MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 200,000 Max Cl/Cd: 58.29 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh80-il-200000-n5.txt Download as CSV file: xf-mh80-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 80 12.72%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5169 0.09255 0.08950 0.0144 1.0000 0.0134
-9.250 -0.5170 0.08812 0.08512 0.0118 1.0000 0.0133
-9.000 -0.5210 0.08275 0.07980 0.0083 1.0000 0.0131
-8.750 -0.5257 0.07664 0.07364 0.0031 0.8728 0.0129
-8.500 -0.5421 0.06970 0.06656 -0.0028 0.8215 0.0126
-8.250 -0.5650 0.06262 0.05928 -0.0060 0.7931 0.0124
-7.750 -0.6330 0.03864 0.03360 -0.0067 0.7689 0.0108
-7.500 -0.6239 0.03552 0.03002 -0.0052 0.7482 0.0108
-7.250 -0.6110 0.03268 0.02669 -0.0038 0.7293 0.0108
-7.000 -0.5953 0.03007 0.02360 -0.0024 0.7112 0.0108
-6.750 -0.5763 0.02809 0.02125 -0.0013 0.6936 0.0109
-6.500 -0.5554 0.02645 0.01932 -0.0003 0.6769 0.0111
-6.250 -0.5330 0.02496 0.01752 0.0006 0.6607 0.0112
-6.000 -0.5096 0.02369 0.01598 0.0014 0.6452 0.0114
-5.500 -0.4607 0.02143 0.01326 0.0029 0.6152 0.0120
-5.250 -0.4356 0.02041 0.01203 0.0036 0.6011 0.0125
-5.000 -0.4102 0.01948 0.01091 0.0043 0.5875 0.0130
-4.750 -0.3847 0.01869 0.00992 0.0050 0.5745 0.0135
-4.500 -0.3594 0.01804 0.00919 0.0055 0.5617 0.0142
-4.250 -0.3332 0.01755 0.00861 0.0060 0.5488 0.0157
-4.000 -0.3072 0.01699 0.00794 0.0065 0.5368 0.0171
-3.750 -0.2812 0.01649 0.00735 0.0070 0.5253 0.0186
-3.500 -0.2548 0.01599 0.00673 0.0075 0.5136 0.0202
-3.250 -0.2282 0.01554 0.00619 0.0080 0.5026 0.0225
-3.000 -0.2015 0.01514 0.00570 0.0084 0.4922 0.0270
-2.750 -0.1750 0.01468 0.00524 0.0089 0.4813 0.0372
-2.500 -0.1491 0.01414 0.00482 0.0093 0.4714 0.0674
-2.250 -0.1236 0.01360 0.00454 0.0097 0.4619 0.1338
-2.000 -0.0980 0.01312 0.00433 0.0101 0.4525 0.2081
-1.750 -0.0731 0.01263 0.00413 0.0105 0.4434 0.2959
-1.500 -0.0498 0.01199 0.00397 0.0113 0.4343 0.4215
-1.250 -0.0303 0.01118 0.00385 0.0130 0.4265 0.6026
-1.000 -0.0088 0.01068 0.00398 0.0154 0.4185 0.7692
-0.750 0.0217 0.01076 0.00411 0.0159 0.4103 0.8511
-0.500 0.0527 0.01088 0.00415 0.0160 0.4016 0.8880
-0.250 0.0834 0.01103 0.00415 0.0160 0.3935 0.9115
0.000 0.1163 0.01116 0.00417 0.0155 0.3853 0.9287
0.250 0.1493 0.01131 0.00417 0.0149 0.3779 0.9432
0.500 0.1878 0.01146 0.00421 0.0131 0.3702 0.9561
0.750 0.2363 0.01165 0.00423 0.0093 0.3618 0.9685
1.000 0.2853 0.01177 0.00423 0.0053 0.3536 0.9788
1.250 0.3285 0.01187 0.00420 0.0023 0.3465 0.9866
1.500 0.3689 0.01195 0.00418 -0.0002 0.3402 0.9928
1.750 0.4078 0.01201 0.00415 -0.0025 0.3333 0.9977
2.250 0.4639 0.01221 0.00421 -0.0027 0.3227 1.0000
2.500 0.4885 0.01233 0.00428 -0.0022 0.3179 1.0000
2.750 0.5128 0.01249 0.00435 -0.0015 0.3135 1.0000
3.000 0.5373 0.01263 0.00446 -0.0009 0.3091 1.0000
3.250 0.5617 0.01277 0.00458 -0.0003 0.3042 1.0000
3.500 0.5860 0.01294 0.00470 0.0003 0.2998 1.0000
3.750 0.6100 0.01315 0.00483 0.0009 0.2963 1.0000
4.000 0.6344 0.01331 0.00501 0.0016 0.2923 1.0000
4.250 0.6586 0.01350 0.00519 0.0022 0.2880 1.0000
4.500 0.6825 0.01370 0.00537 0.0029 0.2841 1.0000
4.750 0.7062 0.01395 0.00554 0.0035 0.2807 1.0000
5.000 0.7303 0.01415 0.00579 0.0042 0.2770 1.0000
5.250 0.7544 0.01437 0.00603 0.0048 0.2733 1.0000
5.500 0.7782 0.01461 0.00627 0.0055 0.2698 1.0000
5.750 0.8018 0.01488 0.00649 0.0061 0.2665 1.0000
6.000 0.8256 0.01514 0.00677 0.0068 0.2631 1.0000
6.250 0.8496 0.01540 0.00709 0.0074 0.2596 1.0000
6.500 0.8735 0.01567 0.00738 0.0080 0.2563 1.0000
6.750 0.8971 0.01596 0.00766 0.0086 0.2531 1.0000
7.000 0.9205 0.01630 0.00796 0.0092 0.2500 1.0000
7.250 0.9445 0.01658 0.00835 0.0097 0.2466 1.0000
7.500 0.9683 0.01690 0.00872 0.0103 0.2434 1.0000
7.750 0.9922 0.01722 0.00909 0.0108 0.2403 1.0000
8.000 1.0158 0.01756 0.00943 0.0113 0.2373 1.0000
8.250 1.0394 0.01794 0.00982 0.0117 0.2343 1.0000
8.500 1.0632 0.01830 0.01030 0.0121 0.2309 1.0000
8.750 1.0869 0.01867 0.01076 0.0126 0.2278 1.0000
9.000 1.1104 0.01905 0.01118 0.0130 0.2248 1.0000
9.250 1.1335 0.01946 0.01159 0.0134 0.2218 1.0000
9.500 1.1565 0.01990 0.01212 0.0138 0.2187 1.0000
9.750 1.1794 0.02035 0.01270 0.0142 0.2154 1.0000
10.000 1.2019 0.02079 0.01323 0.0146 0.2121 1.0000
10.250 1.2239 0.02123 0.01371 0.0151 0.2090 1.0000
10.500 1.2455 0.02174 0.01424 0.0155 0.2061 1.0000
10.750 1.2665 0.02227 0.01495 0.0160 0.2026 1.0000
11.000 1.2870 0.02281 0.01561 0.0165 0.1990 1.0000
11.250 1.3068 0.02334 0.01620 0.0171 0.1958 1.0000
11.500 1.3258 0.02392 0.01679 0.0177 0.1928 1.0000
11.750 1.3433 0.02460 0.01767 0.0184 0.1892 1.0000
12.000 1.3597 0.02529 0.01849 0.0191 0.1856 1.0000
12.250 1.3745 0.02600 0.01927 0.0200 0.1822 1.0000
12.500 1.3871 0.02677 0.02006 0.0210 0.1793 1.0000
12.750 1.3942 0.02777 0.02126 0.0224 0.1759 1.0000
13.000 1.3999 0.02896 0.02258 0.0235 0.1725 1.0000
13.250 1.4053 0.03031 0.02401 0.0241 0.1694 1.0000
13.500 1.4104 0.03180 0.02553 0.0245 0.1666 1.0000
13.750 1.4133 0.03374 0.02764 0.0244 0.1632 1.0000
14.000 1.4148 0.03591 0.02997 0.0241 0.1597 1.0000
14.250 1.4148 0.03829 0.03244 0.0236 0.1563 1.0000
14.500 1.4150 0.04071 0.03487 0.0230 0.1534 1.0000
14.750 1.4103 0.04392 0.03829 0.0219 0.1500 1.0000
15.000 1.4041 0.04736 0.04186 0.0206 0.1465 1.0000
15.250 1.3974 0.05091 0.04547 0.0192 0.1432 1.0000
15.500 1.3904 0.05452 0.04914 0.0178 0.1403 1.0000
15.750 1.3758 0.05937 0.05418 0.0157 0.1369 1.0000
16.000 1.3614 0.06431 0.05923 0.0135 0.1335 1.0000
16.250 1.3514 0.06874 0.06370 0.0115 0.1303 1.0000
16.500 1.3368 0.07410 0.06917 0.0089 0.1271 1.0000
16.750 1.3136 0.08103 0.07626 0.0054 0.1235 1.0000
17.000 1.2986 0.08678 0.08208 0.0025 0.1200 1.0000
17.250 1.2913 0.09133 0.08664 0.0003 0.1165 1.0000
17.500 1.2604 0.10011 0.09560 -0.0042 0.1129 1.0000
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Polar data table (+)
Polar graphs
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