GOE 561 AIRFOIL (goe561-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 561 AIRFOIL (goe561-il) Reynolds number: 1,000,000 Max Cl/Cd: 42.02 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe561-il-1000000-n5.txt Download as CSV file: xf-goe561-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 561 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 0.5413 0.09905 0.09420 -0.1726 0.4814 0.0190
-12.250 0.5484 0.09711 0.09225 -0.1734 0.4792 0.0210
-12.000 0.5532 0.09473 0.08987 -0.1741 0.4779 0.0211
-11.750 0.5635 0.09327 0.08841 -0.1742 0.4760 0.0200
-11.500 0.5692 0.09116 0.08629 -0.1747 0.4743 0.0205
-11.250 0.5748 0.08911 0.08425 -0.1751 0.4729 0.0199
-11.000 0.5793 0.08682 0.08198 -0.1756 0.4723 0.0206
-10.750 0.5845 0.08474 0.07992 -0.1759 0.4718 0.0198
-10.500 0.5893 0.08267 0.07787 -0.1762 0.4709 0.0200
-10.250 0.5944 0.08068 0.07590 -0.1765 0.4697 0.0201
-10.000 0.5964 0.07835 0.07358 -0.1767 0.4689 0.0197
-9.750 0.5982 0.07608 0.07134 -0.1769 0.4679 0.0195
-9.500 0.6014 0.07409 0.06936 -0.1770 0.4660 0.0198
-9.250 0.6017 0.07183 0.06712 -0.1770 0.4641 0.0202
-9.000 0.6036 0.06990 0.06521 -0.1769 0.4627 0.0201
-8.750 0.6013 0.06757 0.06290 -0.1767 0.4614 0.0200
-8.500 0.5975 0.06524 0.06058 -0.1763 0.4599 0.0201
-8.250 0.5914 0.06286 0.05822 -0.1758 0.4582 0.0198
-8.000 0.5832 0.06043 0.05583 -0.1753 0.4569 0.0199
-7.750 0.5698 0.05782 0.05325 -0.1746 0.4555 0.0199
-7.500 0.5418 0.05447 0.04996 -0.1746 0.4549 0.0202
-7.250 0.5121 0.05216 0.04768 -0.1710 0.4536 0.0200
-7.000 0.4695 0.05019 0.04573 -0.1635 0.4533 0.0204
-6.750 0.4353 0.04887 0.04444 -0.1555 0.4528 0.0204
-6.500 0.4061 0.04689 0.04246 -0.1483 0.4521 0.0204
-6.250 0.3810 0.04476 0.04030 -0.1416 0.4514 0.0204
-6.000 0.3576 0.04244 0.03793 -0.1348 0.4507 0.0205
-5.750 0.3373 0.04032 0.03575 -0.1279 0.4499 0.0205
-5.250 0.1543 0.02374 0.01805 -0.0882 0.4502 0.0215
-5.000 0.1674 0.02366 0.01794 -0.0855 0.4487 0.0215
-4.750 0.1774 0.02329 0.01752 -0.0823 0.4469 0.0216
-4.500 0.1576 0.02004 0.01383 -0.0733 0.4461 0.0220
-4.250 0.1709 0.01992 0.01367 -0.0705 0.4442 0.0221
-4.000 0.1854 0.01994 0.01367 -0.0680 0.4425 0.0222
-3.750 0.1961 0.01948 0.01311 -0.0647 0.4409 0.0223
-3.500 0.2033 0.01851 0.01193 -0.0608 0.4391 0.0226
-3.250 0.2146 0.01777 0.01101 -0.0576 0.4367 0.0227
-3.000 0.2302 0.01753 0.01070 -0.0553 0.4354 0.0229
-2.750 0.2482 0.01712 0.01020 -0.0535 0.4340 0.0231
-2.500 0.2669 0.01681 0.00983 -0.0518 0.4324 0.0233
-2.250 0.2868 0.01649 0.00943 -0.0503 0.4308 0.0234
-2.000 0.3065 0.01626 0.00914 -0.0489 0.4291 0.0237
-1.750 0.3260 0.01609 0.00890 -0.0474 0.4270 0.0238
-1.500 0.3455 0.01600 0.00876 -0.0460 0.4251 0.0240
-1.250 0.3637 0.01595 0.00866 -0.0444 0.4222 0.0242
-1.000 0.3799 0.01607 0.00875 -0.0425 0.4199 0.0244
-0.750 0.4021 0.01595 0.00858 -0.0417 0.4180 0.0244
-0.500 0.4242 0.01595 0.00857 -0.0409 0.4159 0.0246
-0.250 0.4490 0.01581 0.00841 -0.0407 0.4139 0.0248
0.000 0.4715 0.01581 0.00840 -0.0401 0.4116 0.0250
0.250 0.4906 0.01597 0.00855 -0.0389 0.4084 0.0253
0.500 0.5106 0.01610 0.00866 -0.0380 0.4050 0.0257
0.750 0.5317 0.01624 0.00877 -0.0373 0.4020 0.0257
1.000 0.5547 0.01636 0.00891 -0.0369 0.4005 0.0261
1.250 0.5795 0.01645 0.00899 -0.0369 0.3968 0.0264
1.500 0.6031 0.01661 0.00913 -0.0368 0.3941 0.0267
1.750 0.6254 0.01683 0.00933 -0.0365 0.3904 0.0271
2.000 0.6473 0.01713 0.00960 -0.0364 0.3869 0.0275
2.250 0.6788 0.01726 0.00974 -0.0379 0.3839 0.0277
2.500 0.7051 0.01750 0.00997 -0.0385 0.3807 0.0280
2.750 0.7307 0.01781 0.01026 -0.0393 0.3753 0.0283
3.000 0.7501 0.01827 0.01071 -0.0389 0.3717 0.0288
3.250 0.7734 0.01858 0.01103 -0.0391 0.3689 0.0295
3.500 0.7951 0.01892 0.01138 -0.0390 0.3656 0.0299
3.750 0.8136 0.01941 0.01186 -0.0385 0.3618 0.0305
4.000 0.8306 0.01996 0.01240 -0.0378 0.3584 0.0309
4.250 0.8472 0.02055 0.01298 -0.0371 0.3551 0.0318
4.500 0.8668 0.02103 0.01348 -0.0369 0.3521 0.0327
4.750 0.8850 0.02156 0.01402 -0.0365 0.3490 0.0331
5.000 0.8991 0.02232 0.01478 -0.0356 0.3451 0.0343
5.250 0.9125 0.02311 0.01556 -0.0347 0.3419 0.0355
5.500 0.9280 0.02383 0.01630 -0.0341 0.3394 0.0365
5.750 0.9433 0.02458 0.01706 -0.0335 0.3357 0.0371
6.000 0.9593 0.02527 0.01777 -0.0330 0.3334 0.0396
6.250 0.9698 0.02633 0.01883 -0.0320 0.3299 0.0411
6.500 0.9790 0.02744 0.01994 -0.0308 0.3261 0.0433
6.750 0.9926 0.02833 0.02086 -0.0302 0.3243 0.0452
7.000 1.0034 0.02939 0.02192 -0.0294 0.3191 0.0484
7.500 1.0271 0.03145 0.02404 -0.0280 0.3154 0.0595
7.750 1.0349 0.03276 0.02536 -0.0270 0.3124 0.0660
8.250 1.3482 0.03612 0.03079 -0.0857 0.3028 1.0000
8.500 1.3507 0.03789 0.03256 -0.0843 0.2994 1.0000
8.750 1.3573 0.03938 0.03407 -0.0832 0.2985 1.0000
9.000 1.3590 0.04129 0.03599 -0.0819 0.2954 1.0000
9.250 1.3682 0.04264 0.03736 -0.0811 0.2941 1.0000
9.500 1.3747 0.04424 0.03898 -0.0802 0.2923 1.0000
9.750 1.3831 0.04567 0.04044 -0.0795 0.2910 1.0000
10.000 1.3848 0.04771 0.04250 -0.0784 0.2884 1.0000
10.250 1.3886 0.04957 0.04437 -0.0775 0.2865 1.0000
10.500 1.3869 0.05198 0.04680 -0.0763 0.2843 1.0000
10.750 1.3876 0.05417 0.04901 -0.0753 0.2821 1.0000
11.000 1.3899 0.05629 0.05116 -0.0745 0.2803 1.0000
11.250 1.3967 0.05798 0.05288 -0.0740 0.2782 1.0000
11.500 1.4000 0.06001 0.05494 -0.0733 0.2765 1.0000
11.750 1.4031 0.06207 0.05702 -0.0727 0.2748 1.0000
12.000 1.4061 0.06414 0.05912 -0.0720 0.2728 1.0000
12.250 1.4040 0.06675 0.06176 -0.0712 0.2710 1.0000
12.500 1.4017 0.06937 0.06438 -0.0704 0.2682 1.0000
12.750 1.4034 0.07161 0.06666 -0.0698 0.2669 1.0000
13.000 1.4096 0.07342 0.06850 -0.0695 0.2657 1.0000
13.250 1.4181 0.07499 0.07010 -0.0693 0.2650 1.0000
13.500 1.4255 0.07668 0.07182 -0.0691 0.2635 1.0000
13.750 1.4297 0.07871 0.07387 -0.0688 0.2619 1.0000
14.000 1.4310 0.08105 0.07624 -0.0684 0.2600 1.0000
14.250 1.4351 0.08309 0.07829 -0.0681 0.2582 1.0000
14.500 1.4382 0.08522 0.08044 -0.0678 0.2563 1.0000
14.750 1.4331 0.08824 0.08348 -0.0672 0.2540 1.0000
15.000 1.4405 0.08995 0.08522 -0.0672 0.2529 1.0000
15.250 1.4497 0.09146 0.08676 -0.0672 0.2520 1.0000
15.500 1.4579 0.09308 0.08841 -0.0672 0.2508 1.0000
15.750 1.4645 0.09485 0.09021 -0.0672 0.2492 1.0000
16.000 1.4670 0.09710 0.09249 -0.0671 0.2479 1.0000
16.250 1.4697 0.09933 0.09474 -0.0670 0.2458 1.0000
16.500 1.4743 0.10129 0.09672 -0.0670 0.2442 1.0000
16.750 1.4759 0.10360 0.09904 -0.0670 0.2421 1.0000
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