MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 50,000 Max Cl/Cd: 33.72 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh200-il-50000.txt Download as CSV file: xf-mh200-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 200 12.97%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3727 0.10024 0.09386 -0.0289 1.0000 0.3129
-8.250 -0.4837 0.08620 0.08031 -0.0413 1.0000 0.1675
-8.000 -0.5238 0.08404 0.07832 -0.0388 1.0000 0.1662
-7.750 -0.5591 0.08035 0.07468 -0.0376 1.0000 0.1531
-7.500 -0.5907 0.07600 0.07032 -0.0366 1.0000 0.1401
-7.250 -0.6157 0.07149 0.06565 -0.0356 1.0000 0.1286
-7.000 -0.6376 0.06645 0.06025 -0.0347 1.0000 0.1173
-6.750 -0.6513 0.06123 0.05444 -0.0336 1.0000 0.1071
-6.500 -0.6430 0.05745 0.05053 -0.0322 1.0000 0.1020
-6.250 -0.6393 0.05300 0.04559 -0.0310 1.0000 0.0964
-6.000 -0.6297 0.04920 0.04097 -0.0297 1.0000 0.0910
-5.750 -0.6149 0.04580 0.03724 -0.0286 1.0000 0.0892
-5.500 -0.5976 0.04272 0.03368 -0.0275 1.0000 0.0883
-5.250 -0.5781 0.04010 0.03055 -0.0265 1.0000 0.0896
-5.000 -0.5569 0.03798 0.02782 -0.0253 1.0000 0.0921
-4.750 -0.5357 0.03555 0.02535 -0.0244 1.0000 0.0961
-4.500 -0.5129 0.03367 0.02327 -0.0230 1.0000 0.1010
-4.250 -0.4908 0.03204 0.02155 -0.0214 1.0000 0.1099
-4.000 -0.4698 0.03059 0.02017 -0.0197 1.0000 0.1269
-3.750 -0.4498 0.02905 0.01878 -0.0178 1.0000 0.1585
-3.500 -0.4412 0.02422 0.01703 -0.0144 1.0000 0.4882
-3.250 -0.4549 0.02546 0.01913 -0.0010 1.0000 0.7281
-3.000 -0.4620 0.02668 0.02029 0.0098 1.0000 0.8015
-2.750 -0.4652 0.02787 0.02139 0.0213 1.0000 0.8712
-2.500 -0.1700 0.03177 0.02321 -0.0202 1.0000 0.9897
-2.250 -0.1350 0.03137 0.02250 -0.0246 1.0000 1.0000
-2.000 -0.1365 0.03094 0.02192 -0.0220 1.0000 1.0000
-1.750 -0.1373 0.03056 0.02142 -0.0194 1.0000 1.0000
-1.500 -0.1377 0.03021 0.02096 -0.0167 1.0000 1.0000
-1.250 -0.1376 0.02989 0.02052 -0.0140 1.0000 1.0000
-1.000 -0.1373 0.02959 0.02012 -0.0113 1.0000 1.0000
-0.750 -0.1367 0.02931 0.01973 -0.0086 1.0000 1.0000
-0.500 -0.1359 0.02904 0.01936 -0.0058 1.0000 1.0000
-0.250 -0.1347 0.02877 0.01899 -0.0031 1.0000 1.0000
0.000 -0.1328 0.02854 0.01867 -0.0005 1.0000 1.0000
0.250 -0.1297 0.02835 0.01839 0.0019 1.0000 1.0000
0.500 -0.1229 0.02829 0.01823 0.0037 1.0000 1.0000
0.750 -0.1118 0.02841 0.01824 0.0046 1.0000 1.0000
1.000 -0.0974 0.02868 0.01841 0.0050 1.0000 1.0000
1.250 -0.0808 0.02908 0.01869 0.0050 1.0000 1.0000
1.500 -0.0630 0.02959 0.01911 0.0048 1.0000 1.0000
1.750 -0.0445 0.03019 0.01962 0.0044 1.0000 1.0000
2.000 -0.0257 0.03087 0.02023 0.0038 1.0000 1.0000
2.250 -0.0068 0.03163 0.02092 0.0032 1.0000 1.0000
2.500 0.0301 0.03324 0.02247 -0.0008 0.9914 1.0000
2.750 0.0912 0.03566 0.02484 -0.0090 0.9656 1.0000
3.000 0.1378 0.03736 0.02653 -0.0143 0.9455 1.0000
3.250 0.1806 0.03886 0.02804 -0.0186 0.9252 1.0000
3.500 0.2174 0.04009 0.02930 -0.0217 0.9055 1.0000
3.750 0.2651 0.04160 0.03085 -0.0263 0.8855 1.0000
4.000 0.2942 0.04253 0.03183 -0.0278 0.8648 1.0000
4.250 0.3351 0.04366 0.03304 -0.0309 0.8442 1.0000
4.500 0.3704 0.04464 0.03412 -0.0329 0.8232 1.0000
4.750 0.4069 0.04548 0.03507 -0.0348 0.8020 1.0000
5.000 0.4458 0.04622 0.03593 -0.0368 0.7810 1.0000
5.250 0.4788 0.04683 0.03670 -0.0379 0.7591 1.0000
5.500 0.5198 0.04718 0.03721 -0.0395 0.7380 1.0000
5.750 0.5530 0.04747 0.03768 -0.0400 0.7155 1.0000
6.000 0.5920 0.04740 0.03781 -0.0408 0.6938 1.0000
6.250 0.6325 0.04695 0.03759 -0.0412 0.6716 1.0000
6.500 0.6673 0.04646 0.03735 -0.0409 0.6481 1.0000
6.750 0.7279 0.04398 0.03521 -0.0415 0.6276 1.0000
7.000 0.7681 0.04220 0.03370 -0.0403 0.6029 1.0000
7.250 0.8457 0.03718 0.02916 -0.0404 0.5788 1.0000
7.500 0.9389 0.03151 0.02386 -0.0423 0.5378 1.0000
7.750 0.9924 0.02959 0.02178 -0.0422 0.4832 1.0000
8.000 1.0141 0.03007 0.02208 -0.0400 0.4342 1.0000
8.250 1.0351 0.03099 0.02273 -0.0380 0.3873 1.0000
8.500 1.0524 0.03228 0.02379 -0.0360 0.3449 1.0000
8.750 1.0687 0.03380 0.02513 -0.0340 0.3056 1.0000
9.000 1.0847 0.03548 0.02659 -0.0322 0.2696 1.0000
9.250 1.1024 0.03747 0.02839 -0.0307 0.2372 1.0000
9.500 1.1189 0.03959 0.03039 -0.0292 0.2093 1.0000
9.750 1.1308 0.04195 0.03292 -0.0272 0.1880 1.0000
10.000 1.1530 0.04451 0.03532 -0.0266 0.1676 1.0000
10.250 1.1680 0.04734 0.03833 -0.0252 0.1534 1.0000
10.500 1.1822 0.05008 0.04115 -0.0239 0.1404 1.0000
10.750 1.1775 0.05340 0.04510 -0.0203 0.1353 1.0000
11.000 1.1952 0.05690 0.04868 -0.0197 0.1263 1.0000
11.250 1.1795 0.06017 0.05248 -0.0156 0.1236 1.0000
11.500 1.1638 0.06340 0.05607 -0.0118 0.1209 1.0000
11.750 1.1858 0.06754 0.06014 -0.0121 0.1135 1.0000
12.000 1.1645 0.07121 0.06413 -0.0085 0.1132 1.0000
12.250 1.1414 0.07525 0.06845 -0.0058 0.1132 1.0000
12.500 1.1171 0.07971 0.07315 -0.0041 0.1133 1.0000
12.750 1.0941 0.08475 0.07838 -0.0034 0.1136 1.0000
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Polar data table (+)
Polar graphs
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