MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 500,000 Max Cl/Cd: 108.57 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh18-il-500000.txt Download as CSV file: xf-mh18-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4200 0.08338 0.08102 -0.0259 0.8436 0.0140
-8.500 -0.4251 0.07894 0.07656 -0.0282 0.8356 0.0145
-8.250 -0.4319 0.07451 0.07213 -0.0310 0.8270 0.0144
-8.000 -0.4478 0.06957 0.06718 -0.0344 0.8185 0.0146
-7.750 -0.4575 0.06484 0.06239 -0.0365 0.8107 0.0145
-7.500 -0.4620 0.05961 0.05704 -0.0384 0.8046 0.0147
-7.250 -0.4629 0.05425 0.05154 -0.0396 0.7982 0.0150
-7.000 -0.4608 0.04909 0.04614 -0.0398 0.7934 0.0154
-6.750 -0.4539 0.04389 0.04068 -0.0393 0.7882 0.0165
-6.500 -0.4351 0.04187 0.03826 -0.0381 0.7833 0.0177
-6.250 -0.4581 0.02777 0.02325 -0.0330 0.7796 0.0094
-6.000 -0.4468 0.02284 0.01765 -0.0301 0.7750 0.0085
-5.750 -0.4264 0.02053 0.01495 -0.0287 0.7705 0.0088
-5.500 -0.4042 0.01869 0.01274 -0.0275 0.7667 0.0089
-5.250 -0.3802 0.01722 0.01103 -0.0266 0.7628 0.0092
-5.000 -0.3544 0.01648 0.01015 -0.0262 0.7586 0.0101
-4.750 -0.3283 0.01588 0.00940 -0.0257 0.7548 0.0107
-4.250 -0.2781 0.01390 0.00713 -0.0243 0.7475 0.0110
-4.000 -0.2556 0.01258 0.00565 -0.0231 0.7438 0.0116
-3.750 -0.2316 0.01172 0.00466 -0.0221 0.7404 0.0135
-3.500 -0.2067 0.01105 0.00390 -0.0213 0.7373 0.0253
-3.250 -0.1811 0.01053 0.00355 -0.0209 0.7335 0.0633
-3.000 -0.1555 0.01011 0.00335 -0.0206 0.7299 0.1093
-2.750 -0.1299 0.00975 0.00315 -0.0203 0.7266 0.1608
-2.500 -0.1042 0.00946 0.00299 -0.0200 0.7235 0.2137
-2.250 -0.0783 0.00911 0.00285 -0.0198 0.7196 0.2743
-2.000 -0.0543 0.00862 0.00269 -0.0193 0.7157 0.3740
-1.750 -0.0336 0.00798 0.00255 -0.0180 0.7122 0.5250
-1.500 -0.0153 0.00736 0.00248 -0.0160 0.7087 0.6791
-1.250 0.0114 0.00672 0.00249 -0.0153 0.7048 0.8577
-1.000 0.0977 0.00688 0.00266 -0.0275 0.7011 0.9348
-0.750 0.1311 0.00709 0.00276 -0.0283 0.6977 0.9564
-0.500 0.1698 0.00728 0.00288 -0.0305 0.6938 0.9693
-0.250 0.2155 0.00739 0.00292 -0.0342 0.6897 0.9766
0.000 0.2572 0.00749 0.00294 -0.0372 0.6857 0.9839
0.250 0.3024 0.00753 0.00289 -0.0409 0.6820 0.9895
0.500 0.3453 0.00752 0.00286 -0.0443 0.6774 0.9947
0.750 0.3911 0.00741 0.00270 -0.0483 0.6730 0.9996
1.250 0.4437 0.00739 0.00263 -0.0480 0.6641 1.0000
1.500 0.4691 0.00738 0.00259 -0.0476 0.6592 1.0000
1.750 0.4945 0.00741 0.00256 -0.0472 0.6548 1.0000
2.000 0.5204 0.00739 0.00258 -0.0470 0.6492 1.0000
2.250 0.5461 0.00740 0.00257 -0.0466 0.6440 1.0000
2.500 0.5720 0.00742 0.00258 -0.0463 0.6385 1.0000
2.750 0.5979 0.00742 0.00260 -0.0461 0.6322 1.0000
3.000 0.6238 0.00745 0.00260 -0.0458 0.6264 1.0000
3.250 0.6499 0.00745 0.00266 -0.0455 0.6190 1.0000
3.500 0.6759 0.00748 0.00268 -0.0452 0.6119 1.0000
3.750 0.7020 0.00749 0.00272 -0.0450 0.6034 1.0000
4.000 0.7281 0.00752 0.00277 -0.0447 0.5938 1.0000
4.250 0.7541 0.00756 0.00283 -0.0444 0.5836 1.0000
4.500 0.7800 0.00761 0.00289 -0.0442 0.5715 1.0000
4.750 0.8059 0.00767 0.00297 -0.0439 0.5573 1.0000
5.000 0.8316 0.00776 0.00307 -0.0436 0.5399 1.0000
5.250 0.8569 0.00790 0.00320 -0.0433 0.5188 1.0000
5.500 0.8816 0.00812 0.00336 -0.0429 0.4923 1.0000
5.750 0.9055 0.00843 0.00358 -0.0424 0.4631 1.0000
6.000 0.9289 0.00881 0.00385 -0.0419 0.4318 1.0000
6.250 0.9508 0.00932 0.00420 -0.0412 0.3930 1.0000
6.500 0.9725 0.00981 0.00457 -0.0405 0.3574 1.0000
7.000 1.0140 0.01086 0.00542 -0.0387 0.2905 1.0000
7.250 1.0328 0.01149 0.00590 -0.0376 0.2533 1.0000
7.500 1.0470 0.01244 0.00654 -0.0359 0.1968 1.0000
7.750 1.0582 0.01352 0.00729 -0.0337 0.1404 1.0000
8.000 1.0648 0.01482 0.00819 -0.0309 0.0835 1.0000
8.250 1.0723 0.01591 0.00905 -0.0282 0.0479 1.0000
8.500 1.0809 0.01683 0.00985 -0.0254 0.0288 1.0000
8.750 1.0856 0.01789 0.01083 -0.0221 0.0140 1.0000
9.000 1.0821 0.01893 0.01188 -0.0173 0.0081 1.0000
9.250 1.0795 0.02012 0.01317 -0.0130 0.0062 1.0000
9.500 1.0857 0.02107 0.01418 -0.0104 0.0049 1.0000
9.750 1.0916 0.02214 0.01535 -0.0079 0.0044 1.0000
10.000 1.0918 0.02372 0.01704 -0.0051 0.0039 1.0000
10.250 1.0955 0.02514 0.01856 -0.0029 0.0038 1.0000
10.500 1.0850 0.02780 0.02138 0.0003 0.0035 1.0000
10.750 1.0878 0.02952 0.02321 0.0022 0.0034 1.0000
11.000 1.0915 0.03125 0.02504 0.0038 0.0034 1.0000
11.250 1.0938 0.03316 0.02706 0.0055 0.0034 1.0000
11.500 1.0964 0.03514 0.02915 0.0070 0.0033 1.0000
11.750 1.0984 0.03725 0.03139 0.0086 0.0033 1.0000
12.000 1.1014 0.03933 0.03359 0.0100 0.0033 1.0000
12.250 1.1029 0.04168 0.03608 0.0114 0.0033 1.0000
12.500 1.1043 0.04414 0.03870 0.0128 0.0033 1.0000
12.750 1.1047 0.04675 0.04147 0.0139 0.0033 1.0000
13.000 1.1017 0.04996 0.04487 0.0152 0.0034 1.0000
13.250 1.0961 0.05353 0.04865 0.0162 0.0034 1.0000
13.500 1.0846 0.05829 0.05365 0.0173 0.0035 1.0000
13.750 1.0810 0.06141 0.05690 0.0173 0.0036 1.0000
14.000 1.0756 0.06494 0.06057 0.0170 0.0036 1.0000
14.250 1.0703 0.06858 0.06438 0.0163 0.0036 1.0000
14.500 1.0646 0.07244 0.06838 0.0154 0.0037 1.0000
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Polar data table (+)
Polar graphs
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