GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 100,000 Max Cl/Cd: 60.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe517-il-100000-n5.txt Download as CSV file: xf-goe517-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3162 0.09180 0.08739 -0.0272 1.0000 0.0403
-7.000 -0.3255 0.09027 0.08596 -0.0253 1.0000 0.0409
-6.750 -0.3333 0.08855 0.08434 -0.0240 1.0000 0.0415
-6.500 -0.3412 0.08694 0.08282 -0.0227 1.0000 0.0420
-6.250 -0.3127 0.08303 0.07885 -0.0346 0.9913 0.0445
-6.000 -0.2754 0.07836 0.07405 -0.0467 0.9818 0.0451
-5.750 -0.2462 0.07301 0.06863 -0.0535 0.9741 0.0455
-5.500 -0.2337 0.06839 0.06407 -0.0520 0.9689 0.0472
-5.000 -0.1726 0.05806 0.05344 -0.0636 0.9540 0.0340
-4.750 -0.1455 0.05381 0.04909 -0.0673 0.9474 0.0306
-4.500 -0.1136 0.04884 0.04392 -0.0723 0.9402 0.0281
-4.250 -0.0755 0.04289 0.03764 -0.0778 0.9344 0.0259
-4.000 -0.0437 0.03795 0.03234 -0.0808 0.9271 0.0253
-3.750 -0.0121 0.03519 0.02934 -0.0830 0.9212 0.0275
-3.250 0.0501 0.02707 0.02018 -0.0855 0.9078 0.0284
-3.000 0.0848 0.02361 0.01602 -0.0867 0.9034 0.0303
-2.750 0.1120 0.02129 0.01306 -0.0861 0.8950 0.0337
-2.500 0.1459 0.01937 0.01071 -0.0868 0.8897 0.0369
-2.250 0.1748 0.01852 0.00966 -0.0868 0.8816 0.0439
-2.000 0.2070 0.01762 0.00864 -0.0873 0.8750 0.0542
-1.750 0.2360 0.01704 0.00799 -0.0873 0.8668 0.0707
-1.500 0.2674 0.01664 0.00751 -0.0877 0.8595 0.0963
-1.250 0.2954 0.01636 0.00714 -0.0876 0.8502 0.1194
-1.000 0.3271 0.01599 0.00666 -0.0881 0.8427 0.1393
-0.750 0.3534 0.01568 0.00633 -0.0876 0.8321 0.1530
-0.500 0.3830 0.01536 0.00596 -0.0876 0.8229 0.1673
-0.250 0.4129 0.01506 0.00559 -0.0877 0.8122 0.1862
0.000 0.4397 0.01478 0.00534 -0.0872 0.7984 0.2180
0.250 0.4657 0.01420 0.00512 -0.0867 0.7835 0.3375
0.500 0.5229 0.01271 0.00478 -0.0923 0.7678 1.0000
0.750 0.5480 0.01276 0.00464 -0.0914 0.7518 1.0000
1.000 0.5730 0.01284 0.00456 -0.0906 0.7367 1.0000
1.250 0.5980 0.01292 0.00451 -0.0898 0.7215 1.0000
1.500 0.6229 0.01302 0.00448 -0.0889 0.7061 1.0000
1.750 0.6477 0.01312 0.00448 -0.0881 0.6903 1.0000
2.000 0.6726 0.01323 0.00449 -0.0873 0.6745 1.0000
2.250 0.6974 0.01336 0.00453 -0.0865 0.6586 1.0000
2.500 0.7222 0.01351 0.00460 -0.0857 0.6426 1.0000
2.750 0.7469 0.01367 0.00468 -0.0850 0.6269 1.0000
3.000 0.7714 0.01386 0.00480 -0.0842 0.6112 1.0000
3.250 0.7959 0.01406 0.00496 -0.0834 0.5958 1.0000
3.500 0.8202 0.01429 0.00513 -0.0826 0.5805 1.0000
3.750 0.8445 0.01455 0.00534 -0.0818 0.5654 1.0000
4.000 0.8685 0.01482 0.00561 -0.0810 0.5505 1.0000
4.250 0.8925 0.01512 0.00590 -0.0802 0.5355 1.0000
4.500 0.9161 0.01543 0.00621 -0.0793 0.5202 1.0000
4.750 0.9396 0.01576 0.00658 -0.0785 0.5047 1.0000
5.000 0.9628 0.01609 0.00696 -0.0776 0.4888 1.0000
5.250 0.9857 0.01643 0.00737 -0.0767 0.4722 1.0000
5.500 1.0083 0.01678 0.00782 -0.0757 0.4549 1.0000
5.750 1.0309 0.01714 0.00827 -0.0747 0.4381 1.0000
6.000 1.0532 0.01751 0.00874 -0.0738 0.4217 1.0000
6.250 1.0754 0.01792 0.00926 -0.0727 0.4061 1.0000
6.500 1.0976 0.01836 0.00981 -0.0717 0.3920 1.0000
6.750 1.1188 0.01882 0.01037 -0.0706 0.3763 1.0000
7.000 1.1341 0.01938 0.01081 -0.0684 0.3419 1.0000
7.250 1.1470 0.02014 0.01142 -0.0661 0.3019 1.0000
7.500 1.1594 0.02098 0.01213 -0.0638 0.2505 1.0000
7.750 1.1647 0.02251 0.01309 -0.0607 0.1450 1.0000
8.000 1.1591 0.02545 0.01512 -0.0566 0.0463 1.0000
8.250 1.1663 0.02717 0.01677 -0.0538 0.0320 1.0000
8.500 1.1743 0.02867 0.01841 -0.0510 0.0274 1.0000
8.750 1.1802 0.03007 0.02003 -0.0480 0.0250 1.0000
9.000 1.1824 0.03162 0.02179 -0.0447 0.0226 1.0000
9.250 1.1797 0.03354 0.02387 -0.0412 0.0209 1.0000
9.500 1.1744 0.03575 0.02623 -0.0378 0.0198 1.0000
9.750 1.1754 0.03765 0.02831 -0.0353 0.0192 1.0000
10.000 1.1767 0.03971 0.03053 -0.0331 0.0185 1.0000
10.250 1.1796 0.04183 0.03279 -0.0311 0.0178 1.0000
10.500 1.1841 0.04395 0.03503 -0.0295 0.0168 1.0000
10.750 1.1888 0.04617 0.03734 -0.0281 0.0157 1.0000
11.000 1.1951 0.04864 0.03984 -0.0267 0.0149 1.0000
11.250 1.2074 0.05120 0.04256 -0.0253 0.0144 1.0000
11.500 1.2178 0.05381 0.04544 -0.0240 0.0141 1.0000
11.750 1.2254 0.05682 0.04874 -0.0228 0.0138 1.0000
12.000 1.2282 0.06005 0.05226 -0.0217 0.0136 1.0000
12.250 1.2259 0.06351 0.05602 -0.0209 0.0133 1.0000
12.500 1.2209 0.06724 0.06003 -0.0204 0.0131 1.0000
12.750 1.2129 0.07128 0.06435 -0.0204 0.0129 1.0000
13.000 1.2033 0.07564 0.06896 -0.0208 0.0128 1.0000
13.250 1.1922 0.08024 0.07380 -0.0218 0.0125 1.0000
13.500 1.1794 0.08537 0.07917 -0.0234 0.0124 1.0000
13.750 1.1657 0.09086 0.08487 -0.0255 0.0123 1.0000
14.000 1.1495 0.09722 0.09149 -0.0284 0.0126 1.0000
14.250 1.1337 0.10378 0.09826 -0.0318 0.0126 1.0000
14.500 1.1174 0.11091 0.10558 -0.0358 0.0127 1.0000
14.750 1.1009 0.11863 0.11348 -0.0404 0.0128 1.0000
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