MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 200,000 Max Cl/Cd: 53.68 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh82-il-200000.txt Download as CSV file: xf-mh82-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3497 0.09547 0.09242 -0.0015 0.8190 0.0482
-8.250 -0.3712 0.09023 0.08714 -0.0097 0.7987 0.0490
-8.000 -0.3739 0.08560 0.08246 -0.0116 0.7797 0.0494
-7.750 -0.3542 0.08395 0.08072 -0.0074 0.7590 0.0503
-7.500 -0.3464 0.08140 0.07809 -0.0072 0.7418 0.0513
-7.250 -0.3448 0.07833 0.07498 -0.0086 0.7268 0.0522
-7.000 -0.3476 0.07474 0.07131 -0.0114 0.7142 0.0534
-6.750 -0.3663 0.06601 0.06221 -0.0250 0.7076 0.0573
-6.500 -0.3582 0.06128 0.05741 -0.0255 0.6962 0.0582
-6.250 -0.3419 0.05916 0.05530 -0.0245 0.6818 0.0591
-6.000 -0.3270 0.05681 0.05290 -0.0244 0.6687 0.0607
-5.750 -0.3142 0.05289 0.04863 -0.0267 0.6590 0.0657
-5.500 -0.3030 0.04824 0.04371 -0.0280 0.6486 0.0688
-5.250 -0.2837 0.04612 0.04154 -0.0278 0.6365 0.0706
-5.000 -0.2676 0.04273 0.03754 -0.0286 0.6276 0.0792
-4.750 -0.2493 0.02939 0.02247 -0.0264 0.6241 0.0356
-4.500 -0.2255 0.02655 0.01952 -0.0261 0.6127 0.0338
-4.250 -0.1991 0.02373 0.01581 -0.0247 0.6024 0.0303
-4.000 -0.1727 0.02204 0.01382 -0.0240 0.5923 0.0300
-3.750 -0.1452 0.02066 0.01222 -0.0234 0.5806 0.0300
-3.500 -0.1176 0.01963 0.01092 -0.0228 0.5704 0.0304
-3.250 -0.0909 0.01835 0.00962 -0.0223 0.5598 0.0315
-3.000 -0.0637 0.01768 0.00891 -0.0219 0.5493 0.0339
-2.750 -0.0370 0.01698 0.00810 -0.0213 0.5402 0.0372
-2.500 -0.0096 0.01636 0.00747 -0.0208 0.5295 0.0410
-2.250 0.0168 0.01569 0.00675 -0.0203 0.5208 0.0463
-2.000 0.0437 0.01503 0.00615 -0.0198 0.5107 0.0615
-1.750 0.0685 0.01391 0.00560 -0.0192 0.5026 0.1849
-1.500 0.0940 0.01328 0.00543 -0.0189 0.4934 0.3023
-1.250 0.1151 0.01235 0.00534 -0.0178 0.4858 0.5248
-1.000 0.1307 0.01143 0.00554 -0.0138 0.4775 0.8293
-0.750 0.1793 0.01156 0.00559 -0.0160 0.4677 0.9528
-0.500 0.2496 0.01169 0.00539 -0.0237 0.4562 0.9878
-0.250 0.3001 0.01175 0.00525 -0.0281 0.4464 1.0000
0.000 0.3241 0.01185 0.00516 -0.0274 0.4396 1.0000
0.250 0.3485 0.01197 0.00516 -0.0267 0.4322 1.0000
0.500 0.3728 0.01208 0.00513 -0.0260 0.4252 1.0000
0.750 0.3973 0.01227 0.00516 -0.0254 0.4192 1.0000
1.000 0.4221 0.01241 0.00523 -0.0247 0.4124 1.0000
1.250 0.4468 0.01259 0.00525 -0.0241 0.4068 1.0000
1.500 0.4717 0.01280 0.00537 -0.0235 0.4009 1.0000
1.750 0.4968 0.01296 0.00546 -0.0229 0.3947 1.0000
2.000 0.5219 0.01318 0.00553 -0.0223 0.3896 1.0000
2.250 0.5472 0.01343 0.00573 -0.0218 0.3842 1.0000
2.500 0.5726 0.01364 0.00589 -0.0213 0.3789 1.0000
2.750 0.5980 0.01387 0.00600 -0.0208 0.3744 1.0000
3.000 0.6235 0.01418 0.00624 -0.0203 0.3697 1.0000
3.250 0.6493 0.01440 0.00646 -0.0199 0.3644 1.0000
3.500 0.6752 0.01464 0.00662 -0.0195 0.3599 1.0000
3.750 0.7012 0.01499 0.00684 -0.0191 0.3562 1.0000
4.000 0.7271 0.01529 0.00719 -0.0188 0.3519 1.0000
4.250 0.7533 0.01555 0.00745 -0.0185 0.3473 1.0000
4.500 0.7796 0.01582 0.00765 -0.0182 0.3433 1.0000
4.750 0.8060 0.01625 0.00794 -0.0180 0.3397 1.0000
5.000 0.8319 0.01656 0.00836 -0.0178 0.3358 1.0000
5.250 0.8581 0.01688 0.00871 -0.0176 0.3318 1.0000
5.500 0.8846 0.01718 0.00898 -0.0174 0.3281 1.0000
5.750 0.9112 0.01757 0.00925 -0.0172 0.3248 1.0000
6.000 0.9368 0.01800 0.00977 -0.0170 0.3211 1.0000
6.250 0.9625 0.01839 0.01025 -0.0169 0.3174 1.0000
6.500 0.9887 0.01874 0.01061 -0.0167 0.3139 1.0000
6.750 1.0152 0.01908 0.01089 -0.0166 0.3108 1.0000
7.000 1.0414 0.01963 0.01139 -0.0165 0.3076 1.0000
7.250 1.0659 0.02007 0.01200 -0.0163 0.3040 1.0000
7.500 1.0910 0.02052 0.01253 -0.0161 0.3006 1.0000
7.750 1.1169 0.02090 0.01292 -0.0159 0.2974 1.0000
8.000 1.1434 0.02130 0.01325 -0.0159 0.2945 1.0000
8.250 1.1682 0.02193 0.01393 -0.0157 0.2914 1.0000
8.500 1.1913 0.02249 0.01468 -0.0154 0.2878 1.0000
8.750 1.2154 0.02301 0.01528 -0.0152 0.2846 1.0000
9.000 1.2408 0.02341 0.01569 -0.0151 0.2815 1.0000
9.250 1.2674 0.02384 0.01605 -0.0150 0.2787 1.0000
9.500 1.2898 0.02460 0.01694 -0.0148 0.2756 1.0000
9.750 1.3107 0.02531 0.01785 -0.0144 0.2722 1.0000
10.000 1.3333 0.02587 0.01851 -0.0140 0.2689 1.0000
10.250 1.3583 0.02624 0.01888 -0.0139 0.2660 1.0000
10.500 1.3852 0.02675 0.01932 -0.0139 0.2632 1.0000
10.750 1.4033 0.02768 0.02047 -0.0134 0.2601 1.0000
11.000 1.4207 0.02849 0.02149 -0.0127 0.2565 1.0000
11.250 1.4417 0.02903 0.02211 -0.0123 0.2532 1.0000
11.500 1.4668 0.02938 0.02245 -0.0121 0.2504 1.0000
11.750 1.4926 0.03006 0.02308 -0.0122 0.2475 1.0000
12.000 1.5017 0.03118 0.02451 -0.0109 0.2440 1.0000
12.250 1.5153 0.03205 0.02557 -0.0100 0.2405 1.0000
12.500 1.5359 0.03246 0.02601 -0.0095 0.2374 1.0000
12.750 1.5647 0.03266 0.02612 -0.0096 0.2345 1.0000
13.000 1.5729 0.03394 0.02760 -0.0084 0.2313 1.0000
13.250 1.5723 0.03534 0.02926 -0.0065 0.2279 1.0000
13.500 1.5788 0.03621 0.03024 -0.0050 0.2248 1.0000
13.750 1.6022 0.03636 0.03036 -0.0046 0.2218 1.0000
14.000 1.6241 0.03695 0.03094 -0.0043 0.2186 1.0000
14.250 1.5971 0.03954 0.03381 -0.0014 0.2162 1.0000
14.500 1.5783 0.04241 0.03688 -0.0004 0.2132 1.0000
14.750 1.5823 0.04389 0.03844 -0.0001 0.2101 1.0000
15.000 1.6250 0.04254 0.03696 0.0003 0.2067 1.0000
15.250 1.6020 0.04634 0.04098 0.0004 0.2040 1.0000
15.500 1.5505 0.05350 0.04844 -0.0014 0.2011 1.0000
15.750 1.5155 0.05990 0.05502 -0.0037 0.1977 1.0000
16.000 1.5765 0.05541 0.05040 -0.0014 0.1944 1.0000
16.250 1.5683 0.05890 0.05398 -0.0024 0.1912 1.0000
16.500 1.0317 0.15528 0.15065 -0.0511 0.1547 1.0000
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Polar data table (+)
Polar graphs
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