MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 500,000 Max Cl/Cd: 73.42 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh92-il-500000-n5.txt Download as CSV file: xf-mh92-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9215 0.11053 0.10735 0.0114 1.0000 0.0064
-16.500 -0.9513 0.09935 0.09596 0.0044 1.0000 0.0064
-16.250 -0.9788 0.08930 0.08568 -0.0018 1.0000 0.0064
-16.000 -0.9946 0.08202 0.07825 -0.0063 1.0000 0.0064
-15.750 -1.0128 0.07467 0.07071 -0.0106 1.0000 0.0064
-15.500 -1.0249 0.06875 0.06465 -0.0139 1.0000 0.0065
-15.250 -1.0362 0.06334 0.05907 -0.0167 1.0000 0.0064
-15.000 -1.0440 0.05872 0.05431 -0.0188 1.0000 0.0065
-14.750 -1.0519 0.05438 0.04982 -0.0205 1.0000 0.0065
-14.500 -1.0571 0.05064 0.04593 -0.0216 1.0000 0.0065
-14.250 -1.0598 0.04742 0.04260 -0.0223 1.0000 0.0066
-14.000 -1.0627 0.04434 0.03938 -0.0226 1.0000 0.0065
-13.750 -1.0613 0.04191 0.03685 -0.0225 1.0000 0.0067
-13.500 -1.0612 0.03944 0.03426 -0.0221 1.0000 0.0067
-13.250 -1.0593 0.03725 0.03195 -0.0214 1.0000 0.0067
-13.000 -1.0555 0.03534 0.02993 -0.0205 1.0000 0.0068
-12.750 -1.0510 0.03355 0.02804 -0.0195 1.0000 0.0069
-12.500 -1.0451 0.03194 0.02633 -0.0182 1.0000 0.0069
-12.250 -1.0384 0.03044 0.02473 -0.0169 1.0000 0.0070
-12.000 -1.0302 0.02911 0.02332 -0.0154 1.0000 0.0071
-11.750 -1.0208 0.02789 0.02200 -0.0139 1.0000 0.0072
-11.500 -1.0118 0.02667 0.02070 -0.0123 1.0000 0.0072
-11.250 -1.0006 0.02562 0.01957 -0.0106 1.0000 0.0074
-11.000 -0.9889 0.02464 0.01852 -0.0090 1.0000 0.0075
-10.750 -0.9771 0.02367 0.01748 -0.0072 1.0000 0.0075
-10.500 -0.9636 0.02283 0.01657 -0.0055 1.0000 0.0077
-10.250 -0.9447 0.02199 0.01565 -0.0049 0.9486 0.0078
-10.000 -0.9318 0.02130 0.01481 -0.0027 0.8960 0.0079
-9.750 -0.9229 0.02064 0.01401 0.0004 0.8675 0.0080
-9.500 -0.9111 0.02007 0.01334 0.0030 0.8460 0.0082
-9.250 -0.8971 0.01952 0.01268 0.0053 0.8278 0.0082
-9.000 -0.8798 0.01899 0.01206 0.0070 0.8118 0.0085
-8.750 -0.8611 0.01849 0.01147 0.0084 0.7967 0.0087
-8.500 -0.8417 0.01799 0.01089 0.0098 0.7830 0.0089
-8.250 -0.8217 0.01751 0.01031 0.0111 0.7696 0.0091
-8.000 -0.8008 0.01706 0.00978 0.0123 0.7565 0.0094
-7.750 -0.7792 0.01661 0.00925 0.0134 0.7437 0.0097
-7.500 -0.7571 0.01620 0.00875 0.0144 0.7317 0.0100
-7.250 -0.7350 0.01576 0.00823 0.0154 0.7194 0.0104
-7.000 -0.7120 0.01536 0.00779 0.0163 0.7074 0.0111
-6.750 -0.6882 0.01504 0.00740 0.0170 0.6959 0.0118
-6.250 -0.6403 0.01434 0.00660 0.0185 0.6724 0.0137
-6.000 -0.6158 0.01405 0.00623 0.0192 0.6612 0.0151
-5.750 -0.5912 0.01372 0.00587 0.0198 0.6493 0.0167
-5.500 -0.5663 0.01343 0.00554 0.0204 0.6383 0.0192
-5.000 -0.5161 0.01285 0.00492 0.0215 0.6154 0.0293
-4.750 -0.4911 0.01255 0.00462 0.0221 0.6046 0.0399
-4.500 -0.4665 0.01221 0.00433 0.0226 0.5930 0.0568
-4.250 -0.4425 0.01178 0.00403 0.0233 0.5824 0.0872
-4.000 -0.4194 0.01129 0.00371 0.0240 0.5716 0.1340
-3.750 -0.3965 0.01075 0.00342 0.0248 0.5610 0.1938
-3.500 -0.3737 0.01024 0.00316 0.0255 0.5508 0.2605
-3.250 -0.3502 0.00981 0.00295 0.0262 0.5400 0.3233
-3.000 -0.3260 0.00945 0.00278 0.0269 0.5302 0.3768
-2.750 -0.3019 0.00912 0.00262 0.0275 0.5193 0.4303
-2.500 -0.2778 0.00879 0.00249 0.0283 0.5090 0.4868
-2.250 -0.2527 0.00857 0.00238 0.0288 0.4991 0.5308
-2.000 -0.2263 0.00843 0.00230 0.0292 0.4887 0.5604
-1.750 -0.1996 0.00833 0.00223 0.0296 0.4781 0.5866
-1.500 -0.1729 0.00824 0.00217 0.0299 0.4677 0.6124
-1.250 -0.1461 0.00815 0.00213 0.0302 0.4582 0.6395
-1.000 -0.1193 0.00810 0.00210 0.0306 0.4477 0.6655
-0.750 -0.0919 0.00806 0.00210 0.0309 0.4375 0.6888
-0.500 -0.0644 0.00806 0.00210 0.0311 0.4282 0.7083
-0.250 -0.0365 0.00807 0.00211 0.0312 0.4179 0.7249
0.000 -0.0086 0.00811 0.00213 0.0314 0.4085 0.7395
0.250 0.0195 0.00816 0.00215 0.0315 0.3988 0.7525
0.500 0.0476 0.00821 0.00218 0.0315 0.3900 0.7649
0.750 0.0756 0.00828 0.00222 0.0316 0.3802 0.7754
1.000 0.1039 0.00834 0.00226 0.0316 0.3718 0.7854
1.250 0.1319 0.00843 0.00231 0.0317 0.3630 0.7946
1.500 0.1602 0.00850 0.00236 0.0317 0.3547 0.8033
1.750 0.1881 0.00860 0.00244 0.0318 0.3462 0.8116
2.000 0.2162 0.00869 0.00250 0.0319 0.3389 0.8204
2.250 0.2439 0.00879 0.00259 0.0320 0.3308 0.8288
2.500 0.2718 0.00890 0.00267 0.0320 0.3235 0.8373
2.750 0.2996 0.00900 0.00277 0.0322 0.3164 0.8435
3.000 0.3273 0.00913 0.00287 0.0322 0.3101 0.8499
3.250 0.3554 0.00923 0.00295 0.0322 0.3033 0.8559
3.500 0.3828 0.00937 0.00307 0.0323 0.2962 0.8607
3.750 0.4105 0.00948 0.00318 0.0324 0.2906 0.8661
4.000 0.4382 0.00961 0.00328 0.0324 0.2847 0.8718
4.250 0.4654 0.00976 0.00342 0.0325 0.2788 0.8764
4.500 0.4928 0.00988 0.00355 0.0326 0.2733 0.8812
4.750 0.5199 0.01002 0.00368 0.0327 0.2671 0.8865
5.000 0.5468 0.01019 0.00383 0.0328 0.2618 0.8919
5.250 0.5738 0.01031 0.00398 0.0330 0.2571 0.8965
5.500 0.6002 0.01047 0.00414 0.0333 0.2514 0.9021
5.750 0.6262 0.01067 0.00432 0.0335 0.2461 0.9082
6.000 0.6528 0.01080 0.00448 0.0337 0.2413 0.9126
6.250 0.6789 0.01097 0.00466 0.0340 0.2364 0.9174
6.500 0.7044 0.01119 0.00486 0.0343 0.2311 0.9225
6.750 0.7306 0.01134 0.00503 0.0345 0.2266 0.9271
7.000 0.7567 0.01152 0.00524 0.0347 0.2215 0.9312
7.250 0.7817 0.01175 0.00546 0.0351 0.2166 0.9361
7.500 0.8069 0.01193 0.00566 0.0354 0.2122 0.9414
7.750 0.8334 0.01214 0.00589 0.0355 0.2068 0.9454
8.000 0.8588 0.01241 0.00615 0.0356 0.2012 0.9501
8.250 0.8841 0.01261 0.00638 0.0359 0.1964 0.9556
8.500 0.9117 0.01287 0.00665 0.0355 0.1910 0.9597
8.750 0.9392 0.01320 0.00697 0.0351 0.1862 0.9640
9.000 0.9665 0.01344 0.00725 0.0349 0.1820 0.9689
9.250 0.9961 0.01374 0.00758 0.0340 0.1770 0.9725
9.750 1.0555 0.01443 0.00831 0.0321 0.1680 0.9802
10.000 1.0849 0.01479 0.00869 0.0311 0.1628 0.9837
10.250 1.1153 0.01525 0.00915 0.0298 0.1581 0.9867
10.500 1.1461 0.01561 0.00956 0.0285 0.1538 0.9901
10.750 1.1749 0.01606 0.01002 0.0274 0.1485 0.9944
11.000 1.2034 0.01657 0.01056 0.0263 0.1440 0.9993
11.250 1.2163 0.01692 0.01095 0.0283 0.1405 1.0000
11.500 1.2261 0.01735 0.01139 0.0308 0.1366 1.0000
11.750 1.2314 0.01790 0.01194 0.0338 0.1327 1.0000
12.000 1.2408 0.01842 0.01251 0.0360 0.1296 1.0000
12.250 1.2507 0.01907 0.01320 0.0378 0.1259 1.0000
12.500 1.2588 0.01994 0.01408 0.0394 0.1216 1.0000
12.750 1.2685 0.02083 0.01501 0.0406 0.1181 1.0000
13.000 1.2784 0.02180 0.01602 0.0416 0.1141 1.0000
13.250 1.2854 0.02304 0.01728 0.0426 0.1100 1.0000
13.500 1.2932 0.02431 0.01860 0.0433 0.1067 1.0000
13.750 1.3007 0.02569 0.02003 0.0439 0.1027 1.0000
14.000 1.3044 0.02744 0.02180 0.0443 0.0989 1.0000
14.250 1.3096 0.02915 0.02357 0.0446 0.0960 1.0000
14.500 1.3133 0.03105 0.02552 0.0448 0.0922 1.0000
14.750 1.3134 0.03337 0.02787 0.0447 0.0888 1.0000
15.000 1.3140 0.03571 0.03028 0.0446 0.0859 1.0000
15.250 1.3145 0.03813 0.03277 0.0443 0.0830 1.0000
15.500 1.3119 0.04094 0.03563 0.0438 0.0805 1.0000
15.750 1.3060 0.04419 0.03893 0.0431 0.0783 1.0000
16.000 1.3035 0.04715 0.04197 0.0424 0.0763 1.0000
16.250 1.3002 0.05029 0.04520 0.0416 0.0743 1.0000
16.500 1.2947 0.05379 0.04878 0.0405 0.0725 1.0000
16.750 1.2869 0.05769 0.05274 0.0391 0.0707 1.0000
17.000 1.2760 0.06208 0.05719 0.0375 0.0689 1.0000
17.250 1.2716 0.06571 0.06092 0.0361 0.0675 1.0000
17.500 1.2650 0.06971 0.06500 0.0345 0.0657 1.0000
17.750 1.2568 0.07402 0.06939 0.0328 0.0642 1.0000
18.000 1.2465 0.07869 0.07414 0.0308 0.0627 1.0000
18.250 1.2333 0.08387 0.07937 0.0285 0.0610 1.0000
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Polar data table (+)
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