GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 500,000 Max Cl/Cd: 97.98 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe182-il-500000.txt Download as CSV file: xf-goe182-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 182 (MVA H.27) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3162 0.09266 0.09051 -0.0221 1.0000 0.0286
-8.000 -0.3177 0.08905 0.08695 -0.0250 1.0000 0.0288
-7.750 -0.3195 0.08495 0.08289 -0.0264 1.0000 0.0290
-7.500 -0.3130 0.08289 0.08086 -0.0244 1.0000 0.0294
-7.250 -0.3069 0.08119 0.07918 -0.0229 1.0000 0.0298
-7.000 -0.3006 0.07914 0.07717 -0.0230 0.9993 0.0303
-6.750 -0.2654 0.07469 0.07269 -0.0315 0.9933 0.0316
-6.500 -0.2097 0.06427 0.06216 -0.0567 0.9829 0.0346
-6.250 -0.1901 0.05989 0.05777 -0.0595 0.9711 0.0354
-6.000 -0.1657 0.05797 0.05583 -0.0611 0.9556 0.0362
-5.750 -0.1429 0.05528 0.05309 -0.0640 0.9339 0.0375
-5.500 -0.0914 0.04200 0.03944 -0.0849 0.9092 0.0422
-5.250 -0.0740 0.04077 0.03811 -0.0840 0.8689 0.0427
-5.000 -0.0549 0.03984 0.03697 -0.0832 0.8216 0.0435
-4.750 -0.0315 0.03822 0.03512 -0.0841 0.7861 0.0450
-4.500 0.0108 0.02774 0.02378 -0.0941 0.7676 0.0511
-4.250 0.0353 0.02651 0.02246 -0.0942 0.7473 0.0519
-4.000 0.0610 0.02534 0.02113 -0.0945 0.7302 0.0531
-3.750 0.0881 0.02399 0.01959 -0.0950 0.7148 0.0555
-3.500 0.1222 0.01495 0.00888 -0.0968 0.7046 0.0413
-3.250 0.1496 0.01361 0.00724 -0.0968 0.6901 0.0423
-3.000 0.1772 0.01274 0.00621 -0.0966 0.6751 0.0430
-2.750 0.2049 0.01221 0.00557 -0.0964 0.6590 0.0438
-2.500 0.2326 0.01181 0.00505 -0.0962 0.6415 0.0447
-2.250 0.2603 0.01147 0.00458 -0.0959 0.6220 0.0457
-2.000 0.2880 0.01117 0.00417 -0.0956 0.6004 0.0469
-1.750 0.3156 0.01101 0.00386 -0.0953 0.5780 0.0486
-1.500 0.3432 0.01091 0.00362 -0.0950 0.5570 0.0498
-1.250 0.3706 0.01045 0.00307 -0.0948 0.5378 0.0521
-1.000 0.3983 0.01035 0.00288 -0.0946 0.5193 0.0546
-0.750 0.4260 0.01029 0.00274 -0.0943 0.5014 0.0577
-0.500 0.4536 0.01018 0.00253 -0.0941 0.4833 0.0620
-0.250 0.4813 0.01012 0.00241 -0.0939 0.4645 0.0693
0.000 0.5090 0.01001 0.00224 -0.0937 0.4438 0.0800
0.250 0.5365 0.00998 0.00214 -0.0936 0.4211 0.0957
0.500 0.5637 0.00995 0.00219 -0.0934 0.3982 0.1520
0.750 0.5909 0.01001 0.00225 -0.0932 0.3761 0.1944
1.000 0.6179 0.01007 0.00234 -0.0931 0.3574 0.2457
1.250 0.6449 0.01006 0.00246 -0.0929 0.3421 0.3255
1.500 0.6713 0.00986 0.00265 -0.0928 0.3298 0.5068
1.750 0.6989 0.00899 0.00275 -0.0926 0.3197 1.0000
2.000 0.7260 0.00922 0.00285 -0.0923 0.3108 1.0000
2.250 0.7535 0.00939 0.00296 -0.0921 0.3038 1.0000
2.500 0.7806 0.00960 0.00308 -0.0919 0.2975 1.0000
2.750 0.8077 0.00983 0.00323 -0.0916 0.2922 1.0000
3.000 0.8351 0.00999 0.00336 -0.0914 0.2878 1.0000
3.250 0.8622 0.01020 0.00351 -0.0912 0.2837 1.0000
3.500 0.8889 0.01046 0.00370 -0.0909 0.2797 1.0000
3.750 0.9159 0.01066 0.00387 -0.0906 0.2764 1.0000
4.000 0.9432 0.01081 0.00402 -0.0904 0.2732 1.0000
4.250 0.9702 0.01100 0.00419 -0.0902 0.2698 1.0000
4.500 0.9968 0.01123 0.00438 -0.0899 0.2667 1.0000
4.750 1.0230 0.01154 0.00464 -0.0896 0.2640 1.0000
5.000 1.0496 0.01178 0.00489 -0.0893 0.2623 1.0000
5.250 1.0765 0.01197 0.00511 -0.0891 0.2609 1.0000
5.500 1.1031 0.01219 0.00535 -0.0888 0.2594 1.0000
5.750 1.1298 0.01239 0.00557 -0.0885 0.2575 1.0000
6.000 1.1563 0.01259 0.00579 -0.0883 0.2551 1.0000
6.250 1.1825 0.01282 0.00603 -0.0880 0.2530 1.0000
6.500 1.2083 0.01311 0.00630 -0.0877 0.2505 1.0000
6.750 1.2337 0.01349 0.00668 -0.0873 0.2478 1.0000
7.000 1.2602 0.01364 0.00690 -0.0870 0.2462 1.0000
7.250 1.2867 0.01376 0.00709 -0.0868 0.2432 1.0000
7.500 1.3129 0.01389 0.00725 -0.0865 0.2390 1.0000
7.750 1.3377 0.01420 0.00753 -0.0861 0.2341 1.0000
8.000 1.3637 0.01435 0.00776 -0.0858 0.2309 1.0000
8.250 1.3899 0.01447 0.00796 -0.0856 0.2270 1.0000
8.500 1.4152 0.01467 0.00817 -0.0853 0.2215 1.0000
8.750 1.4405 0.01488 0.00843 -0.0849 0.2161 1.0000
9.000 1.4661 0.01502 0.00863 -0.0846 0.2085 1.0000
9.250 1.4913 0.01522 0.00885 -0.0843 0.1972 1.0000
9.500 1.5129 0.01580 0.00920 -0.0836 0.1476 1.0000
9.750 1.5149 0.01857 0.01136 -0.0807 0.0635 1.0000
10.000 1.5281 0.01996 0.01269 -0.0789 0.0454 1.0000
10.250 1.5430 0.02109 0.01385 -0.0773 0.0368 1.0000
10.500 1.5563 0.02226 0.01505 -0.0755 0.0310 1.0000
10.750 1.5715 0.02316 0.01600 -0.0740 0.0276 1.0000
11.000 1.5811 0.02443 0.01733 -0.0718 0.0250 1.0000
11.250 1.5913 0.02538 0.01837 -0.0696 0.0235 1.0000
11.500 1.5982 0.02654 0.01960 -0.0672 0.0223 1.0000
11.750 1.5993 0.02816 0.02130 -0.0645 0.0212 1.0000
12.000 1.5946 0.03040 0.02368 -0.0619 0.0203 1.0000
12.250 1.5981 0.03222 0.02561 -0.0604 0.0197 1.0000
12.500 1.5989 0.03451 0.02803 -0.0594 0.0191 1.0000
12.750 1.5977 0.03732 0.03096 -0.0590 0.0185 1.0000
13.000 1.5944 0.04070 0.03446 -0.0592 0.0180 1.0000
13.250 1.5881 0.04467 0.03856 -0.0598 0.0176 1.0000
13.500 1.5775 0.04941 0.04343 -0.0609 0.0172 1.0000
13.750 1.5628 0.05493 0.04908 -0.0623 0.0170 1.0000
14.000 1.5455 0.06094 0.05524 -0.0640 0.0169 1.0000
14.250 1.5267 0.06719 0.06162 -0.0657 0.0167 1.0000
14.500 1.5070 0.07358 0.06813 -0.0674 0.0166 1.0000
14.750 1.4877 0.07988 0.07455 -0.0690 0.0165 1.0000
15.000 1.4697 0.08607 0.08085 -0.0706 0.0163 1.0000
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Polar data table (+)
Polar graphs
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