GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 596 AIRFOIL (goe596-il) Reynolds number: 200,000 Max Cl/Cd: 77.55 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe596-il-200000.txt Download as CSV file: xf-goe596-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 596 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3569 0.08977 0.08632 -0.0377 1.0000 0.0515
-8.000 -0.3756 0.08793 0.08458 -0.0380 1.0000 0.0517
-7.750 -0.3904 0.08560 0.08230 -0.0390 1.0000 0.0519
-7.500 -0.4044 0.08316 0.07986 -0.0393 1.0000 0.0520
-7.250 -0.4113 0.07911 0.07589 -0.0361 1.0000 0.0526
-7.000 -0.4124 0.07709 0.07394 -0.0316 1.0000 0.0532
-6.750 -0.3980 0.07476 0.07162 -0.0306 0.9980 0.0544
-6.500 -0.3697 0.07072 0.06754 -0.0361 0.9932 0.0566
-6.250 -0.3201 0.06290 0.05916 -0.0570 0.9834 0.0631
-6.000 -0.3022 0.05657 0.05286 -0.0599 0.9769 0.0644
-5.750 -0.2747 0.05375 0.05012 -0.0616 0.9728 0.0660
-5.500 -0.2457 0.05103 0.04735 -0.0645 0.9670 0.0693
-5.250 -0.2085 0.04512 0.04087 -0.0725 0.9592 0.0776
-5.000 -0.1758 0.04227 0.03810 -0.0753 0.9555 0.0798
-4.750 -0.1464 0.03991 0.03564 -0.0772 0.9472 0.0843
-4.500 -0.1069 0.03599 0.03131 -0.0820 0.9430 0.0934
-4.250 -0.0733 0.03522 0.03027 -0.0835 0.9347 0.1044
-4.000 -0.0426 0.03149 0.02656 -0.0860 0.9289 0.1101
-3.750 -0.0126 0.02964 0.02441 -0.0872 0.9196 0.1236
-3.500 0.0205 0.02801 0.02261 -0.0887 0.9119 0.1386
-3.250 0.0467 0.02665 0.02115 -0.0887 0.9000 0.1539
-3.000 0.0860 0.02106 0.01414 -0.0871 0.8907 0.0773
-2.750 0.1166 0.01931 0.01225 -0.0872 0.8798 0.0736
-2.500 0.1438 0.01770 0.01039 -0.0864 0.8657 0.0701
-2.250 0.1716 0.01653 0.00896 -0.0856 0.8510 0.0679
-2.000 0.1989 0.01566 0.00790 -0.0849 0.8357 0.0674
-1.750 0.2258 0.01495 0.00706 -0.0841 0.8196 0.0677
-1.500 0.2520 0.01442 0.00646 -0.0833 0.8026 0.0700
-1.250 0.2780 0.01394 0.00589 -0.0824 0.7855 0.0721
-1.000 0.3037 0.01348 0.00534 -0.0816 0.7690 0.0735
-0.750 0.3292 0.01312 0.00490 -0.0807 0.7535 0.0753
-0.500 0.3539 0.01267 0.00443 -0.0799 0.7388 0.0784
-0.250 0.3791 0.01240 0.00414 -0.0791 0.7249 0.0843
0.000 0.4046 0.01218 0.00389 -0.0784 0.7119 0.0951
0.250 0.4282 0.01155 0.00367 -0.0776 0.7004 0.2178
0.500 0.5030 0.00959 0.00357 -0.0870 0.6884 1.0000
0.750 0.5274 0.00973 0.00355 -0.0861 0.6773 1.0000
1.000 0.5517 0.00989 0.00359 -0.0853 0.6666 1.0000
1.250 0.5764 0.01006 0.00362 -0.0845 0.6572 1.0000
1.500 0.6009 0.01023 0.00369 -0.0837 0.6472 1.0000
1.750 0.6254 0.01042 0.00379 -0.0830 0.6375 1.0000
2.000 0.6506 0.01063 0.00388 -0.0823 0.6289 1.0000
2.250 0.6748 0.01081 0.00404 -0.0815 0.6194 1.0000
2.500 0.7000 0.01104 0.00417 -0.0808 0.6110 1.0000
2.750 0.7244 0.01123 0.00434 -0.0801 0.6012 1.0000
3.000 0.7490 0.01144 0.00451 -0.0793 0.5920 1.0000
3.250 0.7739 0.01165 0.00465 -0.0786 0.5825 1.0000
3.500 0.7978 0.01184 0.00485 -0.0777 0.5715 1.0000
3.750 0.8222 0.01204 0.00501 -0.0770 0.5611 1.0000
4.000 0.8468 0.01223 0.00515 -0.0762 0.5506 1.0000
4.250 0.8705 0.01240 0.00536 -0.0753 0.5390 1.0000
4.500 0.8945 0.01259 0.00553 -0.0744 0.5278 1.0000
4.750 0.9186 0.01277 0.00567 -0.0736 0.5163 1.0000
5.000 0.9420 0.01292 0.00580 -0.0726 0.5030 1.0000
5.250 0.9646 0.01304 0.00595 -0.0715 0.4884 1.0000
5.500 0.9874 0.01318 0.00611 -0.0704 0.4739 1.0000
5.750 1.0100 0.01333 0.00627 -0.0693 0.4587 1.0000
6.000 1.0324 0.01349 0.00645 -0.0682 0.4429 1.0000
6.250 1.0549 0.01369 0.00667 -0.0672 0.4276 1.0000
6.500 1.0768 0.01392 0.00689 -0.0660 0.4113 1.0000
6.750 1.0981 0.01416 0.00714 -0.0648 0.3927 1.0000
7.000 1.1188 0.01446 0.00745 -0.0635 0.3726 1.0000
7.250 1.1377 0.01485 0.00777 -0.0619 0.3492 1.0000
7.500 1.1561 0.01530 0.00817 -0.0603 0.3226 1.0000
7.750 1.1718 0.01588 0.00863 -0.0583 0.2851 1.0000
8.000 1.1811 0.01688 0.00929 -0.0555 0.2140 1.0000
8.250 1.1792 0.01881 0.01056 -0.0513 0.1219 1.0000
8.500 1.1816 0.02043 0.01181 -0.0477 0.0829 1.0000
8.750 1.1894 0.02150 0.01287 -0.0447 0.0741 1.0000
9.000 1.1933 0.02264 0.01402 -0.0411 0.0691 1.0000
9.250 1.2005 0.02364 0.01511 -0.0382 0.0656 1.0000
9.500 1.2047 0.02485 0.01639 -0.0351 0.0625 1.0000
9.750 1.2041 0.02646 0.01799 -0.0318 0.0599 1.0000
10.000 1.2088 0.02786 0.01947 -0.0292 0.0579 1.0000
10.250 1.2160 0.02919 0.02089 -0.0271 0.0558 1.0000
10.500 1.2226 0.03065 0.02241 -0.0252 0.0538 1.0000
10.750 1.2290 0.03225 0.02403 -0.0233 0.0518 1.0000
11.000 1.2370 0.03425 0.02598 -0.0216 0.0495 1.0000
11.250 1.2494 0.03574 0.02757 -0.0202 0.0479 1.0000
11.500 1.2631 0.03716 0.02909 -0.0190 0.0464 1.0000
11.750 1.2768 0.03867 0.03069 -0.0178 0.0446 1.0000
12.000 1.2889 0.04024 0.03230 -0.0167 0.0428 1.0000
12.250 1.3260 0.04288 0.03485 -0.0173 0.0401 1.0000
12.500 1.3320 0.04454 0.03674 -0.0157 0.0395 1.0000
12.750 1.3390 0.04647 0.03889 -0.0142 0.0386 1.0000
13.000 1.3455 0.04859 0.04122 -0.0130 0.0377 1.0000
13.250 1.3505 0.05083 0.04365 -0.0118 0.0366 1.0000
13.500 1.3558 0.05302 0.04598 -0.0108 0.0355 1.0000
13.750 1.3625 0.05526 0.04831 -0.0100 0.0345 1.0000
14.000 1.3693 0.05805 0.05122 -0.0094 0.0338 1.0000
14.250 1.3804 0.06231 0.05563 -0.0090 0.0330 1.0000
14.750 1.3603 0.07102 0.06484 -0.0078 0.0327 1.0000
15.000 1.3436 0.07498 0.06905 -0.0078 0.0326 1.0000
15.250 1.3272 0.07952 0.07382 -0.0083 0.0326 1.0000
15.500 1.3074 0.08435 0.07888 -0.0095 0.0325 1.0000
15.750 1.2902 0.08986 0.08460 -0.0111 0.0326 1.0000
16.000 1.2700 0.09575 0.09070 -0.0134 0.0326 1.0000
16.250 1.2484 0.10197 0.09713 -0.0163 0.0326 1.0000
16.500 1.2301 0.10897 0.10430 -0.0193 0.0327 1.0000
17.000 1.0727 0.14979 0.14606 -0.0495 0.0378 1.0000
17.250 1.0423 0.16398 0.16029 -0.0577 0.0395 1.0000
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