GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il) Reynolds number: 100,000 Max Cl/Cd: 59.54 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe602m-il-100000-n5.txt Download as CSV file: xf-goe602m-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 MOD. 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 -0.3669 0.09228 0.08758 -0.0373 1.0000 0.0288
-8.250 -0.3753 0.08925 0.08464 -0.0369 1.0000 0.0284
-8.000 -0.3873 0.08637 0.08186 -0.0359 1.0000 0.0279
-7.750 -0.4029 0.08385 0.07945 -0.0342 1.0000 0.0276
-7.500 -0.4208 0.08090 0.07661 -0.0331 1.0000 0.0270
-7.250 -0.4328 0.07708 0.07288 -0.0338 1.0000 0.0267
-7.000 -0.4412 0.07272 0.06858 -0.0357 1.0000 0.0265
-6.750 -0.4307 0.06794 0.06377 -0.0408 0.9971 0.0273
-6.500 -0.4061 0.05999 0.05568 -0.0517 0.9906 0.0283
-6.250 -0.3803 0.05108 0.04643 -0.0622 0.9843 0.0292
-6.000 -0.3537 0.04291 0.03769 -0.0701 0.9782 0.0298
-5.750 -0.3264 0.03676 0.03083 -0.0746 0.9727 0.0309
-5.500 -0.2953 0.03244 0.02565 -0.0777 0.9679 0.0339
-5.250 -0.2635 0.02901 0.02144 -0.0798 0.9638 0.0364
-5.000 -0.2354 0.02689 0.01906 -0.0809 0.9583 0.0391
-4.750 -0.2014 0.02548 0.01731 -0.0826 0.9543 0.0443
-4.500 -0.1701 0.02387 0.01525 -0.0833 0.9494 0.0471
-4.250 -0.1400 0.02256 0.01382 -0.0842 0.9438 0.0520
-4.000 -0.1047 0.02152 0.01261 -0.0858 0.9398 0.0558
-3.750 -0.0750 0.02066 0.01158 -0.0861 0.9336 0.0589
-3.500 -0.0425 0.01991 0.01075 -0.0872 0.9281 0.0643
-3.250 -0.0051 0.01919 0.00995 -0.0891 0.9244 0.0688
-3.000 0.0220 0.01868 0.00931 -0.0889 0.9160 0.0732
-2.750 0.0590 0.01805 0.00864 -0.0906 0.9115 0.0827
-2.500 0.0887 0.01750 0.00809 -0.0910 0.9039 0.1054
-2.250 0.1234 0.01670 0.00755 -0.0925 0.8984 0.1684
-2.000 0.1559 0.01616 0.00739 -0.0936 0.8918 0.2978
-1.750 0.1868 0.01569 0.00722 -0.0943 0.8846 0.3856
-1.500 0.2169 0.01532 0.00715 -0.0945 0.8772 0.4748
-1.250 0.2482 0.01501 0.00699 -0.0949 0.8697 0.5519
-1.000 0.2770 0.01473 0.00678 -0.0948 0.8610 0.6054
-0.750 0.3081 0.01422 0.00656 -0.0948 0.8542 0.6856
-0.500 0.3558 0.01355 0.00633 -0.0980 0.8465 1.0000
-0.250 0.3904 0.01345 0.00605 -0.0991 0.8386 1.0000
0.000 0.4181 0.01345 0.00592 -0.0989 0.8271 1.0000
0.250 0.4465 0.01345 0.00579 -0.0989 0.8155 1.0000
0.500 0.4759 0.01343 0.00566 -0.0990 0.8039 1.0000
0.750 0.5061 0.01341 0.00553 -0.0992 0.7924 1.0000
1.000 0.5366 0.01338 0.00541 -0.0994 0.7805 1.0000
1.250 0.5664 0.01338 0.00532 -0.0995 0.7676 1.0000
1.500 0.5951 0.01341 0.00528 -0.0995 0.7535 1.0000
1.750 0.6238 0.01345 0.00526 -0.0994 0.7390 1.0000
2.000 0.6523 0.01352 0.00525 -0.0992 0.7240 1.0000
2.250 0.6798 0.01362 0.00530 -0.0989 0.7080 1.0000
2.500 0.7067 0.01374 0.00537 -0.0986 0.6913 1.0000
2.750 0.7333 0.01388 0.00547 -0.0981 0.6740 1.0000
3.000 0.7597 0.01405 0.00560 -0.0976 0.6566 1.0000
3.250 0.7859 0.01424 0.00574 -0.0971 0.6394 1.0000
3.500 0.8118 0.01444 0.00590 -0.0965 0.6221 1.0000
3.750 0.8364 0.01468 0.00612 -0.0958 0.6032 1.0000
4.000 0.8609 0.01493 0.00637 -0.0950 0.5841 1.0000
4.250 0.8852 0.01520 0.00660 -0.0941 0.5651 1.0000
4.500 0.9090 0.01549 0.00689 -0.0932 0.5462 1.0000
4.750 0.9324 0.01579 0.00723 -0.0923 0.5275 1.0000
5.000 0.9559 0.01612 0.00757 -0.0914 0.5094 1.0000
5.250 0.9789 0.01646 0.00792 -0.0904 0.4914 1.0000
5.500 1.0014 0.01682 0.00833 -0.0894 0.4725 1.0000
5.750 1.0213 0.01723 0.00873 -0.0878 0.4450 1.0000
6.000 1.0369 0.01775 0.00907 -0.0855 0.4010 1.0000
6.250 1.0516 0.01838 0.00949 -0.0833 0.3502 1.0000
6.500 1.0675 0.01906 0.01001 -0.0813 0.3052 1.0000
6.750 1.0816 0.01993 0.01064 -0.0791 0.2536 1.0000
7.000 1.0919 0.02118 0.01147 -0.0766 0.1844 1.0000
7.250 1.0990 0.02285 0.01263 -0.0738 0.1072 1.0000
7.500 1.1053 0.02462 0.01396 -0.0709 0.0416 1.0000
7.750 1.1152 0.02602 0.01525 -0.0683 0.0318 1.0000
8.000 1.1239 0.02736 0.01668 -0.0654 0.0278 1.0000
8.250 1.1341 0.02849 0.01798 -0.0628 0.0254 1.0000
8.500 1.1432 0.02969 0.01938 -0.0601 0.0238 1.0000
8.750 1.1505 0.03102 0.02089 -0.0574 0.0228 1.0000
9.000 1.1561 0.03247 0.02252 -0.0546 0.0219 1.0000
9.250 1.1598 0.03408 0.02430 -0.0518 0.0211 1.0000
9.500 1.1619 0.03588 0.02625 -0.0491 0.0202 1.0000
9.750 1.1621 0.03791 0.02841 -0.0466 0.0193 1.0000
10.000 1.1605 0.04030 0.03091 -0.0441 0.0184 1.0000
10.250 1.1609 0.04300 0.03373 -0.0418 0.0176 1.0000
10.500 1.1700 0.04493 0.03580 -0.0403 0.0173 1.0000
10.750 1.1805 0.04695 0.03796 -0.0389 0.0170 1.0000
11.000 1.1921 0.04907 0.04024 -0.0376 0.0168 1.0000
11.250 1.2037 0.05139 0.04275 -0.0363 0.0165 1.0000
11.500 1.2139 0.05392 0.04548 -0.0351 0.0163 1.0000
11.750 1.2204 0.05661 0.04842 -0.0339 0.0160 1.0000
12.000 1.2231 0.05949 0.05155 -0.0328 0.0157 1.0000
12.250 1.2225 0.06261 0.05494 -0.0319 0.0153 1.0000
12.500 1.2189 0.06597 0.05856 -0.0312 0.0149 1.0000
12.750 1.2133 0.06971 0.06255 -0.0309 0.0147 1.0000
13.000 1.2054 0.07374 0.06684 -0.0310 0.0144 1.0000
13.250 1.1956 0.07818 0.07153 -0.0316 0.0143 1.0000
13.500 1.1838 0.08308 0.07668 -0.0327 0.0142 1.0000
13.750 1.1706 0.08840 0.08224 -0.0345 0.0142 1.0000
14.000 1.1560 0.09423 0.08831 -0.0369 0.0142 1.0000
14.250 1.1404 0.10059 0.09489 -0.0399 0.0142 1.0000
14.500 1.1241 0.10752 0.10203 -0.0437 0.0143 1.0000
14.750 1.1070 0.11511 0.10982 -0.0482 0.0144 1.0000
15.000 1.0896 0.12334 0.11823 -0.0533 0.0146 1.0000
15.250 1.0717 0.13232 0.12738 -0.0591 0.0148 1.0000
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Polar data table (+)
Polar graphs
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