GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 428 AIRFOIL (goe428-il) Reynolds number: 500,000 Max Cl/Cd: 104.16 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe428-il-500000.txt Download as CSV file: xf-goe428-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 428 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2964 0.09178 0.08970 -0.0287 1.0000 0.0147
-7.750 -0.2982 0.08983 0.08779 -0.0275 1.0000 0.0150
-7.500 -0.3044 0.08815 0.08616 -0.0257 1.0000 0.0151
-7.250 -0.3012 0.08562 0.08366 -0.0268 0.9985 0.0154
-7.000 -0.2771 0.08140 0.07944 -0.0337 0.9934 0.0170
-6.750 -0.2395 0.07567 0.07369 -0.0478 0.9860 0.0186
-6.500 -0.2057 0.07052 0.06851 -0.0579 0.9800 0.0188
-6.250 -0.1718 0.06521 0.06316 -0.0670 0.9735 0.0189
-6.000 -0.1361 0.05962 0.05749 -0.0760 0.9672 0.0189
-5.750 -0.1115 0.05251 0.05033 -0.0835 0.9588 0.0197
-5.500 -0.0820 0.04922 0.04698 -0.0879 0.9477 0.0204
-5.250 -0.0477 0.04529 0.04294 -0.0937 0.9334 0.0213
-5.000 -0.0133 0.04110 0.03859 -0.0991 0.9160 0.0231
-4.750 0.0276 0.03682 0.03400 -0.1038 0.8967 0.0261
-4.500 0.0545 0.03250 0.02937 -0.1058 0.8787 0.0262
-3.750 0.1185 0.01647 0.01171 -0.1071 0.8358 0.0221
-3.500 0.1438 0.01453 0.00932 -0.1064 0.8239 0.0230
-3.250 0.1698 0.01337 0.00782 -0.1057 0.8122 0.0243
-2.750 0.2214 0.01136 0.00531 -0.1046 0.7889 0.0289
-2.500 0.2476 0.01085 0.00469 -0.1041 0.7776 0.0313
-2.250 0.2741 0.01052 0.00426 -0.1036 0.7664 0.0345
-2.000 0.3008 0.01035 0.00398 -0.1032 0.7551 0.0365
-1.750 0.3259 0.00945 0.00295 -0.1025 0.7435 0.0400
-1.500 0.3520 0.00919 0.00263 -0.1020 0.7307 0.0441
-1.250 0.3783 0.00898 0.00234 -0.1015 0.7178 0.0471
-1.000 0.4046 0.00881 0.00208 -0.1010 0.7049 0.0499
-0.750 0.4309 0.00861 0.00184 -0.1006 0.6924 0.0577
-0.500 0.4572 0.00847 0.00168 -0.1001 0.6799 0.0751
-0.250 0.4834 0.00836 0.00171 -0.0997 0.6675 0.1416
0.000 0.5097 0.00835 0.00166 -0.0994 0.6550 0.1628
0.250 0.5358 0.00831 0.00162 -0.0990 0.6425 0.1863
0.500 0.5608 0.00805 0.00166 -0.0986 0.6296 0.3119
0.750 0.6015 0.00660 0.00176 -0.1017 0.6153 1.0000
1.000 0.6270 0.00672 0.00177 -0.1011 0.6010 1.0000
1.250 0.6525 0.00684 0.00178 -0.1005 0.5849 1.0000
1.500 0.6778 0.00698 0.00180 -0.0999 0.5655 1.0000
1.750 0.7027 0.00714 0.00184 -0.0992 0.5441 1.0000
2.000 0.7277 0.00731 0.00189 -0.0986 0.5211 1.0000
2.250 0.7523 0.00751 0.00196 -0.0979 0.4967 1.0000
2.500 0.7767 0.00774 0.00205 -0.0972 0.4734 1.0000
2.750 0.8014 0.00797 0.00217 -0.0966 0.4531 1.0000
3.000 0.8261 0.00821 0.00230 -0.0960 0.4351 1.0000
3.250 0.8508 0.00845 0.00246 -0.0955 0.4196 1.0000
3.500 0.8758 0.00867 0.00261 -0.0949 0.4065 1.0000
3.750 0.9010 0.00888 0.00277 -0.0944 0.3962 1.0000
4.250 0.9516 0.00928 0.00314 -0.0935 0.3798 1.0000
4.500 0.9765 0.00952 0.00333 -0.0930 0.3726 1.0000
4.750 1.0022 0.00968 0.00352 -0.0927 0.3654 1.0000
5.000 1.0270 0.00991 0.00372 -0.0921 0.3560 1.0000
5.250 1.0515 0.01015 0.00393 -0.0916 0.3436 1.0000
5.500 1.0762 0.01036 0.00413 -0.0911 0.3313 1.0000
5.750 1.1010 0.01057 0.00434 -0.0906 0.3192 1.0000
6.000 1.1250 0.01083 0.00456 -0.0900 0.3031 1.0000
6.250 1.1490 0.01110 0.00481 -0.0894 0.2817 1.0000
6.500 1.1702 0.01161 0.00512 -0.0884 0.2356 1.0000
6.750 1.1729 0.01390 0.00645 -0.0849 0.0868 1.0000
7.000 1.1841 0.01540 0.00761 -0.0823 0.0258 1.0000
7.250 1.2045 0.01598 0.00830 -0.0810 0.0218 1.0000
7.500 1.2237 0.01664 0.00906 -0.0796 0.0194 1.0000
7.750 1.2397 0.01755 0.01008 -0.0777 0.0175 1.0000
8.000 1.2508 0.01877 0.01145 -0.0750 0.0160 1.0000
8.250 1.2679 0.01943 0.01218 -0.0734 0.0152 1.0000
8.500 1.2811 0.02031 0.01315 -0.0711 0.0143 1.0000
8.750 1.2908 0.02126 0.01419 -0.0683 0.0136 1.0000
9.000 1.2974 0.02226 0.01527 -0.0650 0.0131 1.0000
9.250 1.3024 0.02338 0.01648 -0.0617 0.0126 1.0000
9.500 1.3056 0.02468 0.01786 -0.0584 0.0122 1.0000
9.750 1.3068 0.02621 0.01948 -0.0552 0.0119 1.0000
10.000 1.3064 0.02805 0.02140 -0.0521 0.0116 1.0000
10.250 1.3060 0.03025 0.02366 -0.0492 0.0113 1.0000
10.500 1.3092 0.03280 0.02630 -0.0468 0.0107 1.0000
10.750 1.3188 0.03429 0.02790 -0.0452 0.0105 1.0000
11.000 1.3280 0.03579 0.02951 -0.0438 0.0102 1.0000
11.250 1.3380 0.03762 0.03146 -0.0423 0.0100 1.0000
11.500 1.3483 0.03961 0.03357 -0.0409 0.0098 1.0000
11.750 1.3591 0.04184 0.03597 -0.0396 0.0097 1.0000
12.000 1.3686 0.04439 0.03869 -0.0382 0.0097 1.0000
12.250 1.3740 0.04708 0.04158 -0.0369 0.0095 1.0000
12.500 1.3790 0.05070 0.04543 -0.0355 0.0098 1.0000
14.500 1.1503 0.09469 0.09163 -0.0347 0.0166 1.0000
14.750 1.1270 0.09966 0.09675 -0.0377 0.0167 1.0000
15.000 1.1054 0.10499 0.10225 -0.0413 0.0169 1.0000
15.250 1.0810 0.11148 0.10891 -0.0457 0.0170 1.0000
15.500 1.0568 0.11842 0.11604 -0.0510 0.0173 1.0000
15.750 1.0305 0.12647 0.12425 -0.0568 0.0174 1.0000
16.000 0.9691 0.14353 0.14165 -0.0700 0.0187 1.0000
16.250 0.9196 0.16095 0.15924 -0.0816 0.0199 1.0000
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Polar data table (+)
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