MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 500,000 Max Cl/Cd: 90.49 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh82-il-500000-n5.txt Download as CSV file: xf-mh82-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4076 0.08589 0.08256 0.0025 0.5930 0.0094
-8.500 -0.4031 0.08310 0.07976 0.0009 0.5836 0.0089
-8.000 -0.5668 0.03379 0.02945 -0.0256 0.6074 0.0074
-7.500 -0.5391 0.02748 0.02226 -0.0248 0.5874 0.0073
-7.250 -0.5202 0.02521 0.01962 -0.0242 0.5768 0.0073
-7.000 -0.4989 0.02335 0.01743 -0.0236 0.5665 0.0073
-6.750 -0.4761 0.02181 0.01559 -0.0231 0.5561 0.0073
-6.500 -0.4522 0.02044 0.01396 -0.0226 0.5457 0.0073
-6.250 -0.4276 0.01923 0.01251 -0.0221 0.5357 0.0074
-6.000 -0.4025 0.01811 0.01117 -0.0216 0.5255 0.0074
-5.750 -0.3767 0.01721 0.01011 -0.0212 0.5160 0.0075
-5.500 -0.3504 0.01644 0.00919 -0.0208 0.5060 0.0076
-5.250 -0.3238 0.01577 0.00841 -0.0205 0.4966 0.0077
-5.000 -0.2969 0.01521 0.00773 -0.0202 0.4875 0.0078
-4.750 -0.2697 0.01469 0.00713 -0.0198 0.4780 0.0079
-4.500 -0.2424 0.01424 0.00657 -0.0195 0.4691 0.0081
-4.250 -0.2149 0.01381 0.00606 -0.0193 0.4606 0.0083
-4.000 -0.1873 0.01342 0.00559 -0.0190 0.4525 0.0086
-3.750 -0.1595 0.01306 0.00515 -0.0187 0.4438 0.0088
-3.500 -0.1316 0.01275 0.00475 -0.0185 0.4357 0.0093
-3.250 -0.1035 0.01248 0.00441 -0.0183 0.4274 0.0096
-3.000 -0.0756 0.01218 0.00404 -0.0181 0.4202 0.0103
-2.750 -0.0473 0.01196 0.00378 -0.0179 0.4131 0.0111
-2.500 -0.0190 0.01179 0.00353 -0.0177 0.4056 0.0121
-2.250 0.0094 0.01159 0.00330 -0.0176 0.3984 0.0137
-2.000 0.0377 0.01144 0.00310 -0.0174 0.3907 0.0163
-1.750 0.0661 0.01127 0.00292 -0.0173 0.3842 0.0227
-1.500 0.0942 0.01105 0.00276 -0.0172 0.3777 0.0406
-1.250 0.1220 0.01080 0.00263 -0.0171 0.3716 0.0797
-1.000 0.1501 0.01059 0.00256 -0.0170 0.3658 0.1214
-0.750 0.1782 0.01042 0.00249 -0.0170 0.3592 0.1648
-0.500 0.2058 0.01014 0.00244 -0.0169 0.3534 0.2392
-0.250 0.2330 0.00981 0.00240 -0.0169 0.3475 0.3389
0.000 0.2598 0.00946 0.00238 -0.0167 0.3421 0.4544
0.250 0.2862 0.00912 0.00238 -0.0164 0.3374 0.5707
0.500 0.3115 0.00877 0.00240 -0.0157 0.3326 0.6898
0.750 0.3350 0.00850 0.00247 -0.0144 0.3274 0.8061
1.000 0.3594 0.00845 0.00255 -0.0132 0.3227 0.8770
1.250 0.3867 0.00848 0.00261 -0.0125 0.3180 0.9161
1.500 0.4167 0.00856 0.00265 -0.0126 0.3132 0.9420
1.750 0.4502 0.00868 0.00270 -0.0135 0.3087 0.9606
2.000 0.4904 0.00877 0.00274 -0.0159 0.3046 0.9791
2.250 0.5343 0.00887 0.00278 -0.0190 0.2995 0.9921
2.500 0.5770 0.00901 0.00283 -0.0221 0.2945 1.0000
2.750 0.6025 0.00913 0.00291 -0.0215 0.2911 1.0000
3.000 0.6282 0.00924 0.00299 -0.0210 0.2879 1.0000
3.250 0.6540 0.00937 0.00307 -0.0205 0.2846 1.0000
3.500 0.6798 0.00952 0.00318 -0.0201 0.2810 1.0000
3.750 0.7055 0.00970 0.00330 -0.0197 0.2775 1.0000
4.000 0.7319 0.00982 0.00341 -0.0193 0.2746 1.0000
4.250 0.7583 0.00996 0.00353 -0.0190 0.2717 1.0000
4.500 0.7849 0.01012 0.00366 -0.0187 0.2687 1.0000
4.750 0.8114 0.01030 0.00381 -0.0185 0.2656 1.0000
5.000 0.8379 0.01050 0.00397 -0.0182 0.2625 1.0000
5.250 0.8650 0.01064 0.00412 -0.0181 0.2600 1.0000
5.500 0.8920 0.01080 0.00428 -0.0179 0.2573 1.0000
5.750 0.9189 0.01098 0.00445 -0.0178 0.2546 1.0000
6.000 0.9457 0.01118 0.00464 -0.0177 0.2517 1.0000
6.250 0.9723 0.01141 0.00485 -0.0175 0.2488 1.0000
6.500 0.9992 0.01161 0.00505 -0.0175 0.2464 1.0000
6.750 1.0262 0.01179 0.00525 -0.0174 0.2441 1.0000
7.000 1.0530 0.01198 0.00547 -0.0173 0.2416 1.0000
7.250 1.0796 0.01220 0.00569 -0.0172 0.2388 1.0000
7.500 1.1059 0.01245 0.00594 -0.0171 0.2360 1.0000
7.750 1.1319 0.01274 0.00621 -0.0170 0.2334 1.0000
8.000 1.1586 0.01293 0.00645 -0.0170 0.2314 1.0000
8.250 1.1851 0.01315 0.00671 -0.0169 0.2291 1.0000
8.500 1.2112 0.01340 0.00698 -0.0168 0.2263 1.0000
8.750 1.2370 0.01367 0.00727 -0.0167 0.2236 1.0000
9.000 1.2622 0.01398 0.00759 -0.0166 0.2209 1.0000
9.250 1.2874 0.01428 0.00792 -0.0164 0.2187 1.0000
9.500 1.3132 0.01453 0.00823 -0.0163 0.2164 1.0000
9.750 1.3384 0.01481 0.00856 -0.0162 0.2136 1.0000
10.000 1.3631 0.01512 0.00890 -0.0160 0.2109 1.0000
10.250 1.3871 0.01548 0.00929 -0.0158 0.2081 1.0000
10.500 1.4106 0.01587 0.00970 -0.0155 0.2053 1.0000
10.750 1.4349 0.01617 0.01007 -0.0153 0.2028 1.0000
11.000 1.4584 0.01651 0.01048 -0.0151 0.1998 1.0000
11.250 1.4809 0.01691 0.01092 -0.0147 0.1966 1.0000
11.500 1.5020 0.01739 0.01142 -0.0143 0.1936 1.0000
11.750 1.5236 0.01781 0.01190 -0.0138 0.1908 1.0000
12.000 1.5447 0.01823 0.01240 -0.0134 0.1877 1.0000
12.250 1.5640 0.01874 0.01296 -0.0127 0.1842 1.0000
12.500 1.5806 0.01936 0.01361 -0.0119 0.1810 1.0000
12.750 1.5962 0.01996 0.01428 -0.0109 0.1781 1.0000
13.000 1.6084 0.02060 0.01500 -0.0094 0.1752 1.0000
13.250 1.6175 0.02147 0.01594 -0.0080 0.1719 1.0000
13.500 1.6242 0.02264 0.01715 -0.0069 0.1688 1.0000
13.750 1.6322 0.02389 0.01847 -0.0062 0.1659 1.0000
14.000 1.6414 0.02517 0.01983 -0.0057 0.1623 1.0000
14.250 1.6474 0.02679 0.02153 -0.0054 0.1590 1.0000
14.500 1.6491 0.02889 0.02367 -0.0052 0.1557 1.0000
14.750 1.6545 0.03075 0.02563 -0.0052 0.1527 1.0000
15.000 1.6576 0.03291 0.02787 -0.0053 0.1492 1.0000
15.250 1.6547 0.03573 0.03074 -0.0056 0.1454 1.0000
15.500 1.6502 0.03879 0.03387 -0.0061 0.1420 1.0000
15.750 1.6483 0.04165 0.03683 -0.0066 0.1384 1.0000
16.000 1.6392 0.04537 0.04061 -0.0074 0.1344 1.0000
16.250 1.6259 0.04966 0.04497 -0.0085 0.1312 1.0000
16.500 1.6183 0.05336 0.04877 -0.0095 0.1274 1.0000
16.750 1.6041 0.05809 0.05357 -0.0110 0.1234 1.0000
17.000 1.5858 0.06348 0.05902 -0.0128 0.1200 1.0000
17.250 1.5746 0.06811 0.06374 -0.0145 0.1159 1.0000
17.500 1.5571 0.07373 0.06942 -0.0167 0.1118 1.0000
17.750 1.5385 0.07963 0.07540 -0.0190 0.1083 1.0000
18.000 1.5234 0.08520 0.08104 -0.0213 0.1040 1.0000
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Polar data table (+)
Polar graphs
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