MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 500,000 Max Cl/Cd: 91.98 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh84-il-500000-n5.txt Download as CSV file: xf-mh84-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 84 13.69%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5628 0.06319 0.05997 -0.0319 0.8111 0.0099
-10.500 -0.6134 0.05259 0.04918 -0.0392 0.7927 0.0098
-10.250 -0.6470 0.04171 0.03806 -0.0507 0.7762 0.0097
-9.750 -0.6294 0.02957 0.02510 -0.0661 0.7481 0.0098
-9.500 -0.6098 0.02741 0.02267 -0.0675 0.7359 0.0098
-9.250 -0.5878 0.02567 0.02068 -0.0684 0.7232 0.0099
-9.000 -0.5643 0.02417 0.01896 -0.0691 0.7116 0.0099
-8.750 -0.5401 0.02281 0.01738 -0.0695 0.6998 0.0100
-8.500 -0.5153 0.02144 0.01584 -0.0700 0.6882 0.0101
-8.250 -0.4894 0.02043 0.01467 -0.0703 0.6772 0.0103
-8.000 -0.4627 0.01959 0.01372 -0.0704 0.6654 0.0104
-7.750 -0.4355 0.01885 0.01286 -0.0705 0.6546 0.0106
-7.500 -0.4081 0.01818 0.01205 -0.0706 0.6431 0.0108
-7.250 -0.3804 0.01752 0.01127 -0.0706 0.6327 0.0110
-7.000 -0.3526 0.01689 0.01051 -0.0706 0.6215 0.0112
-6.750 -0.3245 0.01628 0.00978 -0.0707 0.6110 0.0113
-6.250 -0.2678 0.01516 0.00843 -0.0706 0.5898 0.0117
-6.000 -0.2393 0.01468 0.00782 -0.0706 0.5795 0.0119
-5.750 -0.2105 0.01423 0.00727 -0.0706 0.5689 0.0121
-5.500 -0.1816 0.01384 0.00677 -0.0705 0.5589 0.0124
-5.250 -0.1528 0.01338 0.00623 -0.0705 0.5486 0.0127
-5.000 -0.1238 0.01303 0.00580 -0.0705 0.5388 0.0131
-4.750 -0.0948 0.01273 0.00543 -0.0704 0.5284 0.0136
-4.500 -0.0656 0.01246 0.00507 -0.0703 0.5188 0.0142
-4.250 -0.0364 0.01222 0.00474 -0.0702 0.5085 0.0149
-4.000 -0.0071 0.01196 0.00442 -0.0702 0.4993 0.0159
-3.750 0.0221 0.01176 0.00415 -0.0701 0.4891 0.0171
-3.500 0.0514 0.01156 0.00390 -0.0701 0.4799 0.0188
-3.250 0.0807 0.01139 0.00367 -0.0700 0.4700 0.0214
-3.000 0.1100 0.01122 0.00346 -0.0699 0.4609 0.0254
-2.750 0.1393 0.01105 0.00327 -0.0699 0.4513 0.0328
-2.500 0.1686 0.01086 0.00311 -0.0699 0.4425 0.0458
-2.250 0.1978 0.01069 0.00297 -0.0698 0.4330 0.0636
-2.000 0.2270 0.01056 0.00287 -0.0698 0.4247 0.0831
-1.750 0.2563 0.01045 0.00278 -0.0698 0.4154 0.1030
-1.500 0.2855 0.01036 0.00273 -0.0698 0.4070 0.1241
-1.250 0.3147 0.01029 0.00269 -0.0698 0.3982 0.1466
-1.000 0.3439 0.01025 0.00267 -0.0697 0.3901 0.1678
-0.750 0.3731 0.01022 0.00266 -0.0697 0.3814 0.1885
-0.500 0.4022 0.01023 0.00265 -0.0696 0.3737 0.2052
-0.250 0.4314 0.01023 0.00265 -0.0696 0.3660 0.2202
0.000 0.4605 0.01028 0.00267 -0.0695 0.3577 0.2349
0.250 0.4896 0.01029 0.00268 -0.0694 0.3502 0.2509
0.500 0.5186 0.01032 0.00271 -0.0694 0.3427 0.2677
0.750 0.5477 0.01036 0.00276 -0.0693 0.3362 0.2864
1.000 0.5766 0.01039 0.00280 -0.0693 0.3286 0.3075
1.250 0.6054 0.01045 0.00287 -0.0692 0.3214 0.3322
1.500 0.6343 0.01046 0.00294 -0.0692 0.3148 0.3623
1.750 0.6630 0.01050 0.00303 -0.0692 0.3081 0.3991
2.000 0.6917 0.01051 0.00313 -0.0692 0.3021 0.4433
2.250 0.7202 0.01052 0.00324 -0.0691 0.2953 0.4967
2.750 0.7765 0.01050 0.00352 -0.0689 0.2835 0.6326
3.000 0.8037 0.01046 0.00367 -0.0685 0.2775 0.7147
3.250 0.8261 0.01023 0.00380 -0.0671 0.2720 0.8555
3.500 0.8575 0.01023 0.00387 -0.0674 0.2663 1.0000
3.750 0.8858 0.01044 0.00401 -0.0674 0.2607 1.0000
4.000 0.9140 0.01065 0.00417 -0.0673 0.2557 1.0000
4.250 0.9423 0.01083 0.00431 -0.0672 0.2506 1.0000
4.500 0.9703 0.01106 0.00448 -0.0671 0.2451 1.0000
4.750 0.9981 0.01130 0.00466 -0.0670 0.2406 1.0000
5.000 1.0261 0.01149 0.00483 -0.0669 0.2364 1.0000
5.250 1.0538 0.01172 0.00503 -0.0668 0.2314 1.0000
5.500 1.0810 0.01200 0.00525 -0.0667 0.2267 1.0000
5.750 1.1087 0.01221 0.00545 -0.0666 0.2232 1.0000
6.000 1.1361 0.01244 0.00566 -0.0665 0.2193 1.0000
6.250 1.1631 0.01271 0.00591 -0.0663 0.2153 1.0000
6.500 1.1898 0.01302 0.00617 -0.0662 0.2113 1.0000
6.750 1.2169 0.01325 0.00641 -0.0660 0.2079 1.0000
7.000 1.2436 0.01352 0.00667 -0.0658 0.2043 1.0000
7.250 1.2699 0.01382 0.00695 -0.0656 0.2008 1.0000
7.500 1.2956 0.01418 0.00727 -0.0654 0.1974 1.0000
7.750 1.3220 0.01443 0.00755 -0.0652 0.1948 1.0000
8.000 1.3480 0.01472 0.00785 -0.0650 0.1915 1.0000
8.250 1.3733 0.01506 0.00818 -0.0647 0.1880 1.0000
8.500 1.3980 0.01545 0.00856 -0.0644 0.1849 1.0000
8.750 1.4229 0.01579 0.00891 -0.0641 0.1825 1.0000
9.000 1.4479 0.01611 0.00926 -0.0637 0.1800 1.0000
9.250 1.4722 0.01647 0.00963 -0.0634 0.1773 1.0000
9.500 1.4957 0.01688 0.01005 -0.0629 0.1743 1.0000
9.750 1.5181 0.01736 0.01052 -0.0624 0.1713 1.0000
10.000 1.5412 0.01775 0.01095 -0.0619 0.1691 1.0000
10.250 1.5639 0.01815 0.01138 -0.0614 0.1669 1.0000
10.500 1.5857 0.01859 0.01186 -0.0608 0.1645 1.0000
10.750 1.6061 0.01909 0.01238 -0.0600 0.1622 1.0000
11.000 1.6249 0.01967 0.01297 -0.0591 0.1599 1.0000
11.250 1.6423 0.02028 0.01360 -0.0581 0.1577 1.0000
11.500 1.6600 0.02079 0.01418 -0.0570 0.1558 1.0000
11.750 1.6732 0.02139 0.01484 -0.0554 0.1537 1.0000
12.000 1.6841 0.02215 0.01564 -0.0538 0.1519 1.0000
12.250 1.6939 0.02307 0.01660 -0.0523 0.1500 1.0000
12.500 1.7026 0.02416 0.01774 -0.0510 0.1483 1.0000
12.750 1.7100 0.02546 0.01907 -0.0499 0.1465 1.0000
13.000 1.7208 0.02661 0.02029 -0.0491 0.1451 1.0000
13.250 1.7313 0.02784 0.02160 -0.0484 0.1435 1.0000
13.500 1.7404 0.02924 0.02308 -0.0478 0.1417 1.0000
13.750 1.7478 0.03085 0.02474 -0.0473 0.1399 1.0000
14.000 1.7535 0.03267 0.02663 -0.0469 0.1383 1.0000
14.250 1.7574 0.03473 0.02874 -0.0466 0.1368 1.0000
14.500 1.7592 0.03705 0.03111 -0.0464 0.1353 1.0000
14.750 1.7640 0.03916 0.03330 -0.0463 0.1341 1.0000
15.000 1.7693 0.04127 0.03550 -0.0463 0.1328 1.0000
15.250 1.7729 0.04357 0.03790 -0.0463 0.1313 1.0000
15.500 1.7746 0.04615 0.04056 -0.0466 0.1298 1.0000
15.750 1.7744 0.04898 0.04346 -0.0469 0.1283 1.0000
16.000 1.7723 0.05210 0.04666 -0.0474 0.1269 1.0000
16.250 1.7688 0.05548 0.05011 -0.0481 0.1256 1.0000
16.500 1.7639 0.05916 0.05384 -0.0490 0.1242 1.0000
16.750 1.7643 0.06222 0.05702 -0.0497 0.1231 1.0000
17.000 1.7639 0.06545 0.06035 -0.0505 0.1219 1.0000
17.250 1.7624 0.06889 0.06388 -0.0515 0.1205 1.0000
17.500 1.7591 0.07264 0.06772 -0.0527 0.1190 1.0000
17.750 1.7539 0.07673 0.07190 -0.0541 0.1176 1.0000
18.000 1.7475 0.08107 0.07630 -0.0556 0.1162 1.0000
18.250 1.7404 0.08552 0.08082 -0.0572 0.1148 1.0000
18.500 1.7354 0.08978 0.08516 -0.0589 0.1134 1.0000
18.750 1.7319 0.09386 0.08936 -0.0605 0.1122 1.0000
19.000 1.7282 0.09802 0.09362 -0.0621 0.1108 1.0000
19.250 1.7216 0.10267 0.09837 -0.0641 0.1093 1.0000
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Polar data table (+)
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