MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 200,000 Max Cl/Cd: 74.2 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh18-il-200000-n5.txt Download as CSV file: xf-mh18-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4220 0.08611 0.08282 -0.0284 0.8737 0.0096
-9.000 -0.4265 0.08157 0.07828 -0.0305 0.8637 0.0097
-8.750 -0.4318 0.07721 0.07392 -0.0327 0.8542 0.0088
-8.500 -0.4427 0.07174 0.06846 -0.0364 0.8449 0.0094
-8.250 -0.4601 0.06607 0.06275 -0.0399 0.8352 0.0083
-8.000 -0.4697 0.06071 0.05729 -0.0421 0.8269 0.0091
-7.750 -0.4784 0.05477 0.05116 -0.0432 0.8204 0.0087
-7.500 -0.4829 0.04857 0.04470 -0.0436 0.8134 0.0088
-7.250 -0.4840 0.04305 0.03881 -0.0426 0.8078 0.0090
-7.000 -0.4809 0.03808 0.03339 -0.0412 0.8022 0.0091
-6.750 -0.4732 0.03385 0.02864 -0.0395 0.7970 0.0093
-6.500 -0.4622 0.03019 0.02441 -0.0374 0.7929 0.0092
-6.250 -0.4460 0.02715 0.02085 -0.0359 0.7876 0.0092
-6.000 -0.4269 0.02472 0.01794 -0.0344 0.7829 0.0093
-5.750 -0.4059 0.02274 0.01555 -0.0331 0.7792 0.0094
-5.500 -0.3825 0.02107 0.01354 -0.0322 0.7743 0.0097
-5.250 -0.3588 0.01967 0.01190 -0.0313 0.7701 0.0100
-5.000 -0.3351 0.01851 0.01051 -0.0304 0.7666 0.0104
-4.750 -0.3108 0.01756 0.00938 -0.0296 0.7626 0.0110
-4.500 -0.2877 0.01645 0.00816 -0.0288 0.7581 0.0123
-4.250 -0.2631 0.01578 0.00736 -0.0281 0.7544 0.0147
-4.000 -0.2387 0.01515 0.00665 -0.0274 0.7514 0.0218
-3.750 -0.2133 0.01454 0.00602 -0.0269 0.7471 0.0385
-3.500 -0.1884 0.01400 0.00560 -0.0265 0.7431 0.0670
-3.250 -0.1633 0.01357 0.00525 -0.0261 0.7397 0.1002
-3.000 -0.1379 0.01322 0.00494 -0.0257 0.7366 0.1332
-2.750 -0.1125 0.01283 0.00472 -0.0254 0.7324 0.1814
-2.500 -0.0876 0.01246 0.00450 -0.0250 0.7287 0.2368
-2.250 -0.0634 0.01206 0.00427 -0.0245 0.7255 0.3033
-2.000 -0.0402 0.01161 0.00410 -0.0237 0.7221 0.3911
-1.750 -0.0192 0.01107 0.00399 -0.0225 0.7179 0.5105
-1.500 -0.0002 0.01041 0.00390 -0.0205 0.7142 0.6633
-1.250 0.0676 0.00994 0.00396 -0.0280 0.7115 0.8653
-1.000 0.1305 0.01007 0.00399 -0.0349 0.7077 0.9180
-0.750 0.1672 0.01022 0.00405 -0.0366 0.7031 0.9429
-0.500 0.2039 0.01034 0.00404 -0.0383 0.6990 0.9607
-0.250 0.2419 0.01043 0.00402 -0.0404 0.6950 0.9742
0.000 0.2836 0.01049 0.00401 -0.0434 0.6899 0.9852
0.250 0.3325 0.01046 0.00388 -0.0480 0.6853 0.9963
0.500 0.3675 0.01042 0.00377 -0.0497 0.6809 1.0000
0.750 0.3927 0.01043 0.00376 -0.0493 0.6753 1.0000
1.000 0.4176 0.01044 0.00370 -0.0489 0.6708 1.0000
1.250 0.4428 0.01046 0.00370 -0.0485 0.6655 1.0000
1.500 0.4681 0.01049 0.00371 -0.0482 0.6598 1.0000
2.000 0.5188 0.01056 0.00374 -0.0474 0.6486 1.0000
2.250 0.5440 0.01059 0.00376 -0.0469 0.6430 1.0000
2.500 0.5694 0.01064 0.00383 -0.0466 0.6364 1.0000
2.750 0.5947 0.01068 0.00387 -0.0462 0.6299 1.0000
3.000 0.6201 0.01074 0.00396 -0.0458 0.6227 1.0000
3.250 0.6454 0.01079 0.00403 -0.0454 0.6155 1.0000
3.500 0.6708 0.01086 0.00415 -0.0450 0.6069 1.0000
3.750 0.6960 0.01092 0.00422 -0.0445 0.5986 1.0000
4.000 0.7212 0.01099 0.00433 -0.0441 0.5885 1.0000
4.250 0.7463 0.01107 0.00449 -0.0437 0.5773 1.0000
4.500 0.7713 0.01116 0.00462 -0.0432 0.5650 1.0000
4.750 0.7960 0.01125 0.00475 -0.0427 0.5507 1.0000
5.000 0.8204 0.01137 0.00488 -0.0421 0.5337 1.0000
5.250 0.8445 0.01152 0.00504 -0.0415 0.5135 1.0000
5.500 0.8678 0.01173 0.00523 -0.0407 0.4908 1.0000
5.750 0.8904 0.01200 0.00547 -0.0399 0.4658 1.0000
6.000 0.9123 0.01236 0.00576 -0.0390 0.4398 1.0000
6.250 0.9333 0.01278 0.00612 -0.0380 0.4134 1.0000
6.500 0.9534 0.01326 0.00653 -0.0369 0.3856 1.0000
6.750 0.9722 0.01381 0.00701 -0.0357 0.3556 1.0000
7.000 0.9895 0.01444 0.00758 -0.0342 0.3226 1.0000
7.250 1.0042 0.01520 0.00818 -0.0325 0.2830 1.0000
7.500 1.0164 0.01607 0.00886 -0.0304 0.2390 1.0000
7.750 1.0275 0.01697 0.00959 -0.0282 0.2000 1.0000
8.000 1.0370 0.01791 0.01038 -0.0257 0.1644 1.0000
8.250 1.0439 0.01895 0.01124 -0.0230 0.1291 1.0000
8.500 1.0477 0.02010 0.01221 -0.0198 0.0960 1.0000
8.750 1.0474 0.02123 0.01319 -0.0160 0.0703 1.0000
9.000 1.0454 0.02246 0.01429 -0.0122 0.0489 1.0000
9.250 1.0466 0.02374 0.01549 -0.0091 0.0338 1.0000
9.500 1.0494 0.02508 0.01679 -0.0065 0.0237 1.0000
9.750 1.0520 0.02655 0.01825 -0.0041 0.0175 1.0000
10.000 1.0562 0.02800 0.01979 -0.0020 0.0124 1.0000
10.250 1.0587 0.02967 0.02156 0.0000 0.0108 1.0000
10.500 1.0627 0.03130 0.02333 0.0018 0.0085 1.0000
10.750 1.0658 0.03305 0.02519 0.0035 0.0075 1.0000
11.000 1.0665 0.03506 0.02728 0.0050 0.0066 1.0000
11.250 1.0662 0.03727 0.02962 0.0065 0.0064 1.0000
11.500 1.0745 0.03872 0.03120 0.0074 0.0053 1.0000
11.750 1.0802 0.04045 0.03302 0.0083 0.0046 1.0000
12.000 1.0824 0.04257 0.03526 0.0092 0.0044 1.0000
12.250 1.0833 0.04488 0.03768 0.0101 0.0040 1.0000
12.500 1.0818 0.04752 0.04044 0.0108 0.0038 1.0000
12.750 1.0798 0.05027 0.04333 0.0114 0.0037 1.0000
13.000 1.0734 0.05364 0.04685 0.0120 0.0035 1.0000
13.250 1.0721 0.05660 0.04995 0.0124 0.0034 1.0000
13.500 1.0708 0.05961 0.05312 0.0126 0.0033 1.0000
13.750 1.0685 0.06288 0.05655 0.0126 0.0033 1.0000
14.000 1.0652 0.06642 0.06032 0.0125 0.0032 1.0000
14.250 1.0608 0.07021 0.06429 0.0120 0.0032 1.0000
14.500 1.0561 0.07419 0.06845 0.0113 0.0031 1.0000
14.750 1.0479 0.07889 0.07335 0.0103 0.0030 1.0000
15.000 1.0400 0.08371 0.07837 0.0088 0.0030 1.0000
15.250 1.0315 0.08881 0.08364 0.0070 0.0030 1.0000
15.500 1.0197 0.09476 0.08979 0.0047 0.0030 1.0000
15.750 1.0089 0.10071 0.09592 0.0021 0.0030 1.0000
16.000 0.9963 0.10730 0.10270 -0.0010 0.0030 1.0000
16.250 0.9865 0.11348 0.10901 -0.0040 0.0031 1.0000
16.500 0.9703 0.12145 0.11716 -0.0081 0.0031 1.0000
16.750 0.9561 0.12926 0.12512 -0.0122 0.0031 1.0000
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