GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 478 AIRFOIL (goe478-il) Reynolds number: 200,000 Max Cl/Cd: 71.05 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe478-il-200000-n5.txt Download as CSV file: xf-goe478-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 478 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2476 0.08709 0.08309 -0.0681 0.9628 0.0388
-9.250 -0.2411 0.08184 0.07783 -0.0730 0.9546 0.0387
-9.000 -0.2359 0.07602 0.07199 -0.0788 0.9451 0.0385
-8.750 -0.2327 0.06896 0.06491 -0.0868 0.9348 0.0383
-8.500 -0.3470 0.03411 0.02859 -0.1158 0.8966 0.0383
-8.250 -0.3383 0.03051 0.02444 -0.1158 0.8866 0.0387
-8.000 -0.3235 0.02810 0.02158 -0.1153 0.8776 0.0390
-7.750 -0.3049 0.02620 0.01928 -0.1148 0.8702 0.0393
-7.500 -0.2865 0.02474 0.01746 -0.1138 0.8614 0.0397
-7.250 -0.2621 0.02351 0.01602 -0.1137 0.8547 0.0400
-7.000 -0.2411 0.02267 0.01509 -0.1127 0.8462 0.0404
-6.750 -0.2169 0.02185 0.01415 -0.1123 0.8393 0.0408
-6.500 -0.1926 0.02112 0.01329 -0.1118 0.8333 0.0413
-6.250 -0.1699 0.02045 0.01251 -0.1109 0.8271 0.0420
-6.000 -0.1450 0.01981 0.01173 -0.1104 0.8212 0.0429
-5.750 -0.1197 0.01918 0.01093 -0.1099 0.8158 0.0438
-5.500 -0.0963 0.01861 0.01023 -0.1090 0.8095 0.0446
-5.250 -0.0714 0.01801 0.00955 -0.1085 0.8045 0.0452
-5.000 -0.0453 0.01747 0.00898 -0.1081 0.8001 0.0459
-4.750 -0.0214 0.01702 0.00852 -0.1073 0.7945 0.0468
-4.500 0.0030 0.01659 0.00805 -0.1066 0.7886 0.0477
-4.250 0.0291 0.01619 0.00757 -0.1061 0.7835 0.0488
-4.000 0.0546 0.01584 0.00714 -0.1054 0.7783 0.0502
-3.750 0.0783 0.01547 0.00679 -0.1046 0.7726 0.0517
-3.500 0.1037 0.01516 0.00647 -0.1040 0.7675 0.0537
-3.250 0.1305 0.01487 0.00611 -0.1036 0.7632 0.0559
-3.000 0.1546 0.01458 0.00584 -0.1028 0.7581 0.0580
-2.750 0.1792 0.01433 0.00559 -0.1020 0.7526 0.0609
-2.500 0.2052 0.01409 0.00533 -0.1014 0.7473 0.0647
-2.250 0.2315 0.01388 0.00513 -0.1010 0.7422 0.0710
-2.000 0.2555 0.01368 0.00504 -0.1001 0.7361 0.0809
-1.750 0.2811 0.01353 0.00491 -0.0994 0.7303 0.0965
-1.500 0.3084 0.01338 0.00474 -0.0991 0.7250 0.1124
-1.250 0.3317 0.01322 0.00468 -0.0981 0.7179 0.1277
-1.000 0.3567 0.01308 0.00462 -0.0974 0.7108 0.1463
-0.750 0.3832 0.01298 0.00456 -0.0969 0.7045 0.1694
-0.500 0.4068 0.01290 0.00457 -0.0959 0.6964 0.1917
-0.250 0.4324 0.01280 0.00449 -0.0953 0.6889 0.2148
0.000 0.4560 0.01268 0.00446 -0.0943 0.6799 0.2390
0.250 0.4798 0.01250 0.00438 -0.0933 0.6703 0.2701
0.500 0.5015 0.01225 0.00436 -0.0920 0.6595 0.3246
0.750 0.5207 0.01177 0.00435 -0.0903 0.6490 0.4733
1.000 0.5362 0.01121 0.00442 -0.0874 0.6362 0.6672
1.250 0.6011 0.01086 0.00461 -0.0942 0.6190 0.9133
1.500 0.6630 0.01097 0.00459 -0.1010 0.5987 0.9771
1.750 0.7140 0.01111 0.00456 -0.1058 0.5796 1.0000
2.000 0.7327 0.01125 0.00455 -0.1038 0.5648 1.0000
2.250 0.7516 0.01143 0.00458 -0.1018 0.5517 1.0000
2.500 0.7711 0.01162 0.00466 -0.1001 0.5404 1.0000
2.750 0.7910 0.01184 0.00475 -0.0983 0.5310 1.0000
3.000 0.8114 0.01204 0.00487 -0.0968 0.5218 1.0000
3.250 0.8315 0.01229 0.00501 -0.0951 0.5122 1.0000
3.500 0.8512 0.01252 0.00516 -0.0934 0.5013 1.0000
3.750 0.8711 0.01278 0.00532 -0.0918 0.4913 1.0000
4.000 0.8911 0.01300 0.00550 -0.0902 0.4819 1.0000
4.250 0.9118 0.01325 0.00568 -0.0887 0.4744 1.0000
4.500 0.9321 0.01345 0.00587 -0.0871 0.4662 1.0000
4.750 0.9522 0.01371 0.00606 -0.0855 0.4587 1.0000
5.000 0.9724 0.01390 0.00627 -0.0840 0.4507 1.0000
5.250 0.9921 0.01413 0.00647 -0.0823 0.4428 1.0000
5.500 1.0119 0.01437 0.00669 -0.0807 0.4352 1.0000
5.750 1.0313 0.01458 0.00691 -0.0790 0.4271 1.0000
6.000 1.0502 0.01485 0.00713 -0.0773 0.4196 1.0000
6.250 1.0693 0.01505 0.00738 -0.0756 0.4112 1.0000
6.500 1.0865 0.01533 0.00761 -0.0735 0.4026 1.0000
6.750 1.1037 0.01556 0.00788 -0.0715 0.3918 1.0000
7.000 1.1179 0.01584 0.00813 -0.0689 0.3806 1.0000
7.250 1.1296 0.01615 0.00840 -0.0659 0.3677 1.0000
7.500 1.1417 0.01647 0.00870 -0.0630 0.3527 1.0000
7.750 1.1526 0.01687 0.00905 -0.0601 0.3359 1.0000
8.000 1.1629 0.01733 0.00945 -0.0571 0.3172 1.0000
8.250 1.1730 0.01786 0.00991 -0.0542 0.2978 1.0000
8.500 1.1820 0.01848 0.01045 -0.0513 0.2783 1.0000
8.750 1.1903 0.01919 0.01107 -0.0484 0.2600 1.0000
9.000 1.1984 0.01997 0.01177 -0.0457 0.2433 1.0000
9.250 1.2065 0.02081 0.01255 -0.0431 0.2279 1.0000
9.500 1.2149 0.02169 0.01337 -0.0407 0.2144 1.0000
9.750 1.2231 0.02263 0.01426 -0.0383 0.2022 1.0000
10.000 1.2318 0.02358 0.01519 -0.0362 0.1913 1.0000
10.250 1.2415 0.02453 0.01613 -0.0342 0.1812 1.0000
10.500 1.2497 0.02560 0.01719 -0.0323 0.1724 1.0000
10.750 1.2591 0.02664 0.01823 -0.0305 0.1636 1.0000
11.000 1.2675 0.02778 0.01937 -0.0288 0.1559 1.0000
11.250 1.2754 0.02899 0.02059 -0.0271 0.1479 1.0000
11.500 1.2836 0.03023 0.02184 -0.0255 0.1409 1.0000
11.750 1.2901 0.03161 0.02323 -0.0240 0.1336 1.0000
12.000 1.2976 0.03298 0.02462 -0.0226 0.1272 1.0000
12.250 1.3034 0.03450 0.02616 -0.0212 0.1209 1.0000
12.500 1.3096 0.03604 0.02773 -0.0199 0.1156 1.0000
12.750 1.3152 0.03767 0.02939 -0.0187 0.1102 1.0000
13.000 1.3185 0.03953 0.03128 -0.0174 0.1059 1.0000
13.250 1.3248 0.04119 0.03301 -0.0164 0.1014 1.0000
13.500 1.3278 0.04319 0.03503 -0.0154 0.0973 1.0000
13.750 1.3306 0.04526 0.03714 -0.0145 0.0940 1.0000
14.000 1.3353 0.04722 0.03918 -0.0138 0.0905 1.0000
14.250 1.3382 0.04941 0.04142 -0.0131 0.0879 1.0000
14.500 1.3382 0.05195 0.04399 -0.0126 0.0853 1.0000
14.750 1.3421 0.05415 0.04627 -0.0121 0.0832 1.0000
15.000 1.3454 0.05647 0.04867 -0.0117 0.0811 1.0000
15.250 1.3478 0.05896 0.05123 -0.0115 0.0793 1.0000
15.500 1.3491 0.06161 0.05394 -0.0114 0.0777 1.0000
15.750 1.3490 0.06447 0.05683 -0.0114 0.0762 1.0000
16.000 1.3515 0.06708 0.05952 -0.0114 0.0747 1.0000
16.250 1.3548 0.06962 0.06215 -0.0114 0.0733 1.0000
16.500 1.3573 0.07231 0.06493 -0.0116 0.0718 1.0000
16.750 1.3593 0.07506 0.06776 -0.0119 0.0706 1.0000
17.000 1.3609 0.07789 0.07065 -0.0122 0.0695 1.0000
17.250 1.3618 0.08081 0.07362 -0.0126 0.0684 1.0000
17.500 1.3632 0.08363 0.07643 -0.0129 0.0673 1.0000
17.750 1.3660 0.08638 0.07932 -0.0133 0.0663 1.0000
18.000 1.3684 0.08920 0.08225 -0.0138 0.0653 1.0000
18.250 1.3697 0.09220 0.08535 -0.0145 0.0641 1.0000
18.500 1.3707 0.09527 0.08851 -0.0152 0.0629 1.0000
18.750 1.3705 0.09853 0.09184 -0.0161 0.0617 1.0000
19.000 1.3711 0.10164 0.09498 -0.0170 0.0605 1.0000
19.250 1.3729 0.10452 0.09787 -0.0178 0.0595 1.0000
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