GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 50,000 Max Cl/Cd: 36.45 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe182-il-50000-n5.txt Download as CSV file: xf-goe182-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2865 0.10374 0.09714 -0.0201 1.0000 0.1144
-7.750 -0.2919 0.10258 0.09611 -0.0218 1.0000 0.1180
-7.500 -0.2996 0.10187 0.09555 -0.0254 1.0000 0.1191
-7.250 -0.2875 0.09711 0.09084 -0.0231 1.0000 0.1209
-7.000 -0.2777 0.09385 0.08762 -0.0216 1.0000 0.1250
-6.750 -0.2787 0.09230 0.08619 -0.0233 1.0000 0.1311
-6.500 -0.2825 0.09120 0.08523 -0.0289 1.0000 0.1335
-6.250 -0.2725 0.08698 0.08107 -0.0230 1.0000 0.1376
-6.000 -0.2697 0.08480 0.07898 -0.0228 1.0000 0.1421
-5.750 -0.2701 0.08409 0.07834 -0.0303 1.0000 0.1475
-5.500 -0.2681 0.08104 0.07541 -0.0290 1.0000 0.1486
-5.250 -0.2675 0.07841 0.07286 -0.0263 1.0000 0.1499
-4.750 -0.1674 0.06251 0.05634 -0.0562 0.9771 0.0932
-4.500 -0.1348 0.05890 0.05266 -0.0592 0.9656 0.0898
-4.250 -0.0895 0.05362 0.04715 -0.0679 0.9532 0.0854
-4.000 -0.0405 0.04832 0.04151 -0.0770 0.9408 0.0842
-3.750 0.0069 0.04419 0.03705 -0.0842 0.9285 0.0861
-3.500 0.0556 0.03964 0.03199 -0.0911 0.9153 0.0850
-3.250 0.0999 0.03586 0.02769 -0.0960 0.8994 0.0847
-3.000 0.1390 0.03308 0.02444 -0.0989 0.8804 0.0860
-2.750 0.1778 0.03076 0.02159 -0.1012 0.8611 0.0901
-2.500 0.2164 0.02853 0.01872 -0.1030 0.8420 0.0926
-2.250 0.2517 0.02692 0.01681 -0.1038 0.8227 0.0947
-2.000 0.2834 0.02576 0.01539 -0.1039 0.8011 0.0976
-1.750 0.3149 0.02480 0.01408 -0.1038 0.7802 0.1032
-1.500 0.3447 0.02406 0.01311 -0.1033 0.7599 0.1102
-1.250 0.3736 0.02343 0.01215 -0.1026 0.7379 0.1172
-1.000 0.4020 0.02295 0.01147 -0.1020 0.7163 0.1265
-0.750 0.4301 0.02258 0.01089 -0.1012 0.6956 0.1417
-0.500 0.4571 0.02221 0.01036 -0.1005 0.6731 0.1612
-0.250 0.4839 0.02182 0.00996 -0.0998 0.6514 0.1931
0.000 0.5103 0.02138 0.00968 -0.0991 0.6301 0.2509
0.250 0.5358 0.02091 0.00949 -0.0984 0.6079 0.3445
0.500 0.5573 0.02002 0.00937 -0.0968 0.5881 0.5690
1.000 0.6107 0.01986 0.00895 -0.0951 0.5472 1.0000
1.250 0.6369 0.02020 0.00894 -0.0944 0.5280 1.0000
1.500 0.6630 0.02057 0.00900 -0.0938 0.5102 1.0000
1.750 0.6891 0.02097 0.00913 -0.0933 0.4935 1.0000
2.000 0.7151 0.02139 0.00932 -0.0928 0.4778 1.0000
2.250 0.7412 0.02184 0.00956 -0.0923 0.4633 1.0000
2.500 0.7672 0.02231 0.00984 -0.0919 0.4501 1.0000
2.750 0.7933 0.02278 0.01013 -0.0914 0.4388 1.0000
3.000 0.8193 0.02328 0.01049 -0.0910 0.4282 1.0000
3.250 0.8453 0.02382 0.01095 -0.0907 0.4189 1.0000
3.500 0.8715 0.02434 0.01134 -0.0903 0.4113 1.0000
3.750 0.8974 0.02494 0.01191 -0.0900 0.4037 1.0000
4.000 0.9233 0.02552 0.01243 -0.0897 0.3973 1.0000
4.250 0.9492 0.02614 0.01300 -0.0893 0.3915 1.0000
4.500 0.9745 0.02682 0.01370 -0.0890 0.3854 1.0000
4.750 1.0002 0.02744 0.01428 -0.0886 0.3807 1.0000
5.000 1.0253 0.02816 0.01504 -0.0883 0.3759 1.0000
5.250 1.0499 0.02895 0.01592 -0.0880 0.3711 1.0000
5.500 1.0749 0.02970 0.01671 -0.0876 0.3672 1.0000
5.750 1.1006 0.03044 0.01745 -0.0873 0.3643 1.0000
6.000 1.1243 0.03140 0.01855 -0.0870 0.3611 1.0000
6.250 1.1471 0.03246 0.01983 -0.0866 0.3578 1.0000
6.500 1.1702 0.03351 0.02103 -0.0862 0.3550 1.0000
6.750 1.1935 0.03454 0.02219 -0.0858 0.3526 1.0000
7.000 1.2172 0.03555 0.02331 -0.0854 0.3504 1.0000
7.250 1.2416 0.03652 0.02439 -0.0851 0.3484 1.0000
7.500 1.2595 0.03808 0.02624 -0.0844 0.3457 1.0000
7.750 1.2766 0.03972 0.02818 -0.0837 0.3428 1.0000
8.000 1.2939 0.04134 0.03005 -0.0830 0.3404 1.0000
8.250 1.3112 0.04300 0.03199 -0.0823 0.3384 1.0000
8.500 1.3284 0.04470 0.03392 -0.0817 0.3367 1.0000
8.750 1.3455 0.04642 0.03586 -0.0810 0.3351 1.0000
9.000 1.3629 0.04816 0.03782 -0.0803 0.3337 1.0000
9.250 1.3709 0.05075 0.04071 -0.0793 0.3319 1.0000
9.500 1.3524 0.05560 0.04597 -0.0775 0.3284 1.0000
9.750 1.3318 0.06058 0.05122 -0.0759 0.3246 1.0000
10.250 1.3951 0.06014 0.05109 -0.0743 0.3175 1.0000
10.500 1.1565 0.09416 0.08496 -0.0839 0.3076 1.0000
10.750 1.1797 0.09418 0.08515 -0.0822 0.3041 1.0000
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Polar data table (+)
Polar graphs
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