MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh18-il-1000000-n5.txt Download as CSV file: xf-mh18-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 18 11.16%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.7329 0.03286 0.02984 -0.0329 0.7463 0.0014
-9.000 -0.7388 0.02724 0.02363 -0.0302 0.7412 0.0014
-8.750 -0.7283 0.02438 0.02038 -0.0284 0.7367 0.0015
-8.500 -0.7135 0.02214 0.01781 -0.0270 0.7321 0.0016
-8.250 -0.6952 0.02048 0.01588 -0.0258 0.7274 0.0016
-8.000 -0.6732 0.01948 0.01469 -0.0251 0.7230 0.0017
-7.750 -0.6511 0.01844 0.01347 -0.0243 0.7185 0.0017
-7.500 -0.6275 0.01767 0.01255 -0.0238 0.7139 0.0018
-7.250 -0.6033 0.01699 0.01171 -0.0233 0.7100 0.0018
-7.000 -0.5828 0.01546 0.00991 -0.0221 0.7064 0.0020
-6.750 -0.5599 0.01444 0.00871 -0.0214 0.7025 0.0021
-6.500 -0.5353 0.01378 0.00793 -0.0209 0.6988 0.0022
-6.250 -0.5100 0.01325 0.00731 -0.0205 0.6954 0.0023
-6.000 -0.4845 0.01273 0.00670 -0.0201 0.6917 0.0024
-5.750 -0.4585 0.01229 0.00618 -0.0198 0.6880 0.0026
-5.500 -0.4326 0.01185 0.00565 -0.0194 0.6847 0.0027
-5.250 -0.4065 0.01143 0.00514 -0.0191 0.6817 0.0028
-5.000 -0.3802 0.01104 0.00468 -0.0188 0.6785 0.0029
-4.750 -0.3537 0.01067 0.00425 -0.0185 0.6751 0.0030
-4.500 -0.3268 0.01042 0.00394 -0.0184 0.6719 0.0033
-4.000 -0.2728 0.00989 0.00331 -0.0180 0.6663 0.0038
-3.750 -0.2461 0.00953 0.00288 -0.0177 0.6632 0.0043
-3.500 -0.2189 0.00929 0.00258 -0.0176 0.6601 0.0051
-3.250 -0.1918 0.00905 0.00233 -0.0174 0.6571 0.0090
-3.000 -0.1649 0.00880 0.00212 -0.0172 0.6542 0.0206
-2.750 -0.1377 0.00859 0.00195 -0.0172 0.6508 0.0324
-2.500 -0.1110 0.00832 0.00179 -0.0170 0.6468 0.0605
-2.250 -0.0842 0.00809 0.00165 -0.0169 0.6430 0.0914
-2.000 -0.0570 0.00791 0.00153 -0.0168 0.6395 0.1170
-1.750 -0.0296 0.00775 0.00144 -0.0168 0.6357 0.1406
-1.500 -0.0027 0.00754 0.00134 -0.0167 0.6318 0.1797
-1.000 0.0514 0.00718 0.00119 -0.0166 0.6246 0.2599
-0.750 0.0785 0.00701 0.00113 -0.0165 0.6208 0.3016
-0.500 0.1050 0.00680 0.00108 -0.0164 0.6169 0.3588
-0.250 0.1305 0.00651 0.00103 -0.0160 0.6133 0.4433
0.000 0.1557 0.00621 0.00100 -0.0156 0.6094 0.5296
0.250 0.1799 0.00590 0.00097 -0.0150 0.6051 0.6233
0.500 0.2028 0.00560 0.00095 -0.0140 0.6008 0.7175
0.750 0.2245 0.00526 0.00094 -0.0126 0.5966 0.8133
1.000 0.2690 0.00503 0.00104 -0.0161 0.5909 0.9200
1.250 0.3304 0.00515 0.00115 -0.0236 0.5849 0.9440
1.750 0.3917 0.00535 0.00130 -0.0248 0.5720 0.9657
2.000 0.4251 0.00545 0.00138 -0.0260 0.5641 0.9730
2.250 0.4567 0.00561 0.00151 -0.0268 0.5555 0.9816
2.500 0.5002 0.00571 0.00158 -0.0304 0.5435 0.9845
2.750 0.5371 0.00581 0.00162 -0.0325 0.5286 0.9868
3.000 0.5717 0.00594 0.00169 -0.0342 0.5097 0.9892
3.250 0.6045 0.00611 0.00177 -0.0355 0.4885 0.9914
3.750 0.6676 0.00654 0.00202 -0.0377 0.4392 0.9944
4.000 0.7002 0.00674 0.00213 -0.0390 0.4156 0.9954
4.250 0.7321 0.00695 0.00227 -0.0402 0.3933 0.9965
4.500 0.7632 0.00718 0.00241 -0.0413 0.3698 0.9975
4.750 0.7939 0.00740 0.00256 -0.0423 0.3493 0.9985
5.000 0.8240 0.00768 0.00274 -0.0432 0.3240 0.9993
5.250 0.8537 0.00794 0.00294 -0.0440 0.3008 1.0000
5.500 0.8777 0.00829 0.00317 -0.0436 0.2726 1.0000
5.750 0.9002 0.00881 0.00349 -0.0431 0.2309 1.0000
6.000 0.9212 0.00946 0.00389 -0.0424 0.1817 1.0000
6.250 0.9408 0.01018 0.00436 -0.0415 0.1335 1.0000
6.500 0.9597 0.01090 0.00485 -0.0404 0.0916 1.0000
6.750 0.9771 0.01168 0.00541 -0.0391 0.0524 1.0000
7.000 0.9965 0.01222 0.00587 -0.0380 0.0348 1.0000
7.250 1.0144 0.01284 0.00639 -0.0366 0.0177 1.0000
7.500 1.0332 0.01333 0.00684 -0.0353 0.0102 1.0000
7.750 1.0522 0.01376 0.00727 -0.0341 0.0071 1.0000
8.000 1.0698 0.01425 0.00775 -0.0326 0.0035 1.0000
8.250 1.0867 0.01475 0.00827 -0.0310 0.0018 1.0000
8.500 1.1039 0.01519 0.00873 -0.0295 0.0015 1.0000
8.750 1.1187 0.01574 0.00932 -0.0276 0.0010 1.0000
9.000 1.1329 0.01628 0.00991 -0.0255 0.0009 1.0000
9.250 1.1444 0.01691 0.01063 -0.0231 0.0007 1.0000
9.500 1.1499 0.01744 0.01121 -0.0196 0.0007 1.0000
9.750 1.1547 0.01805 0.01188 -0.0162 0.0007 1.0000
10.000 1.1616 0.01878 0.01267 -0.0134 0.0006 1.0000
10.250 1.1709 0.01951 0.01346 -0.0112 0.0006 1.0000
10.500 1.1772 0.02052 0.01455 -0.0088 0.0006 1.0000
10.750 1.1861 0.02145 0.01555 -0.0069 0.0006 1.0000
11.000 1.1944 0.02247 0.01665 -0.0050 0.0006 1.0000
11.250 1.2030 0.02354 0.01778 -0.0033 0.0006 1.0000
11.500 1.2096 0.02481 0.01914 -0.0016 0.0005 1.0000
11.750 1.2153 0.02621 0.02063 0.0000 0.0005 1.0000
12.000 1.2223 0.02755 0.02207 0.0014 0.0005 1.0000
12.250 1.2262 0.02921 0.02382 0.0029 0.0005 1.0000
12.500 1.2300 0.03094 0.02565 0.0043 0.0005 1.0000
12.750 1.2347 0.03263 0.02742 0.0054 0.0005 1.0000
13.000 1.2361 0.03468 0.02958 0.0065 0.0005 1.0000
13.250 1.2355 0.03697 0.03199 0.0076 0.0005 1.0000
13.500 1.2370 0.03913 0.03425 0.0085 0.0005 1.0000
13.750 1.2383 0.04137 0.03659 0.0092 0.0005 1.0000
14.000 1.2346 0.04423 0.03958 0.0098 0.0005 1.0000
14.250 1.2325 0.04705 0.04252 0.0102 0.0005 1.0000
14.500 1.2301 0.05000 0.04558 0.0104 0.0005 1.0000
14.750 1.2222 0.05375 0.04948 0.0104 0.0005 1.0000
15.000 1.2179 0.05720 0.05305 0.0102 0.0005 1.0000
15.250 1.2147 0.06064 0.05661 0.0097 0.0005 1.0000
15.500 1.2038 0.06529 0.06141 0.0089 0.0005 1.0000
15.750 1.1982 0.06936 0.06560 0.0079 0.0005 1.0000
16.000 1.1877 0.07430 0.07067 0.0065 0.0005 1.0000
16.250 1.1868 0.07797 0.07443 0.0053 0.0005 1.0000
16.500 1.1709 0.08410 0.08072 0.0032 0.0005 1.0000
16.750 1.1597 0.08966 0.08641 0.0012 0.0005 1.0000
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Polar data table (+)
Polar graphs
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