GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 484 AIRFOIL (goe484-il) Reynolds number: 50,000 Max Cl/Cd: 44.38 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe484-il-50000-n5.txt Download as CSV file: xf-goe484-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 484 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3581 0.10399 0.09710 -0.0260 1.0000 0.1082
-7.250 -0.3703 0.10332 0.09655 -0.0246 1.0000 0.1106
-7.000 -0.3809 0.10287 0.09622 -0.0259 1.0000 0.1121
-6.750 -0.3865 0.10218 0.09561 -0.0298 1.0000 0.1128
-6.500 -0.3796 0.09691 0.09040 -0.0245 1.0000 0.1144
-6.250 -0.3759 0.09386 0.08737 -0.0224 1.0000 0.1164
-6.000 -0.3737 0.09136 0.08490 -0.0217 1.0000 0.1190
-5.750 -0.3712 0.08899 0.08256 -0.0222 1.0000 0.1220
-5.500 -0.3641 0.08717 0.08074 -0.0281 1.0000 0.1266
-5.250 -0.3532 0.08412 0.07769 -0.0324 1.0000 0.1281
-5.000 -0.3515 0.08074 0.07437 -0.0275 1.0000 0.1308
-4.750 -0.3431 0.07812 0.07176 -0.0273 1.0000 0.1363
-4.500 -0.3187 0.07505 0.06858 -0.0365 1.0000 0.1433
-4.250 -0.3116 0.07189 0.06545 -0.0344 1.0000 0.1453
-4.000 -0.2979 0.06897 0.06252 -0.0352 1.0000 0.1481
-3.500 -0.1802 0.05490 0.04748 -0.0625 0.9918 0.0818
-3.250 -0.1372 0.05097 0.04328 -0.0692 0.9870 0.0815
-3.000 -0.0970 0.04745 0.03951 -0.0746 0.9821 0.0802
-2.750 -0.0538 0.04397 0.03569 -0.0803 0.9776 0.0776
-2.500 -0.0105 0.04065 0.03194 -0.0855 0.9727 0.0753
-2.250 0.0341 0.03760 0.02837 -0.0905 0.9684 0.0737
-2.000 0.0750 0.03514 0.02542 -0.0941 0.9634 0.0730
-1.750 0.1139 0.03350 0.02339 -0.0970 0.9580 0.0749
-1.500 0.1505 0.03212 0.02164 -0.0993 0.9519 0.0779
-1.250 0.1890 0.03074 0.01986 -0.1016 0.9465 0.0794
-1.000 0.2236 0.02961 0.01836 -0.1030 0.9398 0.0805
-0.750 0.2608 0.02866 0.01707 -0.1048 0.9339 0.0821
-0.500 0.2937 0.02798 0.01618 -0.1058 0.9263 0.0844
-0.250 0.3317 0.02747 0.01555 -0.1077 0.9204 0.0884
0.000 0.3627 0.02713 0.01508 -0.1083 0.9117 0.0955
0.250 0.4016 0.02681 0.01475 -0.1105 0.9058 0.1100
0.500 0.4312 0.02654 0.01454 -0.1109 0.8962 0.1306
0.750 0.4723 0.02594 0.01416 -0.1136 0.8909 0.2044
1.000 0.4961 0.02405 0.01430 -0.1132 0.8812 1.0000
1.250 0.5349 0.02425 0.01416 -0.1150 0.8750 1.0000
1.500 0.5607 0.02459 0.01432 -0.1148 0.8638 1.0000
1.750 0.5911 0.02488 0.01448 -0.1153 0.8548 1.0000
2.000 0.6245 0.02510 0.01462 -0.1163 0.8468 1.0000
2.250 0.6509 0.02548 0.01494 -0.1161 0.8365 1.0000
2.500 0.6874 0.02561 0.01505 -0.1175 0.8301 1.0000
2.750 0.7110 0.02606 0.01552 -0.1169 0.8189 1.0000
3.000 0.7447 0.02625 0.01575 -0.1178 0.8117 1.0000
3.250 0.7715 0.02660 0.01616 -0.1177 0.8015 1.0000
3.500 0.7981 0.02691 0.01657 -0.1173 0.7904 1.0000
3.750 0.8313 0.02681 0.01657 -0.1175 0.7784 1.0000
4.000 0.8644 0.02656 0.01645 -0.1175 0.7650 1.0000
4.250 0.8952 0.02635 0.01642 -0.1170 0.7505 1.0000
4.500 0.9250 0.02560 0.01581 -0.1154 0.7265 1.0000
4.750 0.9558 0.02432 0.01460 -0.1130 0.6896 1.0000
5.000 0.9867 0.02350 0.01384 -0.1111 0.6501 1.0000
5.250 1.0147 0.02304 0.01323 -0.1089 0.5936 1.0000
5.500 1.0337 0.02329 0.01328 -0.1060 0.5280 1.0000
5.750 1.0451 0.02399 0.01362 -0.1022 0.4109 1.0000
6.000 1.0431 0.02629 0.01450 -0.0973 0.2361 1.0000
6.250 1.0467 0.02870 0.01615 -0.0943 0.1375 1.0000
6.500 1.0561 0.03052 0.01767 -0.0918 0.1148 1.0000
6.750 1.0663 0.03213 0.01921 -0.0894 0.1033 1.0000
7.000 1.0790 0.03351 0.02069 -0.0872 0.0962 1.0000
7.250 1.0914 0.03499 0.02225 -0.0851 0.0916 1.0000
7.500 1.1051 0.03660 0.02391 -0.0831 0.0881 1.0000
7.750 1.1253 0.03797 0.02553 -0.0817 0.0844 1.0000
8.000 1.1482 0.03949 0.02715 -0.0808 0.0788 1.0000
8.250 1.1839 0.04144 0.02910 -0.0817 0.0740 1.0000
8.500 1.2227 0.04347 0.03141 -0.0826 0.0702 1.0000
8.750 1.2513 0.04564 0.03379 -0.0827 0.0653 1.0000
9.000 1.2882 0.04917 0.03730 -0.0843 0.0617 1.0000
9.250 1.3059 0.05169 0.04039 -0.0826 0.0597 1.0000
9.500 1.3191 0.05439 0.04358 -0.0807 0.0567 1.0000
9.750 1.3308 0.05738 0.04697 -0.0788 0.0543 1.0000
10.000 1.3401 0.06077 0.05078 -0.0768 0.0531 1.0000
10.250 1.3474 0.06412 0.05441 -0.0749 0.0515 1.0000
10.500 1.3528 0.06779 0.05826 -0.0732 0.0498 1.0000
10.750 1.3505 0.07214 0.06285 -0.0710 0.0486 1.0000
11.000 1.3362 0.07519 0.06633 -0.0671 0.0481 1.0000
11.250 1.3191 0.07847 0.06996 -0.0635 0.0477 1.0000
11.500 1.3006 0.08214 0.07395 -0.0606 0.0475 1.0000
11.750 1.2809 0.08626 0.07835 -0.0587 0.0474 1.0000
12.000 1.2603 0.09086 0.08319 -0.0578 0.0474 1.0000
12.250 1.2388 0.09598 0.08854 -0.0579 0.0475 1.0000
12.500 1.2170 0.10166 0.09442 -0.0590 0.0476 1.0000
12.750 1.1950 0.10798 0.10092 -0.0613 0.0478 1.0000
13.000 1.1740 0.11492 0.10800 -0.0647 0.0481 1.0000
13.250 1.1546 0.12242 0.11560 -0.0688 0.0483 1.0000
13.500 1.1377 0.13033 0.12359 -0.0735 0.0486 1.0000
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Polar data table (+)
Polar graphs
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