MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 110 10.01% (mh110-il) Reynolds number: 500,000 Max Cl/Cd: 78.45 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh110-il-500000.txt Download as CSV file: xf-mh110-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6591 0.08393 0.08195 0.0133 1.0000 0.0169
-9.000 -0.6737 0.07537 0.07343 0.0056 1.0000 0.0166
-8.750 -0.6997 0.06726 0.06522 -0.0005 1.0000 0.0162
-8.500 -0.7205 0.06247 0.06034 -0.0001 1.0000 0.0161
-8.250 -0.7313 0.05776 0.05547 0.0003 1.0000 0.0163
-8.000 -0.7363 0.05328 0.05081 0.0011 1.0000 0.0167
-7.750 -0.7369 0.04897 0.04627 0.0024 1.0000 0.0173
-7.500 -0.7326 0.04500 0.04203 0.0040 1.0000 0.0182
-7.250 -0.7121 0.04448 0.04123 0.0056 1.0000 0.0201
-7.000 -0.7008 0.04245 0.03890 0.0074 1.0000 0.0203
-6.000 -0.6590 0.02158 0.01629 0.0171 1.0000 0.0110
-5.750 -0.6380 0.01774 0.01189 0.0196 1.0000 0.0087
-5.500 -0.6137 0.01663 0.01065 0.0206 1.0000 0.0084
-5.250 -0.5899 0.01557 0.00949 0.0216 1.0000 0.0082
-5.000 -0.5667 0.01451 0.00835 0.0228 1.0000 0.0082
-4.750 -0.5448 0.01337 0.00713 0.0241 1.0000 0.0082
-4.500 -0.5231 0.01237 0.00605 0.0255 1.0000 0.0085
-4.250 -0.5006 0.01155 0.00515 0.0267 1.0000 0.0090
-4.000 -0.4677 0.01089 0.00444 0.0258 0.9663 0.0110
-3.750 -0.4327 0.01000 0.00348 0.0248 0.8642 0.0486
-3.500 -0.4133 0.00953 0.00313 0.0266 0.8027 0.1164
-3.250 -0.3926 0.00900 0.00284 0.0280 0.7565 0.2068
-3.000 -0.3720 0.00837 0.00259 0.0292 0.7186 0.3238
-2.750 -0.3498 0.00794 0.00238 0.0303 0.6851 0.4148
-2.500 -0.3269 0.00761 0.00221 0.0314 0.6548 0.4925
-2.250 -0.3046 0.00728 0.00204 0.0326 0.6277 0.5708
-2.000 -0.2825 0.00698 0.00192 0.0340 0.6029 0.6502
-1.750 -0.2602 0.00672 0.00184 0.0354 0.5795 0.7228
-1.500 -0.2365 0.00654 0.00179 0.0366 0.5575 0.7850
-1.000 -0.1805 0.00646 0.00178 0.0375 0.5162 0.8810
-0.750 -0.1457 0.00658 0.00183 0.0364 0.4961 0.9104
-0.500 -0.1096 0.00674 0.00189 0.0350 0.4763 0.9290
-0.250 -0.0742 0.00692 0.00195 0.0337 0.4570 0.9423
0.000 -0.0361 0.00713 0.00203 0.0318 0.4391 0.9507
0.250 0.0011 0.00733 0.00211 0.0300 0.4225 0.9578
0.500 0.0404 0.00752 0.00219 0.0278 0.4061 0.9635
0.750 0.0766 0.00770 0.00227 0.0262 0.3908 0.9701
1.000 0.1180 0.00786 0.00233 0.0234 0.3750 0.9741
1.250 0.1545 0.00803 0.00241 0.0216 0.3613 0.9801
1.500 0.1941 0.00816 0.00245 0.0192 0.3483 0.9839
1.750 0.2343 0.00826 0.00247 0.0165 0.3362 0.9875
2.000 0.2721 0.00837 0.00251 0.0144 0.3252 0.9916
2.250 0.3098 0.00846 0.00252 0.0122 0.3145 0.9949
2.500 0.3486 0.00848 0.00251 0.0098 0.3044 0.9980
2.750 0.3828 0.00854 0.00254 0.0084 0.2963 1.0000
3.000 0.4068 0.00861 0.00258 0.0090 0.2893 1.0000
3.250 0.4309 0.00872 0.00265 0.0097 0.2833 1.0000
3.500 0.4553 0.00878 0.00272 0.0103 0.2774 1.0000
3.750 0.4796 0.00894 0.00284 0.0110 0.2717 1.0000
4.000 0.5043 0.00900 0.00294 0.0116 0.2665 1.0000
4.250 0.5289 0.00912 0.00305 0.0122 0.2615 1.0000
4.500 0.5533 0.00931 0.00321 0.0128 0.2570 1.0000
4.750 0.5782 0.00940 0.00337 0.0134 0.2531 1.0000
5.000 0.6028 0.00954 0.00353 0.0140 0.2488 1.0000
5.250 0.6271 0.00978 0.00374 0.0146 0.2445 1.0000
5.500 0.6519 0.00991 0.00394 0.0152 0.2410 1.0000
5.750 0.6767 0.01005 0.00413 0.0158 0.2368 1.0000
6.000 0.7011 0.01026 0.00434 0.0164 0.2315 1.0000
6.250 0.7260 0.01036 0.00452 0.0170 0.2257 1.0000
6.500 0.7506 0.01049 0.00465 0.0176 0.2184 1.0000
6.750 0.7755 0.01057 0.00481 0.0181 0.2108 1.0000
7.000 0.8000 0.01076 0.00502 0.0187 0.2047 1.0000
7.250 0.8249 0.01090 0.00525 0.0193 0.1984 1.0000
7.500 0.8493 0.01108 0.00546 0.0199 0.1887 1.0000
7.750 0.8740 0.01124 0.00565 0.0204 0.1754 1.0000
8.000 0.8983 0.01145 0.00587 0.0209 0.1549 1.0000
8.250 0.9185 0.01235 0.00644 0.0217 0.0987 1.0000
8.500 0.9347 0.01387 0.00762 0.0227 0.0452 1.0000
8.750 0.9536 0.01491 0.00858 0.0237 0.0248 1.0000
9.000 0.9703 0.01627 0.00993 0.0250 0.0115 1.0000
9.250 0.9845 0.01790 0.01171 0.0266 0.0071 1.0000
9.500 1.0028 0.01881 0.01279 0.0278 0.0062 1.0000
9.750 1.0189 0.01992 0.01402 0.0291 0.0055 1.0000
10.000 1.0334 0.02110 0.01534 0.0305 0.0053 1.0000
10.250 1.0452 0.02248 0.01684 0.0320 0.0050 1.0000
10.500 1.0537 0.02403 0.01852 0.0337 0.0048 1.0000
10.750 1.0560 0.02596 0.02060 0.0358 0.0046 1.0000
11.000 1.0558 0.02789 0.02266 0.0378 0.0045 1.0000
11.250 1.0482 0.02982 0.02471 0.0403 0.0045 1.0000
11.500 1.0422 0.03259 0.02762 0.0399 0.0045 1.0000
11.750 1.0394 0.03595 0.03111 0.0383 0.0046 1.0000
12.000 1.0289 0.04048 0.03577 0.0361 0.0045 1.0000
12.250 1.0263 0.04407 0.03947 0.0345 0.0045 1.0000
12.500 1.0153 0.04859 0.04411 0.0328 0.0044 1.0000
12.750 1.0101 0.05246 0.04808 0.0313 0.0044 1.0000
13.000 1.0089 0.05596 0.05168 0.0297 0.0045 1.0000
13.250 0.9974 0.06058 0.05642 0.0281 0.0045 1.0000
13.500 0.9953 0.06429 0.06023 0.0263 0.0046 1.0000
13.750 0.9813 0.06942 0.06548 0.0246 0.0045 1.0000
14.000 0.9769 0.07356 0.06972 0.0226 0.0045 1.0000
14.250 0.9674 0.07852 0.07480 0.0204 0.0045 1.0000
14.500 0.9588 0.08367 0.08008 0.0180 0.0046 1.0000
14.750 0.9489 0.08921 0.08576 0.0153 0.0047 1.0000
15.000 0.9360 0.09549 0.09218 0.0123 0.0047 1.0000
15.250 0.9228 0.10212 0.09897 0.0090 0.0049 1.0000
15.500 0.9080 0.10925 0.10624 0.0055 0.0050 1.0000
15.750 0.8895 0.11747 0.11461 0.0014 0.0052 1.0000
16.000 0.8731 0.12556 0.12283 -0.0028 0.0052 1.0000
16.250 0.8525 0.13515 0.13256 -0.0077 0.0054 1.0000
16.500 0.8281 0.14629 0.14382 -0.0133 0.0056 1.0000
16.750 0.8041 0.15835 0.15598 -0.0191 0.0058 1.0000
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Polar data table (+)
Polar graphs
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