MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.98 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh93-il-1000000.txt Download as CSV file: xf-mh93-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 93 15.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9440 0.10248 0.09990 0.0052 1.0000 0.0077
-16.500 -0.9744 0.09188 0.08911 -0.0015 1.0000 0.0076
-16.250 -0.9995 0.08291 0.07996 -0.0071 1.0000 0.0076
-16.000 -1.0197 0.07540 0.07228 -0.0115 1.0000 0.0075
-15.750 -1.0398 0.06836 0.06505 -0.0153 1.0000 0.0075
-15.500 -1.0517 0.06306 0.05961 -0.0178 1.0000 0.0075
-15.250 -1.0610 0.05843 0.05485 -0.0197 1.0000 0.0075
-15.000 -1.0722 0.05384 0.05009 -0.0212 1.0000 0.0075
-14.750 -1.0807 0.04989 0.04600 -0.0220 1.0000 0.0075
-14.500 -1.0878 0.04631 0.04226 -0.0224 1.0000 0.0074
-14.250 -1.0922 0.04323 0.03905 -0.0222 1.0000 0.0074
-14.000 -1.0934 0.04062 0.03633 -0.0218 1.0000 0.0074
-13.750 -1.0943 0.03814 0.03372 -0.0210 1.0000 0.0074
-13.500 -1.0932 0.03595 0.03142 -0.0200 1.0000 0.0074
-13.250 -1.0898 0.03405 0.02942 -0.0189 1.0000 0.0074
-13.000 -1.0864 0.03218 0.02744 -0.0175 1.0000 0.0075
-12.750 -1.0807 0.03060 0.02574 -0.0160 1.0000 0.0076
-12.500 -1.0733 0.02919 0.02425 -0.0145 1.0000 0.0076
-12.250 -1.0653 0.02785 0.02283 -0.0130 1.0000 0.0076
-12.000 -1.0567 0.02655 0.02145 -0.0113 1.0000 0.0076
-11.750 -1.0457 0.02552 0.02035 -0.0097 1.0000 0.0077
-11.500 -1.0347 0.02448 0.01925 -0.0079 1.0000 0.0077
-11.250 -1.0226 0.02353 0.01824 -0.0063 1.0000 0.0078
-11.000 -1.0156 0.02214 0.01676 -0.0039 1.0000 0.0079
-10.750 -1.0066 0.02099 0.01554 -0.0016 1.0000 0.0080
-10.500 -0.9988 0.01982 0.01432 0.0009 1.0000 0.0082
-10.250 -0.9785 0.01906 0.01346 0.0014 0.9315 0.0083
-10.000 -0.9698 0.01862 0.01287 0.0048 0.8877 0.0085
-9.750 -0.9586 0.01810 0.01222 0.0076 0.8620 0.0086
-9.500 -0.9453 0.01761 0.01163 0.0101 0.8420 0.0087
-9.250 -0.9297 0.01719 0.01113 0.0122 0.8249 0.0089
-9.000 -0.9112 0.01676 0.01062 0.0138 0.8093 0.0092
-8.750 -0.8926 0.01626 0.01004 0.0154 0.7951 0.0094
-8.500 -0.8723 0.01583 0.00953 0.0167 0.7816 0.0097
-8.250 -0.8517 0.01541 0.00902 0.0180 0.7689 0.0098
-8.000 -0.8294 0.01507 0.00862 0.0190 0.7562 0.0100
-7.750 -0.8099 0.01446 0.00794 0.0205 0.7443 0.0103
-7.500 -0.7884 0.01401 0.00743 0.0216 0.7326 0.0107
-7.250 -0.7653 0.01364 0.00701 0.0225 0.7209 0.0111
-7.000 -0.7416 0.01331 0.00663 0.0233 0.7098 0.0116
-6.500 -0.6930 0.01270 0.00591 0.0247 0.6873 0.0127
-6.250 -0.6693 0.01233 0.00550 0.0255 0.6766 0.0139
-6.000 -0.6439 0.01208 0.00521 0.0261 0.6656 0.0150
-5.750 -0.6192 0.01176 0.00487 0.0268 0.6550 0.0174
-5.500 -0.5942 0.01147 0.00455 0.0274 0.6441 0.0214
-5.250 -0.5693 0.01114 0.00426 0.0280 0.6337 0.0292
-5.000 -0.5450 0.01080 0.00396 0.0286 0.6230 0.0450
-4.750 -0.5208 0.01039 0.00367 0.0293 0.6129 0.0691
-4.500 -0.4975 0.00994 0.00337 0.0301 0.6031 0.1072
-4.250 -0.4745 0.00943 0.00308 0.0309 0.5929 0.1581
-4.000 -0.4515 0.00894 0.00282 0.0317 0.5831 0.2153
-3.750 -0.4283 0.00847 0.00259 0.0324 0.5730 0.2767
-3.500 -0.4040 0.00810 0.00241 0.0331 0.5637 0.3305
-3.250 -0.3792 0.00778 0.00224 0.0336 0.5533 0.3791
-3.000 -0.3542 0.00748 0.00210 0.0342 0.5435 0.4287
-2.750 -0.3293 0.00720 0.00198 0.0347 0.5335 0.4811
-2.500 -0.3039 0.00693 0.00188 0.0353 0.5242 0.5281
-2.250 -0.2780 0.00676 0.00179 0.0357 0.5137 0.5698
-2.000 -0.2522 0.00655 0.00171 0.0362 0.5042 0.6106
-1.750 -0.2254 0.00644 0.00166 0.0365 0.4946 0.6427
-1.500 -0.1982 0.00634 0.00162 0.0368 0.4847 0.6691
-1.250 -0.1705 0.00630 0.00160 0.0370 0.4748 0.6928
-1.000 -0.1425 0.00628 0.00159 0.0371 0.4648 0.7131
-0.750 -0.1143 0.00627 0.00159 0.0372 0.4556 0.7311
-0.500 -0.0860 0.00630 0.00160 0.0373 0.4452 0.7472
-0.250 -0.0576 0.00631 0.00161 0.0373 0.4358 0.7606
0.000 -0.0291 0.00636 0.00163 0.0373 0.4260 0.7712
0.250 -0.0001 0.00640 0.00165 0.0372 0.4171 0.7812
0.500 0.0284 0.00647 0.00168 0.0372 0.4069 0.7895
0.750 0.0574 0.00652 0.00171 0.0371 0.3982 0.7978
1.000 0.0861 0.00659 0.00175 0.0370 0.3889 0.8049
1.250 0.1149 0.00665 0.00179 0.0370 0.3801 0.8120
1.500 0.1437 0.00676 0.00183 0.0368 0.3713 0.8185
1.750 0.1724 0.00681 0.00189 0.0368 0.3631 0.8244
2.000 0.2010 0.00691 0.00196 0.0367 0.3545 0.8305
2.250 0.2299 0.00700 0.00200 0.0366 0.3466 0.8362
2.500 0.2582 0.00710 0.00208 0.0366 0.3385 0.8418
2.750 0.2868 0.00717 0.00216 0.0365 0.3321 0.8478
3.000 0.3151 0.00731 0.00225 0.0364 0.3241 0.8539
3.250 0.3434 0.00738 0.00233 0.0364 0.3176 0.8593
3.500 0.3717 0.00749 0.00242 0.0364 0.3106 0.8641
3.750 0.3999 0.00762 0.00252 0.0363 0.3041 0.8689
4.000 0.4285 0.00771 0.00260 0.0362 0.2985 0.8729
4.250 0.4564 0.00783 0.00271 0.0362 0.2918 0.8772
4.500 0.4844 0.00794 0.00282 0.0362 0.2860 0.8813
4.750 0.5125 0.00805 0.00292 0.0361 0.2803 0.8855
5.000 0.5402 0.00821 0.00305 0.0361 0.2740 0.8896
5.250 0.5682 0.00831 0.00315 0.0360 0.2694 0.8934
5.500 0.5957 0.00842 0.00327 0.0361 0.2639 0.8973
5.750 0.6226 0.00860 0.00343 0.0362 0.2575 0.9015
6.000 0.6502 0.00872 0.00356 0.0362 0.2534 0.9059
6.250 0.6775 0.00884 0.00369 0.0362 0.2484 0.9102
6.500 0.7034 0.00902 0.00386 0.0366 0.2424 0.9147
6.750 0.7300 0.00916 0.00401 0.0367 0.2381 0.9191
7.000 0.7569 0.00930 0.00416 0.0368 0.2332 0.9233
7.250 0.7828 0.00949 0.00432 0.0370 0.2276 0.9271
7.500 0.8086 0.00963 0.00449 0.0373 0.2230 0.9310
7.750 0.8344 0.00978 0.00465 0.0376 0.2180 0.9351
8.000 0.8594 0.01001 0.00485 0.0379 0.2120 0.9395
8.250 0.8848 0.01016 0.00502 0.0382 0.2079 0.9435
8.500 0.9095 0.01031 0.00520 0.0387 0.2038 0.9478
8.750 0.9333 0.01053 0.00541 0.0393 0.1987 0.9527
9.000 0.9571 0.01074 0.00563 0.0398 0.1942 0.9576
9.250 0.9820 0.01090 0.00582 0.0402 0.1906 0.9622
9.500 1.0056 0.01112 0.00605 0.0407 0.1862 0.9679
9.750 1.0311 0.01143 0.00635 0.0407 0.1807 0.9725
10.000 1.0606 0.01162 0.00658 0.0400 0.1776 0.9761
10.250 1.0889 0.01189 0.00685 0.0395 0.1732 0.9805
10.500 1.1188 0.01229 0.00723 0.0383 0.1675 0.9836
10.750 1.1523 0.01255 0.00753 0.0367 0.1641 0.9853
11.000 1.1847 0.01288 0.00787 0.0351 0.1594 0.9871
11.250 1.2154 0.01336 0.00833 0.0337 0.1536 0.9894
11.500 1.2469 0.01364 0.00865 0.0324 0.1502 0.9919
11.750 1.2777 0.01404 0.00906 0.0309 0.1451 0.9944
12.000 1.3086 0.01455 0.00956 0.0293 0.1397 0.9971
12.250 1.3403 0.01494 0.00998 0.0277 0.1354 0.9994
12.500 1.3432 0.01530 0.01034 0.0314 0.1317 1.0000
12.750 1.3389 0.01578 0.01082 0.0362 0.1279 1.0000
13.000 1.3483 0.01622 0.01130 0.0385 0.1248 1.0000
13.250 1.3563 0.01691 0.01199 0.0405 0.1203 1.0000
13.500 1.3631 0.01780 0.01289 0.0423 0.1155 1.0000
13.750 1.3738 0.01861 0.01372 0.0435 0.1113 1.0000
14.000 1.3800 0.01977 0.01488 0.0447 0.1066 1.0000
14.250 1.3883 0.02089 0.01604 0.0456 0.1026 1.0000
14.500 1.3956 0.02217 0.01733 0.0464 0.0989 1.0000
15.000 1.4058 0.02528 0.02051 0.0476 0.0918 1.0000
15.250 1.4091 0.02710 0.02235 0.0480 0.0882 1.0000
15.500 1.4082 0.02936 0.02464 0.0482 0.0847 1.0000
15.750 1.4124 0.03126 0.02660 0.0482 0.0822 1.0000
16.000 1.4137 0.03347 0.02886 0.0482 0.0800 1.0000
16.250 1.4098 0.03623 0.03165 0.0479 0.0772 1.0000
16.500 1.4042 0.03926 0.03475 0.0475 0.0749 1.0000
16.750 1.4046 0.04174 0.03730 0.0471 0.0734 1.0000
17.000 1.4007 0.04478 0.04041 0.0464 0.0713 1.0000
17.250 1.3939 0.04821 0.04389 0.0455 0.0698 1.0000
17.500 1.3820 0.05235 0.04809 0.0443 0.0675 1.0000
17.750 1.3728 0.05627 0.05210 0.0431 0.0663 1.0000
18.000 1.3691 0.05962 0.05552 0.0420 0.0649 1.0000
18.250 1.3609 0.06357 0.05955 0.0406 0.0635 1.0000
18.500 1.3494 0.06800 0.06405 0.0390 0.0620 1.0000
18.750 1.3347 0.07294 0.06905 0.0371 0.0604 1.0000
19.000 1.3184 0.07821 0.07440 0.0350 0.0591 1.0000
19.250 1.3115 0.08229 0.07856 0.0333 0.0579 1.0000
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