GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 200,000 Max Cl/Cd: 71.26 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe398-il-200000.txt Download as CSV file: xf-goe398-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2981 0.11009 0.10657 -0.0414 1.0000 0.0675
-10.250 -0.3410 0.10814 0.10476 -0.0423 1.0000 0.0686
-10.000 -0.3670 0.10532 0.10204 -0.0427 0.9992 0.0689
-9.750 -0.3352 0.10236 0.09905 -0.0404 0.9978 0.0699
-9.500 -0.3065 0.09985 0.09653 -0.0414 0.9952 0.0720
-9.250 -0.2901 0.09568 0.09235 -0.0467 0.9907 0.0755
-9.000 -0.3051 0.08584 0.08255 -0.0641 0.9809 0.0790
-8.750 -0.2752 0.08400 0.08069 -0.0620 0.9779 0.0802
-8.500 -0.2514 0.08108 0.07775 -0.0644 0.9735 0.0820
-8.250 -0.2369 0.07688 0.07355 -0.0701 0.9666 0.0854
-8.000 -0.2620 0.06374 0.06024 -0.0914 0.9471 0.0905
-7.750 -0.3036 0.04427 0.03970 -0.1000 0.9314 0.0694
-7.500 -0.2977 0.03431 0.02869 -0.1017 0.9265 0.0601
-7.250 -0.2855 0.03164 0.02563 -0.1000 0.9166 0.0602
-7.000 -0.2582 0.02874 0.02246 -0.1012 0.9127 0.0615
-6.750 -0.2217 0.02722 0.02090 -0.1034 0.9102 0.0631
-6.500 -0.2038 0.02575 0.01918 -0.1017 0.9006 0.0639
-6.250 -0.1715 0.02397 0.01709 -0.1026 0.8957 0.0651
-6.000 -0.1401 0.02267 0.01547 -0.1031 0.8901 0.0674
-5.750 -0.1162 0.02183 0.01430 -0.1019 0.8811 0.0688
-5.500 -0.0810 0.02011 0.01252 -0.1033 0.8763 0.0708
-5.250 -0.0581 0.01942 0.01179 -0.1021 0.8664 0.0728
-5.000 -0.0257 0.01866 0.01089 -0.1026 0.8599 0.0761
-4.750 -0.0007 0.01807 0.01015 -0.1017 0.8515 0.0789
-4.500 0.0268 0.01720 0.00934 -0.1014 0.8444 0.0825
-4.250 0.0566 0.01665 0.00872 -0.1015 0.8384 0.0870
-4.000 0.0781 0.01611 0.00820 -0.1000 0.8295 0.0924
-3.750 0.1078 0.01564 0.00768 -0.1000 0.8236 0.1006
-3.500 0.1285 0.01518 0.00731 -0.0985 0.8153 0.1099
-3.250 0.1544 0.01474 0.00690 -0.0978 0.8082 0.1249
-3.000 0.1797 0.01440 0.00660 -0.0971 0.8012 0.1461
-2.750 0.2027 0.01413 0.00646 -0.0959 0.7929 0.1737
-2.500 0.2315 0.01382 0.00619 -0.0958 0.7871 0.2128
-2.250 0.2511 0.01358 0.00610 -0.0941 0.7783 0.2481
-2.000 0.2765 0.01320 0.00589 -0.0934 0.7714 0.2931
-1.750 0.2971 0.01288 0.00585 -0.0919 0.7632 0.3612
-1.500 0.3171 0.01241 0.00578 -0.0901 0.7553 0.4763
-1.250 0.3356 0.01194 0.00577 -0.0878 0.7481 0.6093
-1.000 0.3780 0.01125 0.00581 -0.0898 0.7397 0.8294
-0.750 0.5030 0.01122 0.00569 -0.1089 0.7317 0.9635
-0.500 0.5796 0.01127 0.00559 -0.1187 0.7211 1.0000
-0.250 0.6003 0.01128 0.00547 -0.1172 0.7115 1.0000
0.000 0.6216 0.01128 0.00535 -0.1158 0.7012 1.0000
0.250 0.6416 0.01133 0.00532 -0.1141 0.6901 1.0000
0.500 0.6645 0.01137 0.00521 -0.1129 0.6798 1.0000
0.750 0.6847 0.01142 0.00519 -0.1112 0.6674 1.0000
1.000 0.7054 0.01150 0.00517 -0.1096 0.6546 1.0000
1.250 0.7271 0.01158 0.00514 -0.1081 0.6419 1.0000
1.500 0.7492 0.01167 0.00509 -0.1067 0.6288 1.0000
1.750 0.7691 0.01178 0.00512 -0.1050 0.6142 1.0000
2.000 0.7893 0.01191 0.00517 -0.1033 0.5996 1.0000
2.250 0.8098 0.01205 0.00523 -0.1016 0.5854 1.0000
2.500 0.8307 0.01221 0.00529 -0.1001 0.5719 1.0000
2.750 0.8518 0.01238 0.00535 -0.0986 0.5587 1.0000
3.000 0.8722 0.01256 0.00546 -0.0970 0.5454 1.0000
3.250 0.8925 0.01276 0.00560 -0.0954 0.5324 1.0000
3.500 0.9133 0.01297 0.00573 -0.0939 0.5207 1.0000
3.750 0.9347 0.01322 0.00586 -0.0926 0.5101 1.0000
4.000 0.9547 0.01344 0.00606 -0.0910 0.4983 1.0000
4.250 0.9755 0.01371 0.00626 -0.0895 0.4879 1.0000
4.500 0.9966 0.01400 0.00645 -0.0882 0.4778 1.0000
4.750 1.0169 0.01427 0.00672 -0.0867 0.4679 1.0000
5.000 1.0390 0.01462 0.00694 -0.0856 0.4590 1.0000
5.250 1.0584 0.01490 0.00725 -0.0840 0.4493 1.0000
5.500 1.0802 0.01526 0.00753 -0.0828 0.4405 1.0000
5.750 1.0992 0.01556 0.00785 -0.0811 0.4309 1.0000
6.000 1.1200 0.01594 0.00817 -0.0799 0.4219 1.0000
6.250 1.1388 0.01626 0.00850 -0.0782 0.4125 1.0000
6.500 1.1586 0.01665 0.00886 -0.0767 0.4037 1.0000
6.750 1.1770 0.01699 0.00919 -0.0750 0.3946 1.0000
7.000 1.1957 0.01738 0.00959 -0.0734 0.3858 1.0000
7.250 1.2135 0.01774 0.00994 -0.0716 0.3770 1.0000
7.500 1.2303 0.01812 0.01034 -0.0696 0.3680 1.0000
7.750 1.2465 0.01848 0.01066 -0.0676 0.3588 1.0000
8.000 1.2591 0.01883 0.01107 -0.0649 0.3489 1.0000
8.250 1.2733 0.01922 0.01138 -0.0625 0.3397 1.0000
8.500 1.2809 0.01953 0.01178 -0.0589 0.3303 1.0000
8.750 1.2937 0.01997 0.01216 -0.0564 0.3221 1.0000
9.000 1.3043 0.02036 0.01264 -0.0535 0.3137 1.0000
9.250 1.3177 0.02086 0.01308 -0.0513 0.3062 1.0000
9.500 1.3287 0.02133 0.01363 -0.0487 0.2982 1.0000
9.750 1.3436 0.02190 0.01412 -0.0469 0.2916 1.0000
10.000 1.3552 0.02243 0.01479 -0.0446 0.2846 1.0000
10.250 1.3678 0.02303 0.01534 -0.0425 0.2779 1.0000
10.500 1.3795 0.02366 0.01605 -0.0405 0.2712 1.0000
10.750 1.3905 0.02431 0.01674 -0.0384 0.2646 1.0000
11.000 1.4034 0.02503 0.01746 -0.0366 0.2586 1.0000
11.250 1.4133 0.02577 0.01832 -0.0346 0.2524 1.0000
11.500 1.4239 0.02658 0.01908 -0.0328 0.2461 1.0000
11.750 1.4331 0.02743 0.02007 -0.0309 0.2401 1.0000
12.000 1.4403 0.02839 0.02108 -0.0289 0.2333 1.0000
12.250 1.4489 0.02939 0.02212 -0.0272 0.2273 1.0000
12.500 1.4556 0.03049 0.02335 -0.0255 0.2206 1.0000
12.750 1.4619 0.03170 0.02453 -0.0238 0.2142 1.0000
13.000 1.4666 0.03303 0.02606 -0.0222 0.2068 1.0000
13.250 1.4683 0.03463 0.02766 -0.0206 0.1989 1.0000
13.500 1.4697 0.03636 0.02954 -0.0192 0.1892 1.0000
13.750 1.4686 0.03841 0.03167 -0.0179 0.1780 1.0000
14.000 1.4645 0.04088 0.03418 -0.0167 0.1644 1.0000
14.250 1.4554 0.04397 0.03727 -0.0157 0.1470 1.0000
14.500 1.4438 0.04754 0.04080 -0.0149 0.1278 1.0000
14.750 1.4291 0.05163 0.04481 -0.0143 0.1114 1.0000
15.000 1.4151 0.05583 0.04898 -0.0140 0.1017 1.0000
15.250 1.4004 0.06029 0.05343 -0.0140 0.0953 1.0000
15.500 1.3896 0.06442 0.05760 -0.0141 0.0907 1.0000
15.750 1.3766 0.06894 0.06213 -0.0145 0.0873 1.0000
16.000 1.3687 0.07292 0.06617 -0.0148 0.0845 1.0000
16.250 1.3622 0.07677 0.07010 -0.0152 0.0817 1.0000
16.500 1.3553 0.08070 0.07406 -0.0157 0.0793 1.0000
16.750 1.3493 0.08431 0.07761 -0.0159 0.0768 1.0000
17.000 1.3484 0.08747 0.08087 -0.0163 0.0749 1.0000
17.250 1.3475 0.09065 0.08413 -0.0167 0.0728 1.0000
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