MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.34 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh82-il-1000000.txt Download as CSV file: xf-mh82-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3306 0.08662 0.08410 0.0083 0.5940 0.0126
-8.750 -0.3273 0.08282 0.08029 0.0068 0.5862 0.0127
-8.500 -0.3275 0.07818 0.07563 0.0048 0.5793 0.0128
-8.250 -0.3273 0.07400 0.07143 0.0031 0.5722 0.0129
-8.000 -0.3283 0.06953 0.06696 0.0010 0.5655 0.0131
-7.750 -0.3342 0.06434 0.06177 -0.0015 0.5601 0.0133
-7.500 -0.3435 0.05898 0.05641 -0.0045 0.5554 0.0134
-7.250 -0.3686 0.05269 0.05015 -0.0095 0.5532 0.0132
-7.000 -0.3830 0.04450 0.04188 -0.0160 0.5503 0.0133
-6.750 -0.3885 0.03649 0.03371 -0.0200 0.5467 0.0135
-6.500 -0.4095 0.02138 0.01762 -0.0226 0.5492 0.0150
-6.250 -0.4019 0.01588 0.01186 -0.0227 0.5418 0.0154
-6.000 -0.3808 0.01425 0.01012 -0.0225 0.5324 0.0156
-5.750 -0.3591 0.01273 0.00844 -0.0223 0.5230 0.0158
-5.500 -0.3367 0.01133 0.00688 -0.0220 0.5144 0.0162
-5.250 -0.3255 0.01592 0.00979 -0.0206 0.5165 0.0098
-5.000 -0.2979 0.01544 0.00917 -0.0202 0.5063 0.0097
-4.750 -0.2701 0.01494 0.00858 -0.0199 0.4968 0.0096
-4.500 -0.2437 0.01384 0.00736 -0.0195 0.4874 0.0095
-4.250 -0.2165 0.01305 0.00647 -0.0191 0.4787 0.0095
-4.000 -0.1892 0.01244 0.00576 -0.0188 0.4700 0.0095
-3.750 -0.1615 0.01192 0.00517 -0.0184 0.4617 0.0095
-3.500 -0.1337 0.01151 0.00468 -0.0182 0.4531 0.0095
-3.250 -0.1056 0.01115 0.00426 -0.0179 0.4446 0.0096
-3.000 -0.0782 0.01060 0.00363 -0.0176 0.4362 0.0099
-2.750 -0.0500 0.01027 0.00325 -0.0174 0.4283 0.0103
-2.500 -0.0215 0.01008 0.00300 -0.0172 0.4203 0.0110
-2.250 0.0072 0.00989 0.00277 -0.0171 0.4132 0.0119
-2.000 0.0357 0.00969 0.00251 -0.0169 0.4052 0.0136
-1.750 0.0644 0.00950 0.00231 -0.0168 0.3984 0.0171
-1.500 0.0928 0.00925 0.00210 -0.0167 0.3906 0.0358
-1.250 0.1208 0.00895 0.00198 -0.0166 0.3839 0.0844
-1.000 0.1492 0.00877 0.00191 -0.0165 0.3770 0.1238
-0.750 0.1775 0.00861 0.00187 -0.0165 0.3705 0.1701
-0.500 0.2054 0.00832 0.00182 -0.0165 0.3645 0.2508
-0.250 0.2327 0.00797 0.00179 -0.0164 0.3578 0.3666
0.000 0.2585 0.00736 0.00178 -0.0162 0.3523 0.5618
0.500 0.3056 0.00657 0.00190 -0.0138 0.3403 0.8706
0.750 0.3309 0.00655 0.00195 -0.0128 0.3360 0.9157
1.000 0.3572 0.00659 0.00199 -0.0120 0.3309 0.9428
1.250 0.3861 0.00669 0.00203 -0.0118 0.3251 0.9615
1.500 0.4186 0.00676 0.00206 -0.0125 0.3205 0.9743
1.750 0.4535 0.00685 0.00209 -0.0137 0.3153 0.9832
2.000 0.4917 0.00698 0.00214 -0.0157 0.3095 0.9881
2.250 0.5303 0.00706 0.00218 -0.0178 0.3056 0.9927
2.500 0.5742 0.00715 0.00221 -0.0210 0.3009 0.9977
2.750 0.6103 0.00727 0.00226 -0.0226 0.2960 1.0000
3.000 0.6354 0.00739 0.00234 -0.0220 0.2919 1.0000
3.250 0.6610 0.00747 0.00240 -0.0215 0.2892 1.0000
3.500 0.6866 0.00757 0.00248 -0.0209 0.2859 1.0000
3.750 0.7124 0.00770 0.00257 -0.0205 0.2825 1.0000
4.000 0.7381 0.00788 0.00269 -0.0200 0.2782 1.0000
4.250 0.7645 0.00798 0.00278 -0.0196 0.2757 1.0000
4.500 0.7911 0.00808 0.00288 -0.0193 0.2731 1.0000
4.750 0.8178 0.00821 0.00298 -0.0190 0.2702 1.0000
5.000 0.8445 0.00836 0.00310 -0.0188 0.2671 1.0000
5.250 0.8712 0.00857 0.00328 -0.0186 0.2631 1.0000
5.500 0.8986 0.00868 0.00339 -0.0185 0.2610 1.0000
5.750 0.9261 0.00879 0.00351 -0.0184 0.2588 1.0000
6.000 0.9536 0.00893 0.00364 -0.0183 0.2563 1.0000
6.250 0.9809 0.00909 0.00379 -0.0182 0.2535 1.0000
6.500 1.0080 0.00930 0.00397 -0.0182 0.2501 1.0000
6.750 1.0352 0.00950 0.00416 -0.0181 0.2472 1.0000
7.000 1.0629 0.00962 0.00431 -0.0181 0.2454 1.0000
7.250 1.0904 0.00976 0.00447 -0.0181 0.2433 1.0000
7.500 1.1178 0.00993 0.00464 -0.0182 0.2407 1.0000
7.750 1.1449 0.01013 0.00483 -0.0182 0.2379 1.0000
8.000 1.1714 0.01040 0.00508 -0.0181 0.2344 1.0000
8.250 1.1985 0.01059 0.00529 -0.0181 0.2324 1.0000
8.500 1.2259 0.01073 0.00547 -0.0181 0.2305 1.0000
8.750 1.2530 0.01090 0.00566 -0.0182 0.2281 1.0000
9.000 1.2798 0.01110 0.00587 -0.0182 0.2254 1.0000
9.250 1.3060 0.01136 0.00613 -0.0182 0.2225 1.0000
9.500 1.3316 0.01169 0.00645 -0.0181 0.2192 1.0000
9.750 1.3586 0.01183 0.00665 -0.0181 0.2174 1.0000
10.000 1.3852 0.01201 0.00687 -0.0181 0.2150 1.0000
10.250 1.4113 0.01224 0.00712 -0.0181 0.2122 1.0000
10.500 1.4367 0.01253 0.00741 -0.0180 0.2091 1.0000
10.750 1.4610 0.01290 0.00778 -0.0178 0.2055 1.0000
11.000 1.4873 0.01307 0.00802 -0.0178 0.2034 1.0000
11.250 1.5129 0.01330 0.00829 -0.0178 0.2007 1.0000
11.500 1.5375 0.01360 0.00861 -0.0176 0.1974 1.0000
11.750 1.5606 0.01401 0.00902 -0.0174 0.1937 1.0000
12.000 1.5848 0.01431 0.00937 -0.0172 0.1912 1.0000
12.250 1.6092 0.01457 0.00969 -0.0170 0.1883 1.0000
12.500 1.6321 0.01493 0.01007 -0.0167 0.1848 1.0000
12.750 1.6528 0.01542 0.01057 -0.0162 0.1809 1.0000
13.000 1.6750 0.01579 0.01099 -0.0159 0.1781 1.0000
13.250 1.6967 0.01615 0.01140 -0.0155 0.1749 1.0000
13.500 1.7158 0.01665 0.01193 -0.0148 0.1710 1.0000
13.750 1.7317 0.01730 0.01259 -0.0138 0.1668 1.0000
14.000 1.7502 0.01772 0.01308 -0.0131 0.1633 1.0000
14.250 1.7591 0.01841 0.01380 -0.0111 0.1592 1.0000
14.500 1.7617 0.01951 0.01491 -0.0090 0.1546 1.0000
14.750 1.7717 0.02041 0.01588 -0.0080 0.1504 1.0000
15.000 1.7727 0.02207 0.01755 -0.0068 0.1445 1.0000
15.250 1.7788 0.02355 0.01908 -0.0062 0.1405 1.0000
15.500 1.7807 0.02550 0.02107 -0.0058 0.1354 1.0000
15.750 1.7784 0.02797 0.02358 -0.0056 0.1311 1.0000
16.000 1.7810 0.03009 0.02577 -0.0056 0.1275 1.0000
16.250 1.7759 0.03305 0.02878 -0.0058 0.1234 1.0000
16.500 1.7623 0.03698 0.03274 -0.0063 0.1162 1.0000
16.750 1.7608 0.03976 0.03563 -0.0067 0.1159 1.0000
17.000 1.7324 0.04554 0.04141 -0.0079 0.1077 1.0000
17.250 1.7226 0.04939 0.04536 -0.0088 0.1058 1.0000
17.500 1.6961 0.05536 0.05138 -0.0105 0.1008 1.0000
17.750 1.6737 0.06116 0.05726 -0.0124 0.0967 1.0000
18.000 1.6593 0.06610 0.06228 -0.0140 0.0947 1.0000
18.250 1.6322 0.07290 0.06915 -0.0166 0.0908 1.0000
18.500 1.6232 0.07736 0.07372 -0.0183 0.0908 1.0000
18.750 1.5975 0.08432 0.08075 -0.0211 0.0868 1.0000
19.000 1.5815 0.09003 0.08654 -0.0235 0.0845 1.0000
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Polar data table (+)
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