MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 50,000 Max Cl/Cd: 31.28 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh61-il-50000.txt Download as CSV file: xf-mh61-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5321 0.11783 0.11180 0.0194 1.0000 0.2361
-9.250 -0.5262 0.11367 0.10769 0.0184 1.0000 0.2427
-9.000 -0.5404 0.11186 0.10599 0.0155 1.0000 0.2523
-8.750 -0.5214 0.10683 0.10097 0.0161 1.0000 0.2643
-8.500 -0.5094 0.10247 0.09665 0.0159 1.0000 0.2740
-8.000 -0.4756 0.07656 0.07134 -0.0122 1.0000 0.1461
-7.750 -0.5019 0.06717 0.06198 -0.0206 1.0000 0.1198
-7.500 -0.5127 0.06024 0.05498 -0.0242 1.0000 0.1096
-7.250 -0.5903 0.06288 0.05668 -0.0266 1.0000 0.1029
-7.000 -0.5756 0.05770 0.05151 -0.0271 1.0000 0.0967
-6.750 -0.5740 0.05184 0.04494 -0.0284 1.0000 0.0885
-6.500 -0.5610 0.04739 0.04024 -0.0283 1.0000 0.0854
-6.250 -0.5493 0.04316 0.03551 -0.0277 1.0000 0.0823
-6.000 -0.5370 0.03967 0.03147 -0.0263 1.0000 0.0807
-5.750 -0.5252 0.03713 0.02864 -0.0243 1.0000 0.0834
-5.500 -0.5150 0.03493 0.02606 -0.0218 1.0000 0.0856
-5.250 -0.5035 0.03287 0.02349 -0.0191 1.0000 0.0888
-5.000 -0.4881 0.03053 0.02087 -0.0168 1.0000 0.0919
-4.750 -0.4705 0.02851 0.01878 -0.0149 1.0000 0.0975
-4.500 -0.4528 0.02669 0.01689 -0.0129 1.0000 0.1098
-4.250 -0.4357 0.02503 0.01528 -0.0108 1.0000 0.1331
-4.000 -0.4197 0.02281 0.01363 -0.0086 1.0000 0.2029
-3.750 -0.4211 0.02040 0.01297 -0.0030 1.0000 0.4574
-3.500 -0.4190 0.02014 0.01312 0.0028 1.0000 0.5685
-3.250 -0.4128 0.01992 0.01314 0.0085 1.0000 0.6566
-3.000 -0.4012 0.01961 0.01302 0.0133 1.0000 0.7382
-2.750 -0.3737 0.01948 0.01298 0.0161 1.0000 0.8366
-2.500 -0.1210 0.02057 0.01252 -0.0208 1.0000 0.9904
-2.250 -0.1285 0.01980 0.01160 -0.0202 1.0000 1.0000
-2.000 -0.1511 0.01941 0.01107 -0.0152 1.0000 1.0000
-1.750 -0.1540 0.01935 0.01076 -0.0121 1.0000 1.0000
-1.500 -0.1491 0.01946 0.01060 -0.0099 1.0000 1.0000
-1.250 -0.1409 0.01965 0.01055 -0.0081 1.0000 1.0000
-1.000 -0.1305 0.01991 0.01059 -0.0065 1.0000 1.0000
-0.750 -0.1186 0.02023 0.01069 -0.0052 1.0000 1.0000
-0.500 -0.0772 0.02095 0.01114 -0.0094 0.9902 1.0000
-0.250 -0.0300 0.02180 0.01178 -0.0147 0.9777 1.0000
0.000 0.0153 0.02264 0.01245 -0.0194 0.9647 1.0000
0.250 0.0587 0.02348 0.01313 -0.0237 0.9515 1.0000
0.500 0.1004 0.02430 0.01386 -0.0275 0.9377 1.0000
0.750 0.1403 0.02512 0.01461 -0.0309 0.9237 1.0000
1.000 0.1787 0.02594 0.01539 -0.0339 0.9093 1.0000
1.250 0.2159 0.02676 0.01618 -0.0365 0.8946 1.0000
1.500 0.2531 0.02757 0.01700 -0.0390 0.8797 1.0000
1.750 0.2917 0.02838 0.01783 -0.0416 0.8646 1.0000
2.000 0.3315 0.02915 0.01867 -0.0442 0.8495 1.0000
2.250 0.3689 0.02989 0.01947 -0.0461 0.8343 1.0000
2.500 0.3887 0.03074 0.02035 -0.0453 0.8179 1.0000
2.750 0.4124 0.03156 0.02122 -0.0450 0.8014 1.0000
3.000 0.4390 0.03233 0.02213 -0.0449 0.7851 1.0000
3.250 0.4678 0.03304 0.02293 -0.0449 0.7691 1.0000
3.500 0.4986 0.03362 0.02364 -0.0448 0.7533 1.0000
3.750 0.5164 0.03450 0.02461 -0.0434 0.7361 1.0000
4.000 0.5360 0.03532 0.02559 -0.0421 0.7185 1.0000
4.250 0.5616 0.03589 0.02629 -0.0410 0.7017 1.0000
4.500 0.5906 0.03618 0.02675 -0.0399 0.6855 1.0000
4.750 0.6083 0.03698 0.02770 -0.0382 0.6671 1.0000
5.000 0.6305 0.03746 0.02834 -0.0365 0.6486 1.0000
5.250 0.6608 0.03720 0.02836 -0.0345 0.6315 1.0000
5.500 0.6803 0.03765 0.02899 -0.0324 0.6111 1.0000
5.750 0.7106 0.03688 0.02846 -0.0297 0.5918 1.0000
6.000 0.7352 0.03645 0.02826 -0.0268 0.5699 1.0000
6.250 0.7720 0.03418 0.02622 -0.0226 0.5489 1.0000
6.500 0.8003 0.03262 0.02485 -0.0187 0.5219 1.0000
6.750 0.8252 0.03129 0.02379 -0.0148 0.4887 1.0000
7.000 0.8515 0.02947 0.02200 -0.0103 0.4474 1.0000
7.250 0.8722 0.02829 0.02067 -0.0061 0.3917 1.0000
7.500 0.8853 0.02830 0.02024 -0.0022 0.3185 1.0000
7.750 0.8910 0.02989 0.02126 0.0011 0.2424 1.0000
8.000 0.9001 0.03238 0.02323 0.0037 0.1858 1.0000
8.250 0.9116 0.03491 0.02546 0.0058 0.1472 1.0000
8.500 0.9315 0.03806 0.02852 0.0074 0.1223 1.0000
8.750 0.9491 0.04094 0.03128 0.0087 0.1038 1.0000
9.000 0.9662 0.04491 0.03574 0.0103 0.0959 1.0000
9.250 0.9808 0.04865 0.03958 0.0114 0.0878 1.0000
9.500 0.9838 0.05209 0.04358 0.0131 0.0829 1.0000
9.750 0.9929 0.05595 0.04763 0.0143 0.0789 1.0000
10.000 0.9967 0.06049 0.05258 0.0154 0.0778 1.0000
10.250 0.9863 0.06470 0.05723 0.0168 0.0782 1.0000
10.500 0.9575 0.06871 0.06168 0.0180 0.0802 1.0000
10.750 0.9299 0.07308 0.06616 0.0181 0.0817 1.0000
11.000 0.9030 0.07833 0.07157 0.0163 0.0832 1.0000
11.250 0.8769 0.08455 0.07788 0.0131 0.0850 1.0000
11.500 0.8556 0.09129 0.08467 0.0094 0.0868 1.0000
11.750 0.8408 0.09820 0.09158 0.0059 0.0882 1.0000
12.000 0.8334 0.10483 0.09821 0.0034 0.0892 1.0000
12.250 0.7807 0.12485 0.11811 -0.0117 0.1148 1.0000
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Polar data table (+)
Polar graphs
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