1.0000
8.250 1.1812 0.01868 0.01144 -0.0479 0.3602 1.0000
8.500 1.2036 0.01900 0.01171 -0.0471 0.3537 1.0000
8.750 1.2208 0.01928 0.01209 -0.0454 0.3458 1.0000
9.000 1.2433 0.01958 0.01229 -0.0445 0.3392 1.0000
9.250 1.2583 0.01992 0.01277 -0.0425 0.3314 1.0000
9.500 1.2771 0.02022 0.01304 -0.0412 0.3244 1.0000
9.750 1.2927 0.02063 0.01352 -0.0394 0.3170 1.0000
10.000 1.3079 0.02099 0.01389 -0.0375 0.3096 1.0000
10.250 1.3229 0.02144 0.01434 -0.0356 0.3025 1.0000
10.500 1.3326 0.02187 0.01483 -0.0329 0.2954 1.0000
10.750 1.3469 0.02237 0.01526 -0.0310 0.2887 1.0000
11.000 1.3528 0.02293 0.01594 -0.0279 0.2815 1.0000
11.250 1.3663 0.02351 0.01643 -0.0261 0.2749 1.0000
11.500 1.3722 0.02425 0.01729 -0.0234 0.2680 1.0000
11.750 1.3812 0.02497 0.01801 -0.0213 0.2613 1.0000
12.000 1.3901 0.02583 0.01889 -0.0193 0.2548 1.0000
12.250 1.3956 0.02677 0.01991 -0.0172 0.2483 1.0000
12.500 1.4081 0.02765 0.02070 -0.0159 0.2420 1.0000
12.750 1.4093 0.02889 0.02210 -0.0137 0.2357 1.0000
13.000 1.4165 0.02999 0.02318 -0.0122 0.2297 1.0000
13.250 1.4222 0.03130 0.02453 -0.0107 0.2238 1.0000
13.500 1.4244 0.03278 0.02611 -0.0092 0.2178 1.0000
13.750 1.4366 0.03386 0.02707 -0.0083 0.2120 1.0000
14.000 1.4331 0.03583 0.02924 -0.0069 0.2066 1.0000
14.250 1.4357 0.03753 0.03098 -0.0059 0.2013 1.0000
14.500 1.4438 0.03896 0.03236 -0.0051 0.1959 1.0000
14.750 1.4402 0.04126 0.03483 -0.0043 0.1908 1.0000
15.000 1.4425 0.04318 0.03677 -0.0037 0.1858 1.0000
15.250 1.4480 0.04494 0.03852 -0.0031 0.1808 1.0000
15.500 1.4430 0.04765 0.04139 -0.0028 0.1760 1.0000
15.750 1.4446 0.04981 0.04357 -0.0025 0.1713 1.0000
16.000 1.4492 0.05179 0.04555 -0.0022 0.1667 1.0000
16.250 1.4426 0.05499 0.04891 -0.0024 0.1623 1.0000
16.500 1.4425 0.05755 0.05151 -0.0026 0.1579 1.0000
16.750 1.4482 0.05952 0.05344 -0.0024 0.1534 1.0000
17.000 1.4393 0.06330 0.05741 -0.0031 0.1494 1.0000
17.250 1.4372 0.06631 0.06048 -0.0037 0.1453 1.0000
17.500 1.4465 0.06791 0.06198 -0.0036 0.1408 1.0000
17.750 1.4334 0.07253 0.06683 -0.0049 0.1374 1.0000
18.000 1.4286 0.07612 0.07051 -0.0059 0.1335 1.0000
18.250 1.4380 0.07771 0.07199 -0.0060 0.1293 1.0000
18.500 1.4258 0.08250 0.07697 -0.0076 0.1260 1.0000
18.750 1.4167 0.08696 0.08156 -0.0092 0.1224 1.0000
19.000 1.4183 0.08981 0.08441 -0.0101 0.1188 1.0000
19.250 1.4181 0.09294 0.08757 -0.0111 0.1153 1.0000
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