MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 110 10.01% (mh110-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.77 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh110-il-1000000.txt Download as CSV file: xf-mh110-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 110 10.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.500 -0.6246 0.01375 0.00856 0.0232 1.0000 0.0050
-5.250 -0.6002 0.01309 0.00784 0.0241 1.0000 0.0049
-5.000 -0.5706 0.01236 0.00707 0.0238 0.9764 0.0048
-4.750 -0.5413 0.01167 0.00602 0.0238 0.8519 0.0048
-4.500 -0.5204 0.01113 0.00519 0.0255 0.7889 0.0048
-4.250 -0.4970 0.01068 0.00451 0.0266 0.7448 0.0048
-4.000 -0.4736 0.01005 0.00364 0.0278 0.7074 0.0051
-3.750 -0.4484 0.00972 0.00311 0.0286 0.6746 0.0056
-3.500 -0.4225 0.00947 0.00272 0.0292 0.6443 0.0075
-3.250 -0.3992 0.00880 0.00225 0.0301 0.6176 0.0640
-3.000 -0.3740 0.00849 0.00203 0.0307 0.5929 0.1068
-2.750 -0.3492 0.00811 0.00183 0.0312 0.5699 0.1658
-2.500 -0.3254 0.00764 0.00164 0.0319 0.5486 0.2556
-2.250 -0.3023 0.00709 0.00146 0.0327 0.5287 0.3670
-2.000 -0.2776 0.00679 0.00134 0.0333 0.5105 0.4397
-1.750 -0.2527 0.00653 0.00124 0.0339 0.4934 0.5059
-1.500 -0.2281 0.00627 0.00115 0.0346 0.4764 0.5739
-1.250 -0.2038 0.00603 0.00107 0.0354 0.4599 0.6412
-1.000 -0.1794 0.00584 0.00102 0.0363 0.4439 0.7004
-0.750 -0.1554 0.00566 0.00098 0.0373 0.4297 0.7598
-0.500 -0.1310 0.00551 0.00097 0.0383 0.4161 0.8110
-0.250 -0.1055 0.00542 0.00096 0.0390 0.4030 0.8554
0.000 -0.0779 0.00540 0.00099 0.0394 0.3901 0.8912
0.250 -0.0471 0.00544 0.00104 0.0390 0.3767 0.9178
0.500 -0.0131 0.00555 0.00110 0.0379 0.3630 0.9357
0.750 0.0218 0.00568 0.00116 0.0366 0.3504 0.9473
1.000 0.0541 0.00581 0.00123 0.0358 0.3389 0.9569
1.500 0.1201 0.00610 0.00140 0.0339 0.3175 0.9693
1.750 0.1588 0.00624 0.00148 0.0316 0.3071 0.9716
2.000 0.1958 0.00639 0.00157 0.0297 0.2967 0.9746
2.250 0.2299 0.00653 0.00165 0.0285 0.2873 0.9784
2.500 0.2620 0.00666 0.00175 0.0276 0.2796 0.9823
2.750 0.2997 0.00679 0.00182 0.0255 0.2712 0.9837
3.000 0.3366 0.00687 0.00189 0.0236 0.2645 0.9855
3.250 0.3723 0.00700 0.00197 0.0219 0.2573 0.9876
3.500 0.4070 0.00708 0.00204 0.0205 0.2518 0.9900
3.750 0.4409 0.00722 0.00215 0.0192 0.2454 0.9925
4.000 0.4767 0.00731 0.00224 0.0174 0.2407 0.9945
4.250 0.5145 0.00738 0.00230 0.0153 0.2358 0.9963
4.500 0.5502 0.00751 0.00240 0.0135 0.2304 0.9981
4.750 0.5852 0.00755 0.00249 0.0119 0.2270 0.9996
5.000 0.6130 0.00763 0.00258 0.0119 0.2232 1.0000
5.250 0.6378 0.00774 0.00269 0.0125 0.2192 1.0000
5.500 0.6627 0.00784 0.00280 0.0130 0.2144 1.0000
5.750 0.6879 0.00791 0.00290 0.0136 0.2091 1.0000
6.000 0.7127 0.00805 0.00302 0.0141 0.2017 1.0000
6.250 0.7377 0.00813 0.00313 0.0147 0.1957 1.0000
6.500 0.7625 0.00829 0.00329 0.0152 0.1904 1.0000
6.750 0.7876 0.00839 0.00341 0.0158 0.1827 1.0000
7.000 0.8122 0.00857 0.00356 0.0163 0.1694 1.0000
7.250 0.8364 0.00884 0.00377 0.0169 0.1512 1.0000
7.500 0.8591 0.00937 0.00413 0.0175 0.1152 1.0000
7.750 0.8795 0.01032 0.00481 0.0183 0.0689 1.0000
8.000 0.9007 0.01107 0.00543 0.0191 0.0424 1.0000
8.250 0.9224 0.01171 0.00600 0.0199 0.0264 1.0000
8.500 0.9441 0.01233 0.00658 0.0208 0.0159 1.0000
8.750 0.9642 0.01318 0.00738 0.0218 0.0059 1.0000
9.000 0.9842 0.01405 0.00833 0.0229 0.0033 1.0000
9.250 1.0051 0.01469 0.00905 0.0239 0.0029 1.0000
9.500 1.0247 0.01548 0.00996 0.0250 0.0026 1.0000
9.750 1.0419 0.01655 0.01118 0.0263 0.0024 1.0000
10.000 1.0588 0.01755 0.01232 0.0276 0.0024 1.0000
10.250 1.0712 0.01900 0.01394 0.0293 0.0023 1.0000
10.500 1.0813 0.02053 0.01563 0.0312 0.0023 1.0000
10.750 1.0860 0.02241 0.01768 0.0334 0.0022 1.0000
11.000 1.0910 0.02405 0.01945 0.0355 0.0022 1.0000
11.250 1.0943 0.02567 0.02119 0.0375 0.0022 1.0000
11.500 1.0935 0.02721 0.02283 0.0399 0.0022 1.0000
11.750 1.0892 0.02904 0.02476 0.0413 0.0023 1.0000
12.000 1.0753 0.03351 0.02941 0.0390 0.0022 1.0000
12.250 1.0757 0.03692 0.03291 0.0368 0.0023 1.0000
12.500 1.0632 0.04197 0.03811 0.0342 0.0023 1.0000
12.750 1.0571 0.04616 0.04240 0.0321 0.0023 1.0000
13.000 1.0594 0.04939 0.04570 0.0302 0.0023 1.0000
13.250 1.0450 0.05449 0.05092 0.0281 0.0023 1.0000
13.500 1.0444 0.05811 0.05460 0.0261 0.0023 1.0000
13.750 1.0266 0.06364 0.06025 0.0241 0.0023 1.0000
14.000 1.0228 0.06770 0.06440 0.0220 0.0023 1.0000
14.250 1.0134 0.07243 0.06923 0.0199 0.0023 1.0000
14.500 1.0066 0.07708 0.07396 0.0177 0.0023 1.0000
14.750 0.9974 0.08217 0.07914 0.0153 0.0023 1.0000
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Polar data table (+)
Polar graphs
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