GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 433 AIRFOIL (goe433-il) Reynolds number: 200,000 Max Cl/Cd: 75.91 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe433-il-200000.txt Download as CSV file: xf-goe433-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 433 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2476 0.12006 0.11616 -0.0469 1.0000 0.1181
-11.250 -0.2590 0.11946 0.11564 -0.0441 1.0000 0.1205
-11.000 -0.6292 0.04004 0.03505 -0.1184 0.9672 0.0998
-10.750 -0.6111 0.03528 0.02969 -0.1258 0.9591 0.1019
-10.500 -0.5834 0.03256 0.02667 -0.1296 0.9526 0.1038
-10.250 -0.5449 0.03167 0.02585 -0.1322 0.9492 0.1058
-10.000 -0.5178 0.03072 0.02483 -0.1332 0.9411 0.1077
-9.750 -0.4877 0.02925 0.02316 -0.1352 0.9347 0.1100
-9.500 -0.4599 0.02774 0.02133 -0.1369 0.9278 0.1124
-9.250 -0.4351 0.02638 0.01983 -0.1374 0.9190 0.1144
-9.000 -0.4038 0.02565 0.01913 -0.1381 0.9135 0.1166
-8.750 -0.3802 0.02499 0.01842 -0.1377 0.9029 0.1187
-8.500 -0.3519 0.02411 0.01737 -0.1381 0.8958 0.1213
-8.250 -0.3273 0.02338 0.01640 -0.1380 0.8851 0.1239
-8.000 -0.3004 0.02235 0.01532 -0.1379 0.8775 0.1265
-7.750 -0.2748 0.02184 0.01483 -0.1376 0.8672 0.1289
-7.500 -0.2473 0.02129 0.01419 -0.1374 0.8588 0.1319
-7.250 -0.2208 0.02080 0.01352 -0.1373 0.8482 0.1353
-7.000 -0.1937 0.02006 0.01264 -0.1372 0.8394 0.1385
-6.750 -0.1671 0.01961 0.01223 -0.1369 0.8293 0.1417
-6.500 -0.1393 0.01921 0.01175 -0.1368 0.8204 0.1456
-6.250 -0.1114 0.01891 0.01126 -0.1368 0.8109 0.1500
-6.000 -0.0844 0.01826 0.01064 -0.1367 0.8018 0.1544
-5.750 -0.0565 0.01794 0.01028 -0.1366 0.7934 0.1594
-5.500 -0.0281 0.01768 0.00985 -0.1366 0.7838 0.1651
-5.250 -0.0002 0.01713 0.00935 -0.1365 0.7771 0.1715
-5.000 0.0278 0.01689 0.00907 -0.1366 0.7678 0.1788
-4.750 0.0561 0.01645 0.00864 -0.1367 0.7608 0.1861
-4.500 0.0850 0.01626 0.00840 -0.1368 0.7541 0.1947
-4.250 0.1132 0.01594 0.00814 -0.1369 0.7463 0.2032
-4.000 0.1426 0.01578 0.00788 -0.1370 0.7402 0.2125
-3.750 0.1712 0.01554 0.00770 -0.1371 0.7338 0.2213
-3.500 0.2002 0.01544 0.00753 -0.1372 0.7266 0.2313
-3.250 0.2293 0.01520 0.00734 -0.1373 0.7208 0.2412
-3.000 0.2585 0.01510 0.00720 -0.1374 0.7147 0.2522
-2.750 0.2873 0.01497 0.00713 -0.1376 0.7079 0.2639
-2.500 0.3166 0.01480 0.00696 -0.1377 0.7021 0.2769
-2.250 0.3458 0.01470 0.00685 -0.1378 0.6962 0.2922
-2.000 0.3746 0.01460 0.00680 -0.1379 0.6893 0.3098
-1.750 0.4039 0.01448 0.00670 -0.1380 0.6836 0.3298
-1.500 0.4331 0.01442 0.00670 -0.1381 0.6779 0.3515
-1.250 0.4614 0.01440 0.00678 -0.1381 0.6709 0.3726
-1.000 0.4905 0.01440 0.00680 -0.1381 0.6646 0.3928
-0.750 0.5197 0.01451 0.00691 -0.1381 0.6588 0.4124
-0.500 0.5479 0.01462 0.00708 -0.1380 0.6519 0.4310
-0.250 0.5770 0.01473 0.00715 -0.1380 0.6455 0.4489
0.000 0.6061 0.01492 0.00729 -0.1380 0.6394 0.4661
0.250 0.6335 0.01505 0.00751 -0.1377 0.6319 0.4810
0.500 0.6623 0.01518 0.00761 -0.1376 0.6256 0.4961
0.750 0.6911 0.01539 0.00777 -0.1375 0.6195 0.5113
1.000 0.7185 0.01553 0.00795 -0.1373 0.6119 0.5258
1.250 0.7469 0.01562 0.00805 -0.1371 0.6054 0.5384
1.500 0.7750 0.01581 0.00822 -0.1370 0.5988 0.5518
1.750 0.8022 0.01595 0.00839 -0.1367 0.5913 0.5657
2.000 0.8304 0.01604 0.00849 -0.1365 0.5851 0.5788
2.250 0.8577 0.01621 0.00869 -0.1362 0.5785 0.5930
2.500 0.8847 0.01631 0.00884 -0.1360 0.5709 0.6074
2.750 0.9129 0.01637 0.00889 -0.1357 0.5649 0.6195
3.000 0.9400 0.01651 0.00908 -0.1355 0.5584 0.6307
3.250 0.9668 0.01660 0.00922 -0.1352 0.5512 0.6421
3.500 0.9952 0.01660 0.00918 -0.1351 0.5447 0.6523
3.750 1.0209 0.01665 0.00931 -0.1346 0.5359 0.6635
4.000 1.0475 0.01657 0.00923 -0.1342 0.5276 0.6745
4.250 1.0737 0.01660 0.00929 -0.1337 0.5192 0.6870
4.500 1.0993 0.01658 0.00933 -0.1331 0.5107 0.6992
4.750 1.1258 0.01662 0.00937 -0.1327 0.5034 0.7129
5.000 1.1503 0.01665 0.00951 -0.1320 0.4943 0.7292
5.250 1.1765 0.01668 0.00951 -0.1315 0.4869 0.7487
5.500 1.1990 0.01673 0.00974 -0.1305 0.4777 0.7745
5.750 1.2225 0.01671 0.00976 -0.1294 0.4700 0.8192
6.000 1.2424 0.01654 0.00984 -0.1277 0.4611 1.0000
6.250 1.2698 0.01679 0.00996 -0.1278 0.4529 1.0000
6.500 1.2952 0.01710 0.01025 -0.1275 0.4451 1.0000
6.750 1.3201 0.01739 0.01050 -0.1271 0.4373 1.0000
7.000 1.3452 0.01773 0.01077 -0.1267 0.4303 1.0000
7.250 1.3680 0.01805 0.01113 -0.1260 0.4221 1.0000
7.750 1.4128 0.01876 0.01181 -0.1243 0.4059 1.0000
8.000 1.4347 0.01915 0.01213 -0.1234 0.3980 1.0000
8.250 1.4548 0.01955 0.01258 -0.1222 0.3897 1.0000
8.500 1.4740 0.01996 0.01297 -0.1209 0.3811 1.0000
8.750 1.4921 0.02041 0.01345 -0.1195 0.3725 1.0000
9.000 1.5077 0.02088 0.01392 -0.1176 0.3634 1.0000
9.250 1.5215 0.02139 0.01446 -0.1156 0.3545 1.0000
9.500 1.5341 0.02199 0.01505 -0.1134 0.3450 1.0000
9.750 1.5467 0.02264 0.01575 -0.1114 0.3355 1.0000
10.000 1.5561 0.02345 0.01653 -0.1091 0.3252 1.0000
10.250 1.5666 0.02429 0.01744 -0.1071 0.3138 1.0000
10.500 1.5752 0.02529 0.01844 -0.1050 0.3030 1.0000
10.750 1.5815 0.02649 0.01962 -0.1029 0.2913 1.0000
11.000 1.5885 0.02776 0.02093 -0.1010 0.2786 1.0000
11.250 1.5935 0.02925 0.02242 -0.0991 0.2660 1.0000
11.500 1.5961 0.03099 0.02413 -0.0972 0.2535 1.0000
11.750 1.5963 0.03299 0.02610 -0.0953 0.2413 1.0000
12.000 1.5966 0.03510 0.02820 -0.0937 0.2280 1.0000
12.250 1.5960 0.03739 0.03048 -0.0921 0.2162 1.0000
12.500 1.5937 0.03988 0.03296 -0.0906 0.2062 1.0000
12.750 1.5911 0.04251 0.03558 -0.0893 0.1969 1.0000
13.000 1.5895 0.04515 0.03823 -0.0881 0.1884 1.0000
13.250 1.5851 0.04815 0.04122 -0.0871 0.1808 1.0000
13.500 1.5843 0.05090 0.04402 -0.0863 0.1733 1.0000
13.750 1.5788 0.05422 0.04732 -0.0855 0.1663 1.0000
14.000 1.5775 0.05717 0.05033 -0.0849 0.1590 1.0000
14.250 1.5705 0.06081 0.05396 -0.0844 0.1521 1.0000
14.500 1.5687 0.06397 0.05719 -0.0841 0.1444 1.0000
14.750 1.5603 0.06790 0.06111 -0.0838 0.1377 1.0000
15.000 1.5567 0.07141 0.06469 -0.0836 0.1296 1.0000
15.250 1.5498 0.07535 0.06865 -0.0836 0.1228 1.0000
15.500 1.5434 0.07928 0.07260 -0.0836 0.1161 1.0000
15.750 1.5380 0.08312 0.07647 -0.0837 0.1106 1.0000
16.000 1.5329 0.08698 0.08036 -0.0839 0.1059 1.0000
16.250 1.5278 0.09083 0.08421 -0.0841 0.1025 1.0000
16.500 1.5273 0.09410 0.08754 -0.0843 0.0992 1.0000
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