GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 590 AIRFOIL (goe590-il) Reynolds number: 100,000 Max Cl/Cd: 53.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe590-il-100000-n5.txt Download as CSV file: xf-goe590-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 590 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4084 0.10833 0.10358 -0.0127 1.0000 0.0281
-8.250 -0.4061 0.10585 0.10116 -0.0147 1.0000 0.0282
-8.000 -0.4038 0.10321 0.09859 -0.0166 1.0000 0.0282
-7.750 -0.3999 0.10049 0.09592 -0.0190 1.0000 0.0283
-7.500 -0.3926 0.09736 0.09282 -0.0215 1.0000 0.0283
-7.250 -0.3840 0.09415 0.08963 -0.0242 1.0000 0.0284
-7.000 -0.3740 0.09082 0.08631 -0.0263 1.0000 0.0284
-6.750 -0.3632 0.08736 0.08285 -0.0283 1.0000 0.0284
-6.500 -0.3570 0.08231 0.07788 -0.0281 1.0000 0.0287
-6.250 -0.3506 0.07787 0.07348 -0.0271 1.0000 0.0292
-6.000 -0.3412 0.07435 0.06999 -0.0276 1.0000 0.0296
-5.750 -0.3311 0.07091 0.06652 -0.0283 1.0000 0.0301
-5.500 -0.3198 0.06763 0.06324 -0.0293 1.0000 0.0306
-5.250 -0.3078 0.06445 0.06006 -0.0301 1.0000 0.0311
-5.000 -0.2953 0.06140 0.05700 -0.0308 1.0000 0.0316
-4.750 -0.2799 0.05821 0.05376 -0.0319 0.9979 0.0316
-4.500 -0.2282 0.05382 0.04897 -0.0396 0.9795 0.0282
-4.250 -0.2053 0.04899 0.04412 -0.0422 0.9619 0.0262
-4.000 -0.1662 0.04476 0.03960 -0.0464 0.9432 0.0271
-3.750 -0.1320 0.04067 0.03525 -0.0494 0.9244 0.0262
-3.500 -0.0977 0.03680 0.03106 -0.0517 0.9049 0.0253
-3.000 -0.0334 0.02972 0.02310 -0.0536 0.8647 0.0255
-2.750 -0.0015 0.02631 0.01894 -0.0530 0.8454 0.0283
-2.500 0.0236 0.02396 0.01625 -0.0527 0.8247 0.0307
-2.250 0.0510 0.02185 0.01362 -0.0519 0.8057 0.0336
-2.000 0.0786 0.01998 0.01115 -0.0511 0.7881 0.0401
-1.750 0.1055 0.01881 0.00957 -0.0505 0.7706 0.0465
-1.500 0.1323 0.01771 0.00814 -0.0499 0.7543 0.0534
-1.250 0.1592 0.01679 0.00695 -0.0493 0.7390 0.0583
-1.000 0.1860 0.01616 0.00608 -0.0488 0.7242 0.0647
-0.750 0.2120 0.01573 0.00551 -0.0483 0.7103 0.0716
-0.500 0.2379 0.01526 0.00487 -0.0477 0.6971 0.0747
-0.250 0.2641 0.01490 0.00437 -0.0472 0.6846 0.0796
0.000 0.2907 0.01464 0.00399 -0.0468 0.6727 0.0915
0.250 0.3168 0.01438 0.00372 -0.0464 0.6617 0.1280
0.500 0.3412 0.01394 0.00361 -0.0460 0.6507 0.2553
1.000 0.4453 0.01249 0.00341 -0.0562 0.6291 1.0000
1.250 0.4699 0.01264 0.00341 -0.0555 0.6204 1.0000
1.500 0.4946 0.01280 0.00349 -0.0550 0.6118 1.0000
1.750 0.5192 0.01297 0.00357 -0.0543 0.6048 1.0000
2.000 0.5439 0.01314 0.00371 -0.0538 0.5966 1.0000
2.250 0.5686 0.01333 0.00384 -0.0532 0.5902 1.0000
2.500 0.5934 0.01354 0.00406 -0.0527 0.5831 1.0000
2.750 0.6182 0.01375 0.00429 -0.0521 0.5775 1.0000
3.000 0.6430 0.01398 0.00459 -0.0517 0.5710 1.0000
3.250 0.6678 0.01422 0.00487 -0.0511 0.5652 1.0000
3.500 0.6927 0.01448 0.00521 -0.0506 0.5598 1.0000
3.750 0.7175 0.01476 0.00567 -0.0501 0.5542 1.0000
4.000 0.7426 0.01504 0.00607 -0.0496 0.5494 1.0000
4.250 0.7671 0.01534 0.00657 -0.0491 0.5427 1.0000
4.500 0.7902 0.01550 0.00685 -0.0480 0.5273 1.0000
4.750 0.8125 0.01560 0.00710 -0.0466 0.5068 1.0000
5.000 0.8289 0.01543 0.00691 -0.0439 0.4401 1.0000
5.250 0.8260 0.01818 0.00774 -0.0397 0.0882 1.0000
5.500 0.8384 0.02008 0.00942 -0.0375 0.0396 1.0000
5.750 0.8538 0.02142 0.01093 -0.0356 0.0296 1.0000
6.000 0.8673 0.02282 0.01255 -0.0335 0.0257 1.0000
6.250 0.8802 0.02420 0.01414 -0.0311 0.0232 1.0000
6.500 0.8932 0.02559 0.01566 -0.0289 0.0198 1.0000
6.750 0.9046 0.02770 0.01771 -0.0265 0.0179 1.0000
7.000 0.9245 0.02957 0.01969 -0.0250 0.0173 1.0000
7.250 0.9484 0.03194 0.02224 -0.0237 0.0166 1.0000
7.500 0.9723 0.03442 0.02498 -0.0226 0.0158 1.0000
7.750 0.9934 0.03689 0.02780 -0.0212 0.0144 1.0000
8.000 1.0117 0.03968 0.03096 -0.0197 0.0136 1.0000
8.250 1.0272 0.04291 0.03461 -0.0178 0.0136 1.0000
8.500 1.0386 0.04640 0.03852 -0.0158 0.0137 1.0000
8.750 1.0465 0.04990 0.04251 -0.0136 0.0139 1.0000
9.000 1.0505 0.05353 0.04652 -0.0114 0.0141 1.0000
9.250 1.0510 0.05706 0.05040 -0.0092 0.0144 1.0000
9.500 1.0473 0.06063 0.05426 -0.0070 0.0146 1.0000
9.750 1.0390 0.06415 0.05805 -0.0048 0.0148 1.0000
10.000 1.0265 0.06731 0.06142 -0.0025 0.0150 1.0000
10.250 1.0119 0.07074 0.06502 -0.0012 0.0152 1.0000
10.500 0.9957 0.07469 0.06915 -0.0012 0.0153 1.0000
10.750 0.9800 0.07898 0.07359 -0.0022 0.0154 1.0000
11.000 0.9640 0.08381 0.07856 -0.0042 0.0155 1.0000
11.250 0.9481 0.08917 0.08405 -0.0070 0.0156 1.0000
11.500 0.9320 0.09524 0.09021 -0.0106 0.0157 1.0000
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Polar data table (+)
Polar graphs
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