MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 500,000 Max Cl/Cd: 87.09 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh82-il-500000.txt Download as CSV file: xf-mh82-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3730 0.09480 0.09196 0.0059 0.6942 0.0201
-8.500 -0.3705 0.09103 0.08815 0.0039 0.6812 0.0202
-8.250 -0.3713 0.08659 0.08369 0.0012 0.6698 0.0209
-7.750 -0.3167 0.06874 0.06588 -0.0015 0.6179 0.0226
-7.500 -0.3173 0.06483 0.06194 -0.0032 0.6101 0.0229
-7.250 -0.3242 0.05998 0.05710 -0.0060 0.6033 0.0230
-7.000 -0.3410 0.05473 0.05186 -0.0102 0.5983 0.0231
-6.750 -0.3474 0.04863 0.04566 -0.0151 0.5928 0.0234
-6.500 -0.3493 0.04220 0.03911 -0.0188 0.5870 0.0239
-6.250 -0.3686 0.02808 0.02431 -0.0238 0.5884 0.0262
-6.000 -0.3502 0.02612 0.02231 -0.0238 0.5774 0.0265
-5.750 -0.3318 0.02411 0.02022 -0.0238 0.5676 0.0271
-5.500 -0.3170 0.02042 0.01574 -0.0233 0.5596 0.0304
-5.250 -0.3004 0.01639 0.01164 -0.0236 0.5515 0.0311
-5.000 -0.2780 0.01480 0.00997 -0.0235 0.5414 0.0318
-4.750 -0.2636 0.01989 0.01339 -0.0222 0.5451 0.0172
-4.500 -0.2363 0.01795 0.01084 -0.0212 0.5359 0.0150
-4.250 -0.2095 0.01662 0.00937 -0.0207 0.5261 0.0149
-4.000 -0.1824 0.01561 0.00823 -0.0203 0.5166 0.0148
-3.750 -0.1551 0.01483 0.00731 -0.0199 0.5068 0.0148
-3.500 -0.1274 0.01418 0.00657 -0.0195 0.4972 0.0149
-3.250 -0.1006 0.01343 0.00573 -0.0190 0.4882 0.0152
-3.000 -0.0734 0.01282 0.00512 -0.0187 0.4794 0.0159
-2.750 -0.0458 0.01246 0.00468 -0.0184 0.4708 0.0168
-2.500 -0.0176 0.01213 0.00429 -0.0181 0.4620 0.0181
-2.250 0.0101 0.01174 0.00385 -0.0179 0.4535 0.0200
-2.000 0.0383 0.01142 0.00351 -0.0176 0.4448 0.0233
-1.750 0.0663 0.01113 0.00319 -0.0174 0.4370 0.0341
-1.500 0.0933 0.01049 0.00293 -0.0172 0.4293 0.1195
-1.250 0.1209 0.01024 0.00283 -0.0171 0.4217 0.1782
-1.000 0.1484 0.00990 0.00275 -0.0170 0.4143 0.2564
-0.750 0.1748 0.00944 0.00268 -0.0169 0.4068 0.3858
-0.500 0.1983 0.00866 0.00266 -0.0162 0.4001 0.6092
-0.250 0.2167 0.00799 0.00276 -0.0136 0.3936 0.8359
0.000 0.2403 0.00799 0.00286 -0.0118 0.3873 0.9209
0.250 0.2727 0.00804 0.00288 -0.0121 0.3806 0.9565
0.500 0.3119 0.00818 0.00288 -0.0140 0.3734 0.9745
0.750 0.3555 0.00827 0.00288 -0.0169 0.3664 0.9850
1.000 0.4014 0.00839 0.00286 -0.0204 0.3590 0.9919
1.250 0.4457 0.00849 0.00286 -0.0237 0.3528 0.9982
1.500 0.4773 0.00857 0.00287 -0.0244 0.3472 1.0000
1.750 0.5022 0.00870 0.00291 -0.0238 0.3423 1.0000
2.000 0.5271 0.00883 0.00298 -0.0231 0.3376 1.0000
2.250 0.5524 0.00891 0.00303 -0.0225 0.3328 1.0000
2.500 0.5776 0.00905 0.00310 -0.0220 0.3282 1.0000
2.750 0.6026 0.00926 0.00321 -0.0214 0.3237 1.0000
3.000 0.6284 0.00935 0.00330 -0.0209 0.3202 1.0000
3.250 0.6543 0.00948 0.00339 -0.0204 0.3161 1.0000
3.500 0.6799 0.00964 0.00350 -0.0199 0.3121 1.0000
3.750 0.7054 0.00988 0.00366 -0.0195 0.3079 1.0000
4.000 0.7319 0.00999 0.00378 -0.0191 0.3047 1.0000
4.250 0.7584 0.01014 0.00391 -0.0188 0.3013 1.0000
4.500 0.7848 0.01031 0.00405 -0.0185 0.2979 1.0000
4.750 0.8110 0.01056 0.00423 -0.0182 0.2941 1.0000
5.000 0.8377 0.01075 0.00441 -0.0180 0.2910 1.0000
5.250 0.8648 0.01090 0.00457 -0.0178 0.2879 1.0000
5.500 0.8917 0.01107 0.00475 -0.0177 0.2849 1.0000
5.750 0.9185 0.01128 0.00493 -0.0175 0.2818 1.0000
6.000 0.9447 0.01160 0.00517 -0.0174 0.2783 1.0000
6.250 0.9717 0.01178 0.00540 -0.0173 0.2756 1.0000
6.500 0.9988 0.01195 0.00560 -0.0172 0.2729 1.0000
6.750 1.0257 0.01215 0.00581 -0.0171 0.2701 1.0000
7.000 1.0523 0.01238 0.00603 -0.0170 0.2673 1.0000
7.250 1.0784 0.01269 0.00630 -0.0169 0.2641 1.0000
7.500 1.1047 0.01298 0.00661 -0.0168 0.2613 1.0000
7.750 1.1315 0.01317 0.00686 -0.0167 0.2589 1.0000
8.000 1.1580 0.01339 0.00712 -0.0166 0.2562 1.0000
8.250 1.1843 0.01363 0.00737 -0.0165 0.2535 1.0000
8.500 1.2100 0.01393 0.00765 -0.0164 0.2506 1.0000
8.750 1.2351 0.01436 0.00806 -0.0162 0.2475 1.0000
9.000 1.2612 0.01457 0.00836 -0.0162 0.2454 1.0000
9.250 1.2870 0.01481 0.00867 -0.0161 0.2428 1.0000
9.500 1.3125 0.01507 0.00896 -0.0160 0.2399 1.0000
9.750 1.3375 0.01537 0.00928 -0.0158 0.2372 1.0000
10.000 1.3615 0.01584 0.00972 -0.0156 0.2342 1.0000
10.250 1.3861 0.01615 0.01011 -0.0154 0.2317 1.0000
10.500 1.4107 0.01641 0.01047 -0.0152 0.2290 1.0000
10.750 1.4349 0.01672 0.01083 -0.0150 0.2262 1.0000
11.000 1.4583 0.01705 0.01119 -0.0147 0.2233 1.0000
11.250 1.4803 0.01757 0.01169 -0.0143 0.2200 1.0000
11.500 1.5029 0.01793 0.01216 -0.0140 0.2175 1.0000
11.750 1.5252 0.01827 0.01259 -0.0136 0.2146 1.0000
12.000 1.5467 0.01864 0.01303 -0.0131 0.2115 1.0000
12.250 1.5666 0.01910 0.01351 -0.0125 0.2085 1.0000
12.500 1.5846 0.01973 0.01415 -0.0118 0.2053 1.0000
12.750 1.6034 0.02015 0.01471 -0.0111 0.2026 1.0000
13.000 1.6198 0.02065 0.01530 -0.0102 0.1996 1.0000
13.250 1.6312 0.02126 0.01596 -0.0086 0.1967 1.0000
13.500 1.6391 0.02215 0.01685 -0.0070 0.1937 1.0000
13.750 1.6487 0.02308 0.01788 -0.0059 0.1909 1.0000
14.000 1.6589 0.02405 0.01898 -0.0052 0.1878 1.0000
14.250 1.6677 0.02523 0.02023 -0.0046 0.1848 1.0000
14.500 1.6735 0.02671 0.02174 -0.0040 0.1817 1.0000
14.750 1.6793 0.02833 0.02342 -0.0037 0.1786 1.0000
15.000 1.6863 0.02995 0.02518 -0.0037 0.1752 1.0000
15.250 1.6903 0.03190 0.02720 -0.0037 0.1716 1.0000
15.500 1.6894 0.03433 0.02965 -0.0038 0.1682 1.0000
15.750 1.6914 0.03665 0.03210 -0.0041 0.1646 1.0000
16.000 1.6908 0.03930 0.03485 -0.0046 0.1606 1.0000
16.250 1.6844 0.04258 0.03815 -0.0053 0.1569 1.0000
16.500 1.6784 0.04591 0.04158 -0.0061 0.1530 1.0000
16.750 1.6726 0.04934 0.04512 -0.0070 0.1492 1.0000
17.000 1.6600 0.05361 0.04942 -0.0083 0.1452 1.0000
17.250 1.6494 0.05784 0.05373 -0.0096 0.1418 1.0000
17.500 1.6394 0.06219 0.05819 -0.0112 0.1377 1.0000
17.750 1.6247 0.06721 0.06326 -0.0131 0.1338 1.0000
18.000 1.6113 0.07217 0.06827 -0.0150 0.1305 1.0000
18.250 1.5988 0.07717 0.07340 -0.0170 0.1266 1.0000
18.500 1.5821 0.08289 0.07916 -0.0194 0.1227 1.0000
18.750 1.5668 0.08844 0.08477 -0.0218 0.1191 1.0000
19.000 1.5524 0.09410 0.09054 -0.0243 0.1151 1.0000
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Polar data table (+)
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