GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 507 AIRFOIL (goe507-il) Reynolds number: 200,000 Max Cl/Cd: 73.76 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe507-il-200000.txt Download as CSV file: xf-goe507-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 507 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4209 0.08781 0.08411 -0.0326 1.0000 0.0650
-8.500 -0.4246 0.08463 0.08098 -0.0340 1.0000 0.0676
-8.250 -0.4412 0.08121 0.07765 -0.0365 1.0000 0.0695
-8.000 -0.3693 0.06682 0.06353 -0.0366 1.0000 0.0744
-7.750 -0.3768 0.06462 0.06138 -0.0347 1.0000 0.0756
-7.500 -0.5014 0.06743 0.06392 -0.0424 1.0000 0.0720
-7.250 -0.4942 0.06697 0.06358 -0.0371 1.0000 0.0734
-7.000 -0.4936 0.06597 0.06261 -0.0334 1.0000 0.0748
-6.750 -0.4966 0.06399 0.06063 -0.0314 1.0000 0.0764
-6.500 -0.4990 0.06137 0.05797 -0.0305 1.0000 0.0792
-6.250 -0.5013 0.05334 0.04955 -0.0363 0.9986 0.0864
-6.000 -0.4749 0.05206 0.04834 -0.0367 0.9956 0.0890
-5.750 -0.4575 0.03412 0.02869 -0.0448 0.9885 0.0721
-5.500 -0.4307 0.02985 0.02394 -0.0464 0.9851 0.0726
-5.250 -0.3998 0.02853 0.02273 -0.0481 0.9820 0.0760
-5.000 -0.3735 0.02559 0.01928 -0.0486 0.9773 0.0765
-4.750 -0.3417 0.02401 0.01740 -0.0498 0.9737 0.0794
-4.500 -0.3061 0.02226 0.01524 -0.0515 0.9709 0.0811
-4.250 -0.2755 0.02127 0.01392 -0.0521 0.9649 0.0835
-4.000 -0.2375 0.02034 0.01270 -0.0540 0.9600 0.0847
-3.750 -0.1972 0.01849 0.01070 -0.0566 0.9569 0.0872
-3.500 -0.1664 0.01775 0.00992 -0.0573 0.9512 0.0897
-3.250 -0.1326 0.01707 0.00918 -0.0584 0.9467 0.0915
-3.000 -0.0943 0.01643 0.00848 -0.0604 0.9435 0.0937
-2.750 -0.0534 0.01589 0.00789 -0.0629 0.9413 0.0969
-2.500 -0.0272 0.01551 0.00749 -0.0625 0.9345 0.0990
-2.250 0.0086 0.01486 0.00692 -0.0641 0.9304 0.1025
-2.000 0.0485 0.01440 0.00650 -0.0664 0.9276 0.1072
-1.500 0.1110 0.01375 0.00597 -0.0674 0.9162 0.1234
-1.250 0.1473 0.01327 0.00573 -0.0689 0.9122 0.1585
-1.000 0.1759 0.01288 0.00564 -0.0689 0.9059 0.2380
-0.750 0.2042 0.01249 0.00549 -0.0689 0.8991 0.2994
-0.500 0.2331 0.01159 0.00533 -0.0690 0.8946 0.4891
-0.250 0.3549 0.01014 0.00519 -0.0873 0.8994 1.0000
0.000 0.3820 0.01008 0.00503 -0.0867 0.8912 1.0000
0.250 0.4065 0.01002 0.00490 -0.0856 0.8814 1.0000
0.500 0.4290 0.00999 0.00483 -0.0841 0.8703 1.0000
0.750 0.4529 0.00989 0.00466 -0.0827 0.8589 1.0000
1.000 0.4772 0.00977 0.00446 -0.0812 0.8469 1.0000
1.250 0.4996 0.00971 0.00436 -0.0795 0.8337 1.0000
1.500 0.5221 0.00969 0.00431 -0.0780 0.8206 1.0000
1.750 0.5451 0.00964 0.00422 -0.0765 0.8062 1.0000
2.000 0.5682 0.00958 0.00411 -0.0749 0.7901 1.0000
2.250 0.5915 0.00952 0.00398 -0.0734 0.7721 1.0000
2.500 0.6142 0.00950 0.00392 -0.0718 0.7521 1.0000
2.750 0.6372 0.00953 0.00391 -0.0704 0.7317 1.0000
3.000 0.6607 0.00957 0.00389 -0.0691 0.7104 1.0000
3.250 0.6831 0.00963 0.00390 -0.0675 0.6832 1.0000
3.500 0.7051 0.00974 0.00390 -0.0659 0.6515 1.0000
3.750 0.7270 0.00992 0.00396 -0.0644 0.6190 1.0000
4.000 0.7487 0.01015 0.00407 -0.0628 0.5862 1.0000
4.250 0.7695 0.01046 0.00423 -0.0612 0.5517 1.0000
4.500 0.7899 0.01084 0.00444 -0.0595 0.5169 1.0000
4.750 0.8098 0.01124 0.00470 -0.0578 0.4815 1.0000
5.000 0.8295 0.01164 0.00497 -0.0562 0.4411 1.0000
5.250 0.8480 0.01211 0.00526 -0.0543 0.3928 1.0000
5.500 0.8643 0.01275 0.00560 -0.0522 0.3297 1.0000
5.750 0.8768 0.01376 0.00613 -0.0496 0.2396 1.0000
6.000 0.8864 0.01523 0.00690 -0.0468 0.1311 1.0000
6.250 0.9025 0.01620 0.00765 -0.0449 0.1059 1.0000
6.500 0.9194 0.01707 0.00845 -0.0430 0.0953 1.0000
6.750 0.9369 0.01786 0.00926 -0.0413 0.0876 1.0000
7.000 0.9526 0.01885 0.01025 -0.0393 0.0814 1.0000
7.250 0.9700 0.01971 0.01113 -0.0376 0.0757 1.0000
7.500 0.9846 0.02119 0.01252 -0.0356 0.0704 1.0000
7.750 1.0043 0.02197 0.01340 -0.0342 0.0658 1.0000
8.000 1.0232 0.02311 0.01452 -0.0329 0.0615 1.0000
8.250 1.0449 0.02495 0.01636 -0.0321 0.0575 1.0000
8.500 1.0652 0.02581 0.01735 -0.0309 0.0538 1.0000
8.750 1.0862 0.02699 0.01858 -0.0299 0.0509 1.0000
9.000 1.1130 0.02992 0.02147 -0.0304 0.0476 1.0000
9.250 1.1298 0.03057 0.02238 -0.0285 0.0456 1.0000
9.500 1.1483 0.03179 0.02378 -0.0271 0.0432 1.0000
9.750 1.1676 0.03332 0.02543 -0.0260 0.0415 1.0000
10.000 1.1861 0.03504 0.02724 -0.0251 0.0400 1.0000
10.250 1.2039 0.03874 0.03110 -0.0245 0.0384 1.0000
10.500 1.2116 0.04001 0.03275 -0.0216 0.0373 1.0000
10.750 1.2185 0.04204 0.03511 -0.0190 0.0362 1.0000
11.000 1.2227 0.04474 0.03814 -0.0163 0.0354 1.0000
11.250 1.2227 0.04757 0.04129 -0.0134 0.0350 1.0000
11.500 1.2162 0.05049 0.04451 -0.0099 0.0348 1.0000
11.750 1.2040 0.05348 0.04778 -0.0060 0.0348 1.0000
12.000 1.1881 0.05668 0.05125 -0.0027 0.0347 1.0000
12.250 1.1693 0.06030 0.05512 -0.0001 0.0348 1.0000
12.500 1.1475 0.06443 0.05950 0.0016 0.0350 1.0000
12.750 1.1242 0.06907 0.06437 0.0021 0.0353 1.0000
13.000 1.0980 0.07455 0.07006 0.0013 0.0357 1.0000
13.250 1.0725 0.08058 0.07627 -0.0007 0.0362 1.0000
13.500 1.0450 0.08769 0.08355 -0.0042 0.0366 1.0000
13.750 1.0178 0.09570 0.09170 -0.0090 0.0370 1.0000
14.000 0.9936 0.10443 0.10051 -0.0141 0.0377 1.0000
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Polar data table (+)
Polar graphs
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