MH 81 13% (mh81-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 81 13% (mh81-il) Reynolds number: 100,000 Max Cl/Cd: 28.85 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh81-il-100000.txt Download as CSV file: xf-mh81-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 81 13%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3905 0.10336 0.09950 0.0088 1.0000 0.0988
-8.500 -0.3951 0.10001 0.09625 0.0044 1.0000 0.1033
-8.250 -0.4293 0.09651 0.09293 -0.0079 1.0000 0.1050
-8.000 -0.3871 0.09176 0.08821 -0.0007 1.0000 0.1079
-7.750 -0.3722 0.08852 0.08505 -0.0016 1.0000 0.1114
-7.500 -0.3732 0.08464 0.08132 -0.0078 1.0000 0.1167
-7.250 -0.3809 0.07828 0.07501 -0.0210 0.9431 0.1209
-7.000 -0.3546 0.07568 0.07234 -0.0181 0.8922 0.1244
-6.750 -0.3546 0.07308 0.06962 -0.0181 0.8573 0.1290
-6.500 -0.3718 0.06869 0.06497 -0.0238 0.8344 0.1362
-6.250 -0.3573 0.06620 0.06247 -0.0204 0.8122 0.1392
-6.000 -0.3496 0.06351 0.05965 -0.0205 0.7923 0.1459
-5.750 -0.3465 0.05983 0.05578 -0.0218 0.7761 0.1541
-5.500 -0.3414 0.05740 0.05299 -0.0230 0.7608 0.1682
-5.250 -0.3271 0.03857 0.03217 -0.0261 0.7586 0.0611
-5.000 -0.3078 0.03587 0.02906 -0.0245 0.7437 0.0589
-4.750 -0.2872 0.03329 0.02602 -0.0232 0.7285 0.0584
-4.500 -0.2644 0.03099 0.02326 -0.0220 0.7135 0.0583
-4.250 -0.2402 0.02886 0.02069 -0.0207 0.6989 0.0580
-4.000 -0.2147 0.02698 0.01840 -0.0195 0.6851 0.0580
-3.750 -0.1884 0.02539 0.01641 -0.0181 0.6724 0.0590
-3.500 -0.1619 0.02391 0.01472 -0.0171 0.6590 0.0614
-3.250 -0.1354 0.02298 0.01374 -0.0163 0.6449 0.0677
-3.000 -0.1095 0.02189 0.01266 -0.0154 0.6321 0.0753
-2.750 -0.0848 0.02093 0.01166 -0.0141 0.6214 0.0890
-2.500 -0.0604 0.01980 0.01077 -0.0130 0.6085 0.1237
-2.250 -0.0414 0.01785 0.00993 -0.0114 0.5978 0.3089
-1.750 0.0339 0.01636 0.01037 -0.0091 0.5729 0.9341
-1.500 0.1534 0.01650 0.00975 -0.0247 0.5533 0.9982
-1.250 0.1797 0.01654 0.00957 -0.0248 0.5420 1.0000
-1.000 0.2012 0.01660 0.00930 -0.0238 0.5338 1.0000
-0.750 0.2247 0.01673 0.00931 -0.0233 0.5226 1.0000
-0.500 0.2473 0.01688 0.00920 -0.0224 0.5148 1.0000
-0.250 0.2709 0.01707 0.00927 -0.0219 0.5048 1.0000
0.000 0.2938 0.01727 0.00923 -0.0210 0.4974 1.0000
0.250 0.3177 0.01751 0.00938 -0.0204 0.4878 1.0000
0.500 0.3407 0.01772 0.00934 -0.0194 0.4814 1.0000
0.750 0.3648 0.01808 0.00969 -0.0190 0.4723 1.0000
1.000 0.3882 0.01831 0.00971 -0.0181 0.4661 1.0000
1.250 0.4121 0.01873 0.01011 -0.0176 0.4580 1.0000
1.500 0.4358 0.01901 0.01024 -0.0168 0.4512 1.0000
1.750 0.4594 0.01940 0.01051 -0.0161 0.4452 1.0000
2.000 0.4832 0.01987 0.01099 -0.0156 0.4379 1.0000
2.250 0.5071 0.02018 0.01115 -0.0148 0.4327 1.0000
2.500 0.5306 0.02075 0.01171 -0.0143 0.4263 1.0000
2.750 0.5543 0.02122 0.01215 -0.0137 0.4198 1.0000
3.000 0.5784 0.02154 0.01231 -0.0129 0.4152 1.0000
3.250 0.6015 0.02230 0.01314 -0.0125 0.4094 1.0000
3.500 0.6248 0.02290 0.01376 -0.0120 0.4036 1.0000
3.750 0.6491 0.02325 0.01399 -0.0112 0.3991 1.0000
4.000 0.6718 0.02402 0.01478 -0.0107 0.3939 1.0000
4.250 0.6942 0.02483 0.01569 -0.0103 0.3881 1.0000
4.500 0.7183 0.02533 0.01613 -0.0097 0.3839 1.0000
4.750 0.7435 0.02577 0.01641 -0.0090 0.3805 1.0000
5.000 0.7623 0.02719 0.01812 -0.0089 0.3740 1.0000
5.250 0.7856 0.02785 0.01879 -0.0084 0.3692 1.0000
5.500 0.8108 0.02825 0.01910 -0.0078 0.3657 1.0000
5.750 0.8311 0.02955 0.02052 -0.0076 0.3614 1.0000
6.000 0.8481 0.03120 0.02238 -0.0074 0.3556 1.0000
6.250 0.8725 0.03170 0.02286 -0.0069 0.3516 1.0000
6.500 0.8993 0.03196 0.02301 -0.0063 0.3485 1.0000
6.750 0.9081 0.03475 0.02615 -0.0064 0.3430 1.0000
7.000 0.9209 0.03683 0.02841 -0.0062 0.3379 1.0000
7.250 0.9474 0.03704 0.02858 -0.0056 0.3346 1.0000
7.500 0.9783 0.03686 0.02826 -0.0050 0.3319 1.0000
7.750 0.9219 0.04722 0.03935 -0.0065 0.3227 1.0000
8.000 0.9300 0.04950 0.04169 -0.0063 0.3190 1.0000
8.250 0.9848 0.04637 0.03844 -0.0047 0.3174 1.0000
8.500 1.0332 0.04432 0.03623 -0.0037 0.3156 1.0000
8.750 0.7091 0.09171 0.08407 -0.0243 0.3145 1.0000
9.000 0.7215 0.09521 0.08762 -0.0248 0.3154 1.0000
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Polar data table (+)
Polar graphs
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