GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 500,000 Max Cl/Cd: 105.85 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe796-il-500000.txt Download as CSV file: xf-goe796-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 796 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3084 0.10346 0.10127 -0.0445 1.0000 0.0407
-10.500 -0.3138 0.09973 0.09756 -0.0448 0.9997 0.0407
-10.250 -0.6917 0.03916 0.03614 -0.0796 0.9930 0.0260
-10.000 -0.6959 0.03092 0.02709 -0.0830 0.9865 0.0254
-9.750 -0.6751 0.02706 0.02275 -0.0851 0.9839 0.0252
-9.500 -0.6504 0.02463 0.01999 -0.0864 0.9810 0.0252
-9.250 -0.6245 0.02278 0.01789 -0.0873 0.9772 0.0253
-9.000 -0.5940 0.02120 0.01608 -0.0888 0.9749 0.0254
-8.750 -0.5617 0.01983 0.01452 -0.0904 0.9731 0.0255
-8.500 -0.5290 0.01866 0.01318 -0.0920 0.9712 0.0257
-8.250 -0.5032 0.01773 0.01213 -0.0919 0.9658 0.0259
-8.000 -0.4744 0.01686 0.01113 -0.0924 0.9617 0.0261
-7.750 -0.4443 0.01604 0.01020 -0.0931 0.9584 0.0263
-7.500 -0.4201 0.01539 0.00946 -0.0924 0.9517 0.0265
-7.250 -0.3937 0.01476 0.00874 -0.0922 0.9461 0.0267
-7.000 -0.3681 0.01420 0.00809 -0.0917 0.9404 0.0270
-6.750 -0.3436 0.01369 0.00751 -0.0909 0.9329 0.0272
-6.500 -0.3178 0.01321 0.00695 -0.0904 0.9271 0.0275
-6.250 -0.2932 0.01279 0.00647 -0.0896 0.9184 0.0278
-6.000 -0.2677 0.01229 0.00589 -0.0890 0.9120 0.0287
-5.750 -0.2422 0.01191 0.00549 -0.0884 0.9027 0.0299
-5.500 -0.2158 0.01159 0.00512 -0.0880 0.8953 0.0313
-5.250 -0.1894 0.01129 0.00477 -0.0875 0.8856 0.0332
-5.000 -0.1628 0.01096 0.00445 -0.0871 0.8767 0.0382
-4.750 -0.1360 0.01069 0.00416 -0.0868 0.8677 0.0475
-4.500 -0.1090 0.01045 0.00391 -0.0865 0.8577 0.0558
-4.250 -0.0816 0.01028 0.00368 -0.0863 0.8486 0.0621
-4.000 -0.0542 0.01010 0.00350 -0.0861 0.8386 0.0688
-3.750 -0.0267 0.00997 0.00337 -0.0860 0.8286 0.0767
-3.500 0.0010 0.00987 0.00322 -0.0858 0.8190 0.0838
-3.250 0.0287 0.00979 0.00313 -0.0857 0.8084 0.0927
-3.000 0.0565 0.00970 0.00301 -0.0856 0.7988 0.1007
-2.500 0.1122 0.00956 0.00280 -0.0855 0.7811 0.1169
-2.250 0.1401 0.00950 0.00269 -0.0854 0.7732 0.1238
-2.000 0.1681 0.00943 0.00260 -0.0854 0.7647 0.1298
-1.750 0.1959 0.00935 0.00251 -0.0853 0.7570 0.1385
-1.500 0.2238 0.00927 0.00244 -0.0853 0.7493 0.1488
-1.250 0.2516 0.00920 0.00237 -0.0853 0.7421 0.1624
-1.000 0.2794 0.00907 0.00232 -0.0853 0.7341 0.1818
-0.750 0.3068 0.00894 0.00226 -0.0852 0.7270 0.2201
-0.500 0.3339 0.00865 0.00225 -0.0852 0.7199 0.2978
-0.250 0.3599 0.00826 0.00223 -0.0850 0.7138 0.4256
0.000 0.3840 0.00767 0.00227 -0.0845 0.7078 0.6159
0.250 0.4047 0.00711 0.00234 -0.0827 0.7017 0.8063
0.500 0.4400 0.00700 0.00248 -0.0835 0.6963 0.9564
0.750 0.4915 0.00707 0.00253 -0.0885 0.6888 0.9882
1.000 0.5421 0.00716 0.00252 -0.0935 0.6803 0.9992
1.250 0.5700 0.00719 0.00252 -0.0935 0.6717 1.0000
1.500 0.5957 0.00726 0.00252 -0.0930 0.6646 1.0000
1.750 0.6213 0.00730 0.00254 -0.0925 0.6567 1.0000
2.000 0.6469 0.00738 0.00255 -0.0920 0.6497 1.0000
2.250 0.6726 0.00742 0.00259 -0.0915 0.6411 1.0000
2.500 0.6979 0.00750 0.00262 -0.0910 0.6323 1.0000
2.750 0.7231 0.00757 0.00265 -0.0904 0.6214 1.0000
3.000 0.7485 0.00764 0.00271 -0.0898 0.6109 1.0000
3.250 0.7736 0.00774 0.00276 -0.0892 0.6005 1.0000
3.500 0.7984 0.00785 0.00282 -0.0886 0.5882 1.0000
3.750 0.8232 0.00796 0.00290 -0.0879 0.5739 1.0000
4.000 0.8477 0.00809 0.00299 -0.0872 0.5580 1.0000
4.250 0.8720 0.00825 0.00309 -0.0865 0.5394 1.0000
4.500 0.8955 0.00846 0.00322 -0.0856 0.5153 1.0000
4.750 0.9183 0.00872 0.00337 -0.0847 0.4883 1.0000
5.000 0.9405 0.00905 0.00356 -0.0836 0.4594 1.0000
5.250 0.9623 0.00941 0.00379 -0.0825 0.4316 1.0000
5.500 0.9836 0.00983 0.00406 -0.0814 0.4043 1.0000
5.750 1.0059 0.01019 0.00431 -0.0805 0.3822 1.0000
6.000 1.0287 0.01052 0.00457 -0.0796 0.3659 1.0000
6.250 1.0519 0.01083 0.00484 -0.0788 0.3528 1.0000
6.500 1.0748 0.01115 0.00512 -0.0780 0.3406 1.0000
6.750 1.0976 0.01147 0.00540 -0.0772 0.3276 1.0000
7.000 1.1205 0.01178 0.00567 -0.0764 0.3133 1.0000
7.250 1.1432 0.01210 0.00596 -0.0756 0.2987 1.0000
7.500 1.1654 0.01243 0.00626 -0.0748 0.2829 1.0000
7.750 1.1868 0.01280 0.00657 -0.0737 0.2633 1.0000
8.000 1.2065 0.01327 0.00692 -0.0725 0.2351 1.0000
8.250 1.2233 0.01391 0.00738 -0.0708 0.2016 1.0000
8.500 1.2393 0.01456 0.00791 -0.0690 0.1813 1.0000
8.750 1.2561 0.01514 0.00844 -0.0673 0.1685 1.0000
9.000 1.2723 0.01566 0.00894 -0.0655 0.1587 1.0000
9.250 1.2864 0.01627 0.00951 -0.0633 0.1490 1.0000
9.500 1.3043 0.01670 0.00977 -0.0618 0.1406 1.0000
9.750 1.3202 0.01726 0.01053 -0.0600 0.1319 1.0000
10.000 1.3358 0.01786 0.01110 -0.0583 0.1211 1.0000
10.250 1.3518 0.01845 0.01168 -0.0567 0.1099 1.0000
10.500 1.3660 0.01915 0.01236 -0.0550 0.0989 1.0000
10.750 1.3794 0.01993 0.01311 -0.0532 0.0895 1.0000
11.000 1.3915 0.02080 0.01396 -0.0513 0.0814 1.0000
11.250 1.4042 0.02166 0.01483 -0.0496 0.0745 1.0000
11.500 1.4161 0.02260 0.01578 -0.0478 0.0677 1.0000
11.750 1.4257 0.02372 0.01688 -0.0459 0.0601 1.0000
12.000 1.4361 0.02481 0.01797 -0.0442 0.0520 1.0000
12.250 1.4436 0.02615 0.01929 -0.0424 0.0425 1.0000
12.500 1.4484 0.02774 0.02083 -0.0404 0.0336 1.0000
12.750 1.4533 0.02939 0.02248 -0.0386 0.0283 1.0000
13.000 1.4585 0.03109 0.02422 -0.0369 0.0251 1.0000
13.250 1.4609 0.03308 0.02625 -0.0353 0.0228 1.0000
13.500 1.4644 0.03504 0.02830 -0.0339 0.0213 1.0000
13.750 1.4684 0.03702 0.03037 -0.0327 0.0201 1.0000
14.000 1.4695 0.03933 0.03276 -0.0315 0.0191 1.0000
14.250 1.4662 0.04214 0.03565 -0.0303 0.0182 1.0000
14.500 1.4641 0.04495 0.03858 -0.0294 0.0175 1.0000
14.750 1.4662 0.04739 0.04113 -0.0288 0.0169 1.0000
15.000 1.4667 0.05008 0.04393 -0.0282 0.0163 1.0000
15.250 1.4658 0.05301 0.04695 -0.0279 0.0157 1.0000
15.500 1.4629 0.05626 0.05029 -0.0277 0.0152 1.0000
15.750 1.4555 0.06014 0.05426 -0.0277 0.0147 1.0000
16.000 1.4427 0.06484 0.05907 -0.0279 0.0143 1.0000
16.250 1.4377 0.06871 0.06306 -0.0283 0.0139 1.0000
16.500 1.4357 0.07227 0.06673 -0.0288 0.0135 1.0000
16.750 1.4310 0.07627 0.07086 -0.0295 0.0131 1.0000
17.000 1.4252 0.08052 0.07522 -0.0303 0.0128 1.0000
17.250 1.4185 0.08502 0.07984 -0.0314 0.0125 1.0000
17.500 1.4107 0.08975 0.08467 -0.0327 0.0122 1.0000
17.750 1.4020 0.09467 0.08969 -0.0341 0.0119 1.0000
18.000 1.3924 0.09983 0.09495 -0.0358 0.0117 1.0000
18.250 1.3818 0.10519 0.10041 -0.0376 0.0115 1.0000
18.500 1.3698 0.11078 0.10608 -0.0395 0.0113 1.0000
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Polar data table (+)
Polar graphs
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