MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 100,000 Max Cl/Cd: 42.05 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh82-il-100000-n5.txt Download as CSV file: xf-mh82-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3574 0.09536 0.09108 -0.0035 0.8319 0.0299
-8.500 -0.3531 0.09246 0.08810 -0.0038 0.8037 0.0292
-8.000 -0.3642 0.08131 0.07687 -0.0107 0.7685 0.0256
-7.750 -0.3639 0.07759 0.07312 -0.0127 0.7514 0.0253
-7.500 -0.3679 0.07330 0.06881 -0.0159 0.7364 0.0249
-7.250 -0.3686 0.06841 0.06384 -0.0197 0.7232 0.0244
-7.000 -0.3692 0.06260 0.05787 -0.0236 0.7120 0.0238
-6.500 -0.3773 0.04528 0.03947 -0.0304 0.6961 0.0217
-6.250 -0.3644 0.04161 0.03540 -0.0305 0.6835 0.0215
-6.000 -0.3496 0.03793 0.03119 -0.0303 0.6720 0.0215
-5.750 -0.3320 0.03483 0.02753 -0.0297 0.6610 0.0215
-5.500 -0.3116 0.03201 0.02415 -0.0290 0.6488 0.0218
-5.250 -0.2888 0.03071 0.02272 -0.0287 0.6364 0.0226
-5.000 -0.2654 0.02924 0.02092 -0.0280 0.6251 0.0237
-4.750 -0.2407 0.02749 0.01871 -0.0274 0.6132 0.0250
-4.500 -0.2151 0.02588 0.01667 -0.0267 0.6020 0.0259
-4.250 -0.1898 0.02468 0.01529 -0.0260 0.5916 0.0268
-4.000 -0.1634 0.02356 0.01401 -0.0255 0.5797 0.0278
-3.750 -0.1371 0.02255 0.01279 -0.0249 0.5695 0.0290
-3.500 -0.1109 0.02163 0.01168 -0.0242 0.5591 0.0307
-3.250 -0.0848 0.02095 0.01096 -0.0238 0.5483 0.0337
-3.000 -0.0589 0.02029 0.01016 -0.0231 0.5393 0.0377
-2.750 -0.0323 0.01965 0.00942 -0.0226 0.5287 0.0423
-2.500 -0.0063 0.01906 0.00878 -0.0221 0.5197 0.0513
-2.250 0.0200 0.01841 0.00820 -0.0215 0.5100 0.0707
-2.000 0.0458 0.01774 0.00777 -0.0211 0.5014 0.1275
-1.750 0.0715 0.01718 0.00751 -0.0207 0.4923 0.2079
-1.500 0.0962 0.01652 0.00730 -0.0202 0.4840 0.3274
-1.250 0.1189 0.01568 0.00719 -0.0192 0.4757 0.5179
-1.000 0.1399 0.01498 0.00725 -0.0164 0.4685 0.7463
-0.750 0.1824 0.01492 0.00724 -0.0175 0.4587 0.8980
-0.500 0.2291 0.01502 0.00709 -0.0204 0.4495 0.9550
-0.250 0.2825 0.01509 0.00685 -0.0251 0.4402 0.9882
0.000 0.3204 0.01519 0.00673 -0.0272 0.4322 1.0000
0.250 0.3445 0.01533 0.00668 -0.0265 0.4252 1.0000
0.500 0.3687 0.01550 0.00664 -0.0258 0.4191 1.0000
0.750 0.3932 0.01567 0.00670 -0.0252 0.4120 1.0000
1.000 0.4176 0.01586 0.00669 -0.0245 0.4064 1.0000
1.250 0.4423 0.01608 0.00679 -0.0239 0.4005 1.0000
1.500 0.4671 0.01630 0.00689 -0.0233 0.3943 1.0000
1.750 0.4918 0.01652 0.00693 -0.0227 0.3893 1.0000
2.000 0.5167 0.01677 0.00711 -0.0221 0.3833 1.0000
2.250 0.5418 0.01703 0.00728 -0.0216 0.3778 1.0000
2.500 0.5668 0.01729 0.00739 -0.0211 0.3734 1.0000
2.750 0.5921 0.01759 0.00763 -0.0206 0.3684 1.0000
3.000 0.6174 0.01789 0.00788 -0.0202 0.3630 1.0000
3.250 0.6428 0.01816 0.00805 -0.0198 0.3585 1.0000
3.500 0.6682 0.01848 0.00826 -0.0193 0.3544 1.0000
3.750 0.6936 0.01884 0.00865 -0.0190 0.3494 1.0000
4.000 0.7190 0.01918 0.00894 -0.0187 0.3452 1.0000
4.250 0.7446 0.01950 0.00916 -0.0183 0.3414 1.0000
4.500 0.7700 0.01988 0.00953 -0.0180 0.3374 1.0000
4.750 0.7952 0.02030 0.00998 -0.0178 0.3327 1.0000
5.000 0.8205 0.02067 0.01033 -0.0175 0.3287 1.0000
5.250 0.8461 0.02104 0.01062 -0.0171 0.3256 1.0000
5.500 0.8712 0.02148 0.01107 -0.0169 0.3221 1.0000
5.750 0.8957 0.02199 0.01166 -0.0166 0.3178 1.0000
6.000 0.9206 0.02243 0.01211 -0.0164 0.3139 1.0000
6.250 0.9458 0.02282 0.01247 -0.0161 0.3107 1.0000
6.500 0.9713 0.02326 0.01285 -0.0158 0.3080 1.0000
6.750 0.9943 0.02392 0.01367 -0.0156 0.3040 1.0000
7.000 1.0180 0.02448 0.01431 -0.0153 0.3001 1.0000
7.250 1.0423 0.02495 0.01481 -0.0150 0.2968 1.0000
7.500 1.0673 0.02538 0.01520 -0.0147 0.2941 1.0000
7.750 1.0905 0.02603 0.01593 -0.0145 0.2911 1.0000
8.000 1.1115 0.02682 0.01690 -0.0141 0.2873 1.0000
8.250 1.1337 0.02747 0.01763 -0.0138 0.2838 1.0000
8.500 1.1571 0.02798 0.01816 -0.0135 0.2808 1.0000
8.750 1.1818 0.02845 0.01861 -0.0132 0.2783 1.0000
9.000 1.2010 0.02938 0.01971 -0.0128 0.2752 1.0000
9.250 1.2184 0.03039 0.02092 -0.0122 0.2715 1.0000
9.500 1.2378 0.03118 0.02182 -0.0118 0.2682 1.0000
9.750 1.2597 0.03175 0.02243 -0.0114 0.2654 1.0000
10.250 1.2959 0.03358 0.02448 -0.0103 0.2599 1.0000
10.500 1.3054 0.03500 0.02613 -0.0094 0.2563 1.0000
10.750 1.3188 0.03606 0.02731 -0.0087 0.2532 1.0000
11.000 1.3376 0.03674 0.02805 -0.0081 0.2505 1.0000
11.250 1.3620 0.03713 0.02842 -0.0078 0.2483 1.0000
11.500 1.3547 0.03943 0.03099 -0.0062 0.2451 1.0000
11.750 1.3328 0.04253 0.03433 -0.0044 0.2418 1.0000
12.000 1.3200 0.04557 0.03752 -0.0040 0.2387 1.0000
12.250 1.3310 0.04682 0.03883 -0.0037 0.2361 1.0000
12.500 1.3642 0.04623 0.03822 -0.0030 0.2340 1.0000
13.000 1.1634 0.07620 0.06865 -0.0153 0.2196 1.0000
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Polar data table (+)
Polar graphs
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