GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 50,000 Max Cl/Cd: 36.51 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe430-il-50000-n5.txt Download as CSV file: xf-goe430-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 430 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3621 0.10851 0.10102 -0.0451 1.0000 0.1037
-9.250 -0.3681 0.10609 0.09867 -0.0438 1.0000 0.1035
-9.000 -0.3802 0.10350 0.09616 -0.0428 1.0000 0.1036
-8.750 -0.3960 0.10083 0.09357 -0.0417 1.0000 0.1038
-8.500 -0.3877 0.10003 0.09283 -0.0388 1.0000 0.1054
-8.250 -0.3990 0.09797 0.09084 -0.0371 1.0000 0.1057
-8.000 -0.4177 0.09554 0.08851 -0.0353 1.0000 0.1056
-7.750 -0.4392 0.09249 0.08556 -0.0344 1.0000 0.1051
-7.500 -0.4548 0.08720 0.08033 -0.0376 0.9984 0.1045
-7.250 -0.4444 0.07930 0.07236 -0.0479 0.9906 0.1044
-7.000 -0.4281 0.07081 0.06374 -0.0596 0.9831 0.1049
-6.750 -0.4067 0.06640 0.05923 -0.0657 0.9759 0.1066
-6.500 -0.3813 0.05972 0.05229 -0.0763 0.9693 0.1095
-6.250 -0.3508 0.05058 0.04255 -0.0907 0.9622 0.1126
-6.000 -0.3062 0.04327 0.03433 -0.1033 0.9580 0.1160
-5.750 -0.2733 0.04057 0.03127 -0.1074 0.9516 0.1189
-5.500 -0.2381 0.03946 0.03007 -0.1102 0.9460 0.1232
-5.250 -0.1981 0.03733 0.02745 -0.1148 0.9410 0.1297
-5.000 -0.1649 0.03586 0.02575 -0.1172 0.9341 0.1346
-4.750 -0.1259 0.03472 0.02445 -0.1203 0.9291 0.1409
-4.500 -0.0913 0.03352 0.02295 -0.1226 0.9223 0.1497
-4.250 -0.0556 0.03275 0.02207 -0.1249 0.9155 0.1614
-4.000 -0.0133 0.03197 0.02126 -0.1281 0.9108 0.1749
-3.750 0.0156 0.03140 0.02067 -0.1287 0.9004 0.1869
-3.500 0.0597 0.03087 0.02009 -0.1319 0.8944 0.2051
-3.250 0.0886 0.03064 0.01983 -0.1324 0.8831 0.2213
-3.000 0.1295 0.03041 0.01956 -0.1349 0.8761 0.2448
-2.750 0.1592 0.03028 0.01943 -0.1354 0.8657 0.2629
-2.500 0.1964 0.02991 0.01900 -0.1371 0.8587 0.2800
-2.000 0.2622 0.02922 0.01821 -0.1389 0.8424 0.3115
-1.500 0.3240 0.02871 0.01773 -0.1399 0.8251 0.3480
-1.250 0.3539 0.02854 0.01760 -0.1402 0.8160 0.3699
-1.000 0.3836 0.02843 0.01753 -0.1404 0.8072 0.3954
-0.750 0.4148 0.02828 0.01745 -0.1407 0.7990 0.4221
-0.500 0.4417 0.02830 0.01750 -0.1404 0.7892 0.4482
-0.250 0.4747 0.02811 0.01734 -0.1408 0.7820 0.4788
0.000 0.4992 0.02822 0.01752 -0.1401 0.7716 0.5059
0.250 0.5323 0.02797 0.01733 -0.1403 0.7651 0.5365
0.500 0.5549 0.02816 0.01760 -0.1393 0.7540 0.5665
0.750 0.5872 0.02788 0.01742 -0.1391 0.7482 0.6055
1.000 0.6078 0.02813 0.01776 -0.1377 0.7368 0.6411
1.250 0.6396 0.02784 0.01751 -0.1376 0.7309 0.6808
1.500 0.6602 0.02802 0.01778 -0.1363 0.7202 0.7132
1.750 0.6879 0.02774 0.01759 -0.1356 0.7134 0.7477
2.000 0.7078 0.02774 0.01774 -0.1338 0.7038 0.7871
2.500 0.7566 0.02756 0.01771 -0.1320 0.6870 1.0000
2.750 0.7894 0.02783 0.01785 -0.1331 0.6797 1.0000
3.000 0.8184 0.02824 0.01818 -0.1336 0.6711 1.0000
3.250 0.8502 0.02843 0.01828 -0.1342 0.6636 1.0000
3.750 0.9056 0.02905 0.01879 -0.1340 0.6446 1.0000
4.000 0.9371 0.02908 0.01877 -0.1342 0.6360 1.0000
4.250 0.9603 0.02963 0.01931 -0.1336 0.6257 1.0000
4.500 0.9939 0.02956 0.01919 -0.1339 0.6182 1.0000
4.750 1.0135 0.03030 0.01998 -0.1329 0.6074 1.0000
5.000 1.0491 0.03009 0.01972 -0.1333 0.6002 1.0000
5.250 1.0655 0.03097 0.02067 -0.1319 0.5887 1.0000
5.500 1.0915 0.03126 0.02100 -0.1313 0.5791 1.0000
5.750 1.1183 0.03143 0.02118 -0.1307 0.5688 1.0000
6.000 1.1360 0.03214 0.02197 -0.1292 0.5573 1.0000
6.250 1.1645 0.03228 0.02215 -0.1289 0.5484 1.0000
6.500 1.1834 0.03292 0.02289 -0.1275 0.5374 1.0000
6.750 1.2017 0.03358 0.02365 -0.1261 0.5264 1.0000
7.000 1.2286 0.03369 0.02380 -0.1254 0.5161 1.0000
7.250 1.2476 0.03417 0.02438 -0.1238 0.5034 1.0000
7.500 1.2631 0.03478 0.02508 -0.1218 0.4895 1.0000
7.750 1.2796 0.03526 0.02563 -0.1199 0.4748 1.0000
8.000 1.2954 0.03570 0.02612 -0.1178 0.4588 1.0000
8.250 1.3085 0.03622 0.02669 -0.1153 0.4420 1.0000
8.500 1.3200 0.03683 0.02732 -0.1127 0.4239 1.0000
8.750 1.3298 0.03759 0.02809 -0.1100 0.4051 1.0000
9.000 1.3377 0.03855 0.02905 -0.1074 0.3861 1.0000
9.250 1.3397 0.04004 0.03064 -0.1046 0.3666 1.0000
9.500 1.3427 0.04163 0.03232 -0.1022 0.3477 1.0000
9.750 1.3478 0.04317 0.03394 -0.1000 0.3301 1.0000
10.000 1.3542 0.04467 0.03545 -0.0980 0.3139 1.0000
10.250 1.3609 0.04618 0.03695 -0.0961 0.2992 1.0000
10.500 1.3678 0.04774 0.03847 -0.0942 0.2861 1.0000
10.750 1.3752 0.04931 0.03997 -0.0925 0.2745 1.0000
11.000 1.3831 0.05091 0.04150 -0.0908 0.2638 1.0000
11.250 1.3895 0.05284 0.04349 -0.0892 0.2536 1.0000
11.500 1.4006 0.05433 0.04492 -0.0877 0.2448 1.0000
11.750 1.4091 0.05622 0.04691 -0.0863 0.2360 1.0000
12.000 1.4229 0.05767 0.04836 -0.0850 0.2281 1.0000
12.250 1.4319 0.05966 0.05051 -0.0837 0.2203 1.0000
12.500 1.4524 0.06069 0.05155 -0.0825 0.2129 1.0000
12.750 1.4532 0.06348 0.05460 -0.0813 0.2060 1.0000
13.000 1.4700 0.06461 0.05563 -0.0801 0.1974 1.0000
13.250 1.4570 0.06860 0.05997 -0.0790 0.1910 1.0000
13.500 1.4593 0.07081 0.06219 -0.0780 0.1827 1.0000
13.750 1.4457 0.07507 0.06672 -0.0775 0.1764 1.0000
14.000 1.4366 0.07878 0.07057 -0.0771 0.1694 1.0000
14.250 1.4278 0.08261 0.07453 -0.0771 0.1628 1.0000
14.500 1.4129 0.08762 0.07979 -0.0777 0.1567 1.0000
14.750 1.4079 0.09104 0.08323 -0.0780 0.1498 1.0000
15.000 1.3892 0.09730 0.08981 -0.0797 0.1442 1.0000
15.250 1.3873 0.10037 0.09285 -0.0803 0.1370 1.0000
15.500 1.3653 0.10782 0.10065 -0.0831 0.1317 1.0000
15.750 1.3626 0.11139 0.10424 -0.0843 0.1246 1.0000
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