MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 500,000 Max Cl/Cd: 77.32 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh78-il-500000-n5.txt Download as CSV file: xf-mh78-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9623 0.06897 0.06567 0.0057 1.0000 0.0089
-13.500 -1.0007 0.05700 0.05333 -0.0039 1.0000 0.0088
-13.250 -1.0219 0.05046 0.04656 -0.0081 1.0000 0.0088
-13.000 -1.0395 0.04564 0.04154 -0.0097 1.0000 0.0088
-12.750 -1.0497 0.04229 0.03802 -0.0096 1.0000 0.0088
-12.500 -1.0582 0.03947 0.03504 -0.0084 1.0000 0.0088
-12.250 -1.0626 0.03718 0.03259 -0.0066 1.0000 0.0088
-12.000 -1.0643 0.03525 0.03054 -0.0044 1.0000 0.0089
-11.750 -1.0638 0.03355 0.02869 -0.0018 1.0000 0.0089
-11.500 -1.0615 0.03202 0.02705 0.0010 1.0000 0.0089
-11.250 -1.0554 0.03071 0.02563 0.0036 1.0000 0.0090
-11.000 -1.0444 0.02941 0.02422 0.0055 1.0000 0.0090
-10.750 -1.0309 0.02820 0.02290 0.0073 1.0000 0.0091
-10.500 -1.0156 0.02706 0.02167 0.0089 1.0000 0.0091
-10.250 -1.0016 0.02627 0.02060 0.0111 0.8500 0.0092
-10.000 -0.9874 0.02548 0.01954 0.0134 0.7954 0.0092
-9.750 -0.9699 0.02467 0.01851 0.0151 0.7573 0.0093
-9.500 -0.9510 0.02384 0.01749 0.0165 0.7265 0.0094
-9.250 -0.9309 0.02305 0.01652 0.0178 0.6991 0.0095
-9.000 -0.9100 0.02230 0.01560 0.0190 0.6747 0.0096
-8.750 -0.8883 0.02158 0.01473 0.0201 0.6524 0.0097
-8.500 -0.8661 0.02088 0.01388 0.0212 0.6317 0.0099
-8.250 -0.8433 0.02022 0.01308 0.0222 0.6125 0.0100
-8.000 -0.8201 0.01958 0.01232 0.0231 0.5940 0.0102
-7.750 -0.7965 0.01899 0.01160 0.0240 0.5766 0.0104
-7.500 -0.7724 0.01843 0.01092 0.0249 0.5603 0.0105
-7.250 -0.7480 0.01792 0.01029 0.0257 0.5447 0.0107
-7.000 -0.7232 0.01743 0.00970 0.0264 0.5291 0.0109
-6.750 -0.6985 0.01693 0.00910 0.0272 0.5148 0.0110
-6.500 -0.6737 0.01642 0.00852 0.0280 0.5013 0.0113
-6.250 -0.6483 0.01600 0.00803 0.0286 0.4873 0.0116
-6.000 -0.6224 0.01563 0.00760 0.0292 0.4746 0.0119
-5.750 -0.5963 0.01528 0.00718 0.0298 0.4628 0.0121
-5.500 -0.5701 0.01494 0.00677 0.0304 0.4506 0.0125
-5.250 -0.5436 0.01463 0.00638 0.0310 0.4391 0.0129
-5.000 -0.5169 0.01435 0.00602 0.0315 0.4276 0.0133
-4.750 -0.4903 0.01403 0.00566 0.0320 0.4182 0.0138
-4.500 -0.4635 0.01377 0.00534 0.0325 0.4077 0.0144
-4.250 -0.4364 0.01352 0.00506 0.0329 0.3982 0.0153
-4.000 -0.4092 0.01332 0.00479 0.0334 0.3877 0.0165
-3.750 -0.3819 0.01308 0.00454 0.0338 0.3787 0.0182
-3.500 -0.3545 0.01289 0.00430 0.0342 0.3699 0.0201
-3.250 -0.3271 0.01268 0.00408 0.0346 0.3622 0.0232
-3.000 -0.2997 0.01249 0.00387 0.0350 0.3534 0.0275
-2.750 -0.2723 0.01231 0.00368 0.0353 0.3456 0.0340
-2.500 -0.2449 0.01212 0.00350 0.0357 0.3373 0.0441
-2.250 -0.2179 0.01190 0.00333 0.0361 0.3302 0.0626
-2.000 -0.1912 0.01159 0.00317 0.0365 0.3239 0.0954
-1.750 -0.1649 0.01128 0.00302 0.0370 0.3171 0.1427
-1.500 -0.1383 0.01102 0.00291 0.0373 0.3108 0.1899
-1.250 -0.1120 0.01072 0.00281 0.0378 0.3044 0.2458
-1.000 -0.0861 0.01041 0.00271 0.0383 0.2980 0.3101
-0.750 -0.0603 0.01010 0.00264 0.0388 0.2930 0.3800
-0.500 -0.0372 0.00956 0.00254 0.0397 0.2882 0.4993
-0.250 -0.0167 0.00893 0.00246 0.0413 0.2833 0.6426
0.000 0.0050 0.00855 0.00248 0.0429 0.2781 0.7534
0.250 0.0308 0.00848 0.00260 0.0440 0.2738 0.8162
0.500 0.0583 0.00855 0.00270 0.0446 0.2690 0.8463
0.750 0.0862 0.00866 0.00277 0.0451 0.2646 0.8646
1.000 0.1142 0.00878 0.00285 0.0455 0.2606 0.8774
1.250 0.1420 0.00886 0.00290 0.0459 0.2569 0.8888
1.500 0.1704 0.00898 0.00299 0.0462 0.2525 0.8970
1.750 0.1976 0.00911 0.00305 0.0466 0.2486 0.9065
2.000 0.2256 0.00927 0.00318 0.0471 0.2450 0.9151
2.250 0.2518 0.00939 0.00329 0.0479 0.2424 0.9261
2.500 0.2804 0.00955 0.00343 0.0482 0.2390 0.9344
2.750 0.3064 0.00970 0.00354 0.0490 0.2357 0.9430
3.000 0.3378 0.00988 0.00368 0.0487 0.2319 0.9479
3.250 0.3670 0.01005 0.00380 0.0487 0.2290 0.9529
3.500 0.3937 0.01015 0.00389 0.0492 0.2267 0.9576
3.750 0.4263 0.01027 0.00399 0.0484 0.2239 0.9593
4.000 0.4582 0.01040 0.00409 0.0477 0.2207 0.9609
4.250 0.4893 0.01055 0.00419 0.0471 0.2176 0.9627
4.500 0.5195 0.01073 0.00432 0.0467 0.2145 0.9647
4.750 0.5492 0.01084 0.00444 0.0465 0.2126 0.9668
5.000 0.5769 0.01096 0.00455 0.0466 0.2103 0.9696
5.250 0.6066 0.01109 0.00468 0.0463 0.2078 0.9714
5.500 0.6385 0.01125 0.00481 0.0454 0.2049 0.9723
5.750 0.6704 0.01144 0.00497 0.0446 0.2021 0.9734
6.000 0.7023 0.01164 0.00515 0.0437 0.1997 0.9746
6.250 0.7342 0.01179 0.00532 0.0429 0.1977 0.9758
6.500 0.7652 0.01195 0.00549 0.0422 0.1956 0.9772
6.750 0.7953 0.01213 0.00567 0.0416 0.1932 0.9787
7.000 0.8244 0.01232 0.00586 0.0413 0.1907 0.9806
7.250 0.8520 0.01255 0.00607 0.0412 0.1883 0.9829
7.500 0.8842 0.01280 0.00630 0.0401 0.1860 0.9838
7.750 0.9163 0.01298 0.00653 0.0391 0.1842 0.9848
8.000 0.9476 0.01319 0.00676 0.0383 0.1821 0.9860
8.250 0.9783 0.01341 0.00700 0.0375 0.1800 0.9872
8.500 1.0084 0.01366 0.00726 0.0368 0.1777 0.9887
8.750 1.0378 0.01394 0.00754 0.0361 0.1754 0.9904
9.000 1.0664 0.01426 0.00786 0.0356 0.1732 0.9922
9.250 1.0958 0.01450 0.00815 0.0350 0.1716 0.9938
9.500 1.1268 0.01477 0.00846 0.0341 0.1698 0.9952
9.750 1.1573 0.01505 0.00878 0.0332 0.1678 0.9969
10.000 1.1871 0.01537 0.00912 0.0323 0.1656 0.9985
10.250 1.2162 0.01573 0.00949 0.0315 0.1635 1.0000
10.500 1.2339 0.01611 0.00988 0.0329 0.1616 1.0000
10.750 1.2520 0.01644 0.01026 0.0343 0.1603 1.0000
11.000 1.2703 0.01675 0.01062 0.0357 0.1589 1.0000
11.250 1.2885 0.01708 0.01101 0.0370 0.1572 1.0000
11.500 1.3065 0.01745 0.01142 0.0382 0.1553 1.0000
11.750 1.3242 0.01786 0.01186 0.0394 0.1536 1.0000
12.000 1.3414 0.01833 0.01234 0.0406 0.1518 1.0000
12.250 1.3577 0.01888 0.01290 0.0417 0.1499 1.0000
12.500 1.3752 0.01937 0.01346 0.0427 0.1484 1.0000
12.750 1.3928 0.01986 0.01402 0.0435 0.1467 1.0000
13.000 1.4088 0.02042 0.01465 0.0445 0.1449 1.0000
13.250 1.4207 0.02109 0.01537 0.0458 0.1431 1.0000
13.500 1.4259 0.02202 0.01634 0.0475 0.1414 1.0000
13.750 1.4307 0.02328 0.01765 0.0484 0.1399 1.0000
14.000 1.4345 0.02489 0.01930 0.0487 0.1381 1.0000
14.250 1.4437 0.02626 0.02077 0.0487 0.1367 1.0000
14.500 1.4512 0.02788 0.02248 0.0485 0.1352 1.0000
14.750 1.4566 0.02977 0.02445 0.0480 0.1332 1.0000
15.000 1.4596 0.03196 0.02671 0.0475 0.1318 1.0000
15.250 1.4592 0.03456 0.02937 0.0467 0.1301 1.0000
15.500 1.4558 0.03748 0.03235 0.0457 0.1285 1.0000
15.750 1.4521 0.04049 0.03542 0.0447 0.1272 1.0000
16.000 1.4511 0.04326 0.03830 0.0438 0.1257 1.0000
16.250 1.4464 0.04648 0.04162 0.0426 0.1239 1.0000
16.500 1.4391 0.05002 0.04525 0.0412 0.1224 1.0000
16.750 1.4288 0.05395 0.04925 0.0397 0.1207 1.0000
17.000 1.4150 0.05846 0.05382 0.0377 0.1188 1.0000
17.250 1.4033 0.06284 0.05825 0.0357 0.1174 1.0000
17.500 1.3955 0.06689 0.06242 0.0339 0.1158 1.0000
17.750 1.3849 0.07140 0.06703 0.0318 0.1139 1.0000
18.000 1.3719 0.07630 0.07200 0.0294 0.1119 1.0000
18.250 1.3577 0.08149 0.07725 0.0269 0.1099 1.0000
18.500 1.3443 0.08656 0.08235 0.0243 0.1080 1.0000
18.750 1.3318 0.09174 0.08765 0.0217 0.1061 1.0000
19.000 1.3183 0.09710 0.09311 0.0190 0.1039 1.0000
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Polar data table (+)
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