MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 200,000 Max Cl/Cd: 61.71 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh82-il-200000-n5.txt Download as CSV file: xf-mh82-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 82 13.31%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3838 0.08747 0.08365 -0.0003 0.6889 0.0184
-8.250 -0.3727 0.08633 0.08245 -0.0003 0.6728 0.0193
-7.750 -0.4143 0.06824 0.06438 -0.0134 0.6628 0.0149
-7.500 -0.4146 0.06337 0.05942 -0.0173 0.6525 0.0148
-7.250 -0.4136 0.05807 0.05398 -0.0207 0.6435 0.0146
-7.000 -0.4121 0.05186 0.04756 -0.0237 0.6350 0.0143
-6.750 -0.4104 0.04494 0.04026 -0.0256 0.6275 0.0139
-6.500 -0.4066 0.03777 0.03250 -0.0265 0.6201 0.0134
-6.250 -0.3955 0.03238 0.02640 -0.0262 0.6113 0.0131
-6.000 -0.3776 0.02880 0.02223 -0.0256 0.6013 0.0130
-5.750 -0.3561 0.02637 0.01929 -0.0249 0.5912 0.0130
-5.500 -0.3324 0.02450 0.01703 -0.0243 0.5800 0.0131
-5.250 -0.3076 0.02298 0.01517 -0.0238 0.5697 0.0133
-5.000 -0.2820 0.02169 0.01358 -0.0232 0.5591 0.0135
-4.750 -0.2558 0.02056 0.01221 -0.0227 0.5486 0.0138
-4.500 -0.2295 0.01958 0.01100 -0.0222 0.5388 0.0142
-4.250 -0.2027 0.01869 0.00992 -0.0217 0.5284 0.0147
-4.000 -0.1761 0.01794 0.00903 -0.0213 0.5189 0.0152
-3.750 -0.1495 0.01733 0.00835 -0.0209 0.5090 0.0158
-3.500 -0.1224 0.01685 0.00776 -0.0206 0.4997 0.0171
-3.250 -0.0953 0.01639 0.00720 -0.0202 0.4903 0.0187
-3.000 -0.0680 0.01599 0.00673 -0.0200 0.4813 0.0207
-2.750 -0.0407 0.01556 0.00619 -0.0196 0.4728 0.0226
-2.500 -0.0131 0.01518 0.00574 -0.0193 0.4643 0.0254
-2.250 0.0144 0.01484 0.00532 -0.0190 0.4560 0.0311
-2.000 0.0418 0.01442 0.00495 -0.0188 0.4476 0.0445
-1.750 0.0686 0.01397 0.00466 -0.0185 0.4397 0.0893
-1.500 0.0958 0.01362 0.00450 -0.0184 0.4323 0.1453
-1.250 0.1225 0.01326 0.00437 -0.0182 0.4249 0.2158
-1.000 0.1483 0.01278 0.00426 -0.0180 0.4180 0.3246
-0.750 0.1726 0.01218 0.00419 -0.0174 0.4107 0.4747
-0.500 0.1942 0.01159 0.00416 -0.0159 0.4044 0.6479
-0.250 0.2160 0.01120 0.00428 -0.0135 0.3977 0.8102
0.000 0.2487 0.01123 0.00431 -0.0136 0.3910 0.8982
0.250 0.2865 0.01132 0.00429 -0.0150 0.3844 0.9402
0.500 0.3270 0.01142 0.00426 -0.0172 0.3771 0.9648
0.750 0.3685 0.01155 0.00421 -0.0198 0.3706 0.9835
1.000 0.4189 0.01162 0.00416 -0.0242 0.3630 0.9997
1.250 0.4442 0.01176 0.00417 -0.0237 0.3580 1.0000
1.500 0.4691 0.01191 0.00421 -0.0231 0.3534 1.0000
1.750 0.4943 0.01205 0.00428 -0.0226 0.3482 1.0000
2.000 0.5194 0.01221 0.00434 -0.0220 0.3432 1.0000
2.250 0.5445 0.01240 0.00441 -0.0214 0.3388 1.0000
2.500 0.5700 0.01255 0.00453 -0.0209 0.3340 1.0000
2.750 0.5955 0.01273 0.00464 -0.0204 0.3297 1.0000
3.000 0.6209 0.01294 0.00476 -0.0200 0.3259 1.0000
3.250 0.6466 0.01315 0.00490 -0.0195 0.3220 1.0000
3.500 0.6725 0.01334 0.00507 -0.0191 0.3177 1.0000
3.750 0.6985 0.01355 0.00523 -0.0188 0.3135 1.0000
4.000 0.7243 0.01378 0.00539 -0.0184 0.3100 1.0000
4.250 0.7503 0.01403 0.00559 -0.0181 0.3067 1.0000
4.500 0.7766 0.01425 0.00582 -0.0179 0.3030 1.0000
4.750 0.8028 0.01448 0.00604 -0.0176 0.2993 1.0000
5.000 0.8288 0.01474 0.00625 -0.0173 0.2958 1.0000
5.250 0.8546 0.01504 0.00646 -0.0171 0.2928 1.0000
5.500 0.8810 0.01529 0.00677 -0.0169 0.2896 1.0000
5.750 0.9071 0.01555 0.00706 -0.0167 0.2863 1.0000
6.000 0.9331 0.01583 0.00733 -0.0165 0.2830 1.0000
6.250 0.9589 0.01613 0.00760 -0.0163 0.2799 1.0000
6.500 0.9845 0.01646 0.00790 -0.0161 0.2771 1.0000
6.750 1.0104 0.01676 0.00827 -0.0159 0.2742 1.0000
7.000 1.0361 0.01708 0.00864 -0.0157 0.2711 1.0000
7.250 1.0615 0.01739 0.00898 -0.0155 0.2680 1.0000
7.500 1.0867 0.01773 0.00931 -0.0153 0.2651 1.0000
7.750 1.1117 0.01812 0.00966 -0.0151 0.2625 1.0000
8.000 1.1368 0.01848 0.01012 -0.0149 0.2598 1.0000
8.250 1.1615 0.01885 0.01058 -0.0147 0.2569 1.0000
8.500 1.1860 0.01923 0.01101 -0.0145 0.2539 1.0000
8.750 1.2102 0.01961 0.01141 -0.0142 0.2510 1.0000
9.000 1.2342 0.02003 0.01183 -0.0139 0.2486 1.0000
9.250 1.2578 0.02049 0.01237 -0.0137 0.2461 1.0000
9.500 1.2810 0.02094 0.01294 -0.0134 0.2431 1.0000
9.750 1.3038 0.02138 0.01348 -0.0130 0.2401 1.0000
10.000 1.3263 0.02184 0.01398 -0.0127 0.2373 1.0000
10.250 1.3485 0.02232 0.01448 -0.0123 0.2349 1.0000
10.500 1.3702 0.02286 0.01507 -0.0119 0.2325 1.0000
10.750 1.3903 0.02342 0.01580 -0.0114 0.2295 1.0000
11.000 1.4100 0.02399 0.01648 -0.0108 0.2264 1.0000
11.250 1.4291 0.02456 0.01714 -0.0102 0.2237 1.0000
11.500 1.4477 0.02514 0.01774 -0.0096 0.2211 1.0000
11.750 1.4652 0.02579 0.01845 -0.0088 0.2185 1.0000
12.000 1.4791 0.02658 0.01942 -0.0079 0.2155 1.0000
12.250 1.4899 0.02738 0.02035 -0.0065 0.2126 1.0000
12.500 1.4988 0.02825 0.02132 -0.0052 0.2098 1.0000
12.750 1.5088 0.02918 0.02228 -0.0042 0.2073 1.0000
13.000 1.5173 0.03031 0.02348 -0.0033 0.2047 1.0000
13.250 1.5215 0.03185 0.02520 -0.0027 0.2017 1.0000
13.500 1.5260 0.03347 0.02696 -0.0023 0.1987 1.0000
13.750 1.5309 0.03513 0.02871 -0.0021 0.1958 1.0000
14.000 1.5376 0.03669 0.03028 -0.0019 0.1931 1.0000
14.250 1.5376 0.03902 0.03278 -0.0021 0.1902 1.0000
14.500 1.5348 0.04175 0.03568 -0.0026 0.1869 1.0000
14.750 1.5334 0.04442 0.03846 -0.0031 0.1838 1.0000
15.000 1.5346 0.04681 0.04089 -0.0035 0.1810 1.0000
15.250 1.5298 0.05001 0.04420 -0.0044 0.1780 1.0000
15.500 1.5175 0.05427 0.04866 -0.0058 0.1746 1.0000
15.750 1.5073 0.05837 0.05288 -0.0073 0.1712 1.0000
16.000 1.5055 0.06139 0.05592 -0.0082 0.1683 1.0000
16.250 1.4918 0.06629 0.06097 -0.0102 0.1651 1.0000
16.500 1.4672 0.07298 0.06784 -0.0131 0.1614 1.0000
16.750 1.4556 0.07794 0.07288 -0.0153 0.1577 1.0000
17.000 1.4580 0.08073 0.07566 -0.0163 0.1546 1.0000
17.250 1.4127 0.09133 0.08651 -0.0213 0.1504 1.0000
17.500 1.3916 0.09827 0.09354 -0.0246 0.1463 1.0000
17.750 1.4082 0.09886 0.09409 -0.0247 0.1433 1.0000
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Polar data table (+)
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