MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 200,000 Max Cl/Cd: 77.17 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh18-il-200000.txt Download as CSV file: xf-mh18-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4100 0.11437 0.11125 -0.0166 1.0000 0.0350
-10.250 -0.4078 0.11026 0.10718 -0.0205 1.0000 0.0365
-10.000 -0.4062 0.10622 0.10320 -0.0256 1.0000 0.0374
-9.000 -0.3817 0.08929 0.08640 -0.0352 1.0000 0.0422
-8.750 -0.3703 0.08445 0.08157 -0.0411 0.9723 0.0427
-8.500 -0.3620 0.07953 0.07663 -0.0477 0.9539 0.0475
-8.250 -0.3648 0.07543 0.07251 -0.0508 0.9350 0.0470
-7.250 -0.3710 0.04958 0.04655 -0.0522 0.8686 0.0533
-7.000 -0.4044 0.05536 0.05187 -0.0558 0.8772 0.0531
-6.750 -0.3946 0.05287 0.04931 -0.0551 0.8704 0.0552
-6.500 -0.3874 0.04974 0.04599 -0.0543 0.8640 0.0579
-6.250 -0.3881 0.04567 0.04126 -0.0531 0.8574 0.0646
-6.000 -0.3724 0.04246 0.03806 -0.0525 0.8521 0.0663
-5.750 -0.3642 0.03212 0.02623 -0.0464 0.8480 0.0271
-5.500 -0.3479 0.02782 0.02158 -0.0452 0.8421 0.0250
-5.250 -0.3289 0.02503 0.01832 -0.0433 0.8375 0.0241
-5.000 -0.3077 0.02283 0.01570 -0.0415 0.8341 0.0237
-4.750 -0.2815 0.02100 0.01359 -0.0410 0.8289 0.0240
-4.500 -0.2568 0.01956 0.01195 -0.0400 0.8245 0.0251
-4.250 -0.2332 0.01844 0.01066 -0.0386 0.8211 0.0270
-4.000 -0.2100 0.01722 0.00943 -0.0378 0.8165 0.0364
-3.750 -0.1879 0.01612 0.00834 -0.0366 0.8119 0.0647
-3.500 -0.1663 0.01531 0.00774 -0.0353 0.8084 0.1107
-3.250 -0.1435 0.01472 0.00737 -0.0346 0.8045 0.1698
-3.000 -0.1205 0.01419 0.00713 -0.0340 0.7996 0.2433
-2.750 -0.1007 0.01351 0.00690 -0.0327 0.7958 0.3550
-2.500 -0.0861 0.01267 0.00673 -0.0300 0.7929 0.5257
-2.250 -0.0631 0.01177 0.00683 -0.0285 0.7879 0.7763
-2.000 0.0433 0.01196 0.00702 -0.0429 0.7865 0.9301
-1.750 0.0947 0.01228 0.00714 -0.0470 0.7831 0.9598
-1.500 0.1491 0.01244 0.00707 -0.0520 0.7803 0.9807
-1.250 0.2102 0.01236 0.00682 -0.0589 0.7766 0.9953
-1.000 0.2477 0.01226 0.00662 -0.0614 0.7715 1.0000
-0.750 0.2695 0.01221 0.00644 -0.0604 0.7672 1.0000
-0.500 0.2927 0.01224 0.00639 -0.0598 0.7624 1.0000
-0.250 0.3165 0.01227 0.00635 -0.0593 0.7568 1.0000
0.000 0.3390 0.01223 0.00621 -0.0583 0.7527 1.0000
0.250 0.3635 0.01231 0.00625 -0.0580 0.7470 1.0000
0.500 0.3873 0.01232 0.00621 -0.0573 0.7417 1.0000
0.750 0.4103 0.01228 0.00608 -0.0562 0.7379 1.0000
1.000 0.4355 0.01240 0.00623 -0.0561 0.7311 1.0000
1.250 0.4592 0.01239 0.00615 -0.0552 0.7263 1.0000
1.500 0.4835 0.01245 0.00619 -0.0547 0.7206 1.0000
1.750 0.5079 0.01249 0.00621 -0.0541 0.7145 1.0000
2.000 0.5316 0.01244 0.00609 -0.0530 0.7102 1.0000
2.250 0.5566 0.01256 0.00628 -0.0527 0.7023 1.0000
2.500 0.5808 0.01250 0.00617 -0.0518 0.6974 1.0000
2.750 0.6055 0.01260 0.00631 -0.0513 0.6895 1.0000
3.000 0.6299 0.01253 0.00621 -0.0504 0.6839 1.0000
3.250 0.6546 0.01261 0.00636 -0.0499 0.6756 1.0000
3.500 0.6793 0.01253 0.00625 -0.0490 0.6696 1.0000
3.750 0.7039 0.01259 0.00637 -0.0485 0.6604 1.0000
4.000 0.7287 0.01254 0.00634 -0.0477 0.6528 1.0000
4.250 0.7534 0.01251 0.00636 -0.0469 0.6437 1.0000
4.500 0.7780 0.01251 0.00642 -0.0463 0.6334 1.0000
4.750 0.8028 0.01247 0.00641 -0.0455 0.6232 1.0000
5.000 0.8276 0.01239 0.00637 -0.0447 0.6123 1.0000
5.250 0.8522 0.01234 0.00635 -0.0439 0.6000 1.0000
5.500 0.8764 0.01233 0.00645 -0.0431 0.5853 1.0000
5.750 0.9004 0.01234 0.00654 -0.0424 0.5685 1.0000
6.000 0.9243 0.01235 0.00662 -0.0415 0.5496 1.0000
6.250 0.9476 0.01243 0.00672 -0.0406 0.5280 1.0000
6.500 0.9700 0.01257 0.00685 -0.0396 0.5024 1.0000
6.750 0.9912 0.01285 0.00708 -0.0384 0.4725 1.0000
7.000 1.0106 0.01329 0.00745 -0.0370 0.4386 1.0000
7.250 1.0279 0.01387 0.00790 -0.0354 0.4001 1.0000
7.500 1.0437 0.01453 0.00845 -0.0337 0.3620 1.0000
7.750 1.0581 0.01526 0.00906 -0.0318 0.3260 1.0000
8.000 1.0700 0.01608 0.00976 -0.0295 0.2853 1.0000
8.250 1.0782 0.01706 0.01056 -0.0269 0.2387 1.0000
8.500 1.0810 0.01829 0.01152 -0.0235 0.1875 1.0000
8.750 1.0744 0.01997 0.01277 -0.0190 0.1250 1.0000
9.000 1.0611 0.02167 0.01410 -0.0135 0.0804 1.0000
9.250 1.0494 0.02363 0.01581 -0.0088 0.0521 1.0000
9.500 1.0400 0.02579 0.01786 -0.0049 0.0374 1.0000
9.750 1.0385 0.02762 0.01970 -0.0022 0.0282 1.0000
10.000 1.0346 0.02981 0.02199 0.0007 0.0217 1.0000
10.250 1.0350 0.03174 0.02403 0.0028 0.0199 1.0000
10.500 1.0285 0.03445 0.02680 0.0054 0.0168 1.0000
10.750 1.0342 0.03622 0.02867 0.0071 0.0153 1.0000
11.000 1.0415 0.03770 0.03021 0.0081 0.0133 1.0000
11.250 1.0464 0.03970 0.03230 0.0097 0.0128 1.0000
11.500 1.0493 0.04234 0.03497 0.0117 0.0114 1.0000
11.750 1.0596 0.04480 0.03761 0.0136 0.0109 1.0000
12.000 1.0680 0.04702 0.04002 0.0149 0.0107 1.0000
12.250 1.0732 0.04958 0.04281 0.0162 0.0104 1.0000
12.500 1.0753 0.05252 0.04599 0.0174 0.0103 1.0000
12.750 1.0740 0.05575 0.04947 0.0184 0.0103 1.0000
13.000 1.0683 0.05947 0.05344 0.0191 0.0103 1.0000
13.250 1.0589 0.06351 0.05773 0.0195 0.0103 1.0000
13.500 1.0484 0.06771 0.06216 0.0195 0.0104 1.0000
13.750 1.0357 0.07233 0.06699 0.0191 0.0106 1.0000
14.000 1.0198 0.07745 0.07234 0.0180 0.0106 1.0000
14.250 1.0042 0.08290 0.07797 0.0165 0.0107 1.0000
14.500 0.9881 0.08870 0.08395 0.0144 0.0108 1.0000
14.750 0.9694 0.09530 0.09075 0.0115 0.0108 1.0000
15.000 0.9505 0.10255 0.09815 0.0083 0.0110 1.0000
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Polar data table (+)
Polar graphs
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