GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 360 AIRFOIL (goe360-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.26 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe360-il-1000000-n5.txt Download as CSV file: xf-goe360-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 360 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2758 0.09914 0.09703 -0.0280 0.8269 0.0080
-9.000 -0.2696 0.09589 0.09375 -0.0297 0.8143 0.0083
-8.750 -0.2709 0.09046 0.08829 -0.0325 0.8027 0.0092
-8.500 -0.2615 0.08810 0.08588 -0.0340 0.7866 0.0094
-8.250 -0.2523 0.08564 0.08335 -0.0357 0.7682 0.0095
-8.000 -0.2429 0.08313 0.08076 -0.0376 0.7453 0.0097
-7.750 -0.2341 0.08051 0.07803 -0.0399 0.7181 0.0099
-7.500 -0.2211 0.07738 0.07479 -0.0437 0.6905 0.0102
-7.250 -0.2067 0.07377 0.07108 -0.0482 0.6695 0.0106
-7.000 -0.1915 0.06729 0.06452 -0.0565 0.6564 0.0117
-6.750 -0.1717 0.06487 0.06201 -0.0597 0.6427 0.0119
-6.500 -0.1508 0.06223 0.05931 -0.0632 0.6322 0.0121
-6.250 -0.1288 0.05933 0.05634 -0.0669 0.6240 0.0124
-6.000 -0.1054 0.05607 0.05300 -0.0710 0.6166 0.0128
-5.750 -0.0760 0.04869 0.04545 -0.0792 0.6113 0.0145
-5.500 -0.0514 0.04657 0.04326 -0.0814 0.6051 0.0147
-5.250 -0.0263 0.04456 0.04117 -0.0834 0.5987 0.0149
-5.000 -0.0002 0.04233 0.03885 -0.0855 0.5929 0.0152
-4.750 0.0268 0.03985 0.03627 -0.0876 0.5868 0.0156
-4.500 0.0547 0.03710 0.03338 -0.0897 0.5811 0.0163
-4.250 0.0890 0.03062 0.02653 -0.0931 0.5772 0.0178
-4.000 0.1154 0.02884 0.02464 -0.0940 0.5711 0.0180
-3.500 0.1687 0.02646 0.02205 -0.0952 0.5576 0.0185
-3.250 0.1959 0.02523 0.02071 -0.0957 0.5507 0.0190
-3.000 0.2240 0.02345 0.01876 -0.0961 0.5446 0.0194
-2.750 0.2525 0.02155 0.01665 -0.0965 0.5367 0.0199
-2.500 0.2811 0.01963 0.01449 -0.0967 0.5286 0.0202
-2.250 0.3096 0.01768 0.01227 -0.0968 0.5190 0.0205
-2.000 0.3385 0.01542 0.00968 -0.0967 0.5103 0.0212
-1.750 0.3665 0.01351 0.00742 -0.0966 0.5008 0.0219
-1.500 0.3942 0.01279 0.00653 -0.0967 0.4893 0.0222
-1.250 0.4220 0.01234 0.00595 -0.0968 0.4768 0.0224
-1.000 0.4497 0.01194 0.00542 -0.0968 0.4637 0.0226
-0.750 0.4774 0.01155 0.00490 -0.0968 0.4519 0.0228
-0.500 0.5050 0.01118 0.00442 -0.0968 0.4411 0.0229
-0.250 0.5328 0.01092 0.00408 -0.0969 0.4313 0.0232
0.000 0.5606 0.01073 0.00382 -0.0969 0.4218 0.0236
0.250 0.5881 0.01046 0.00345 -0.0969 0.4118 0.0238
0.500 0.6158 0.01021 0.00314 -0.0969 0.4030 0.0241
0.750 0.6433 0.01005 0.00292 -0.0968 0.3949 0.0245
1.000 0.6711 0.00990 0.00274 -0.0969 0.3880 0.0250
1.250 0.6987 0.00983 0.00262 -0.0969 0.3809 0.0255
1.500 0.7266 0.00976 0.00253 -0.0970 0.3746 0.0260
1.750 0.7542 0.00975 0.00248 -0.0970 0.3673 0.0264
2.000 0.7819 0.00974 0.00245 -0.0971 0.3611 0.0266
2.250 0.8096 0.00975 0.00244 -0.0971 0.3549 0.0268
2.500 0.8372 0.00971 0.00236 -0.0972 0.3494 0.0273
2.750 0.8650 0.00967 0.00233 -0.0973 0.3450 0.0285
3.000 0.8927 0.00971 0.00235 -0.0973 0.3398 0.0293
3.250 0.9201 0.00978 0.00241 -0.0973 0.3344 0.0301
3.500 0.9477 0.00983 0.00245 -0.0974 0.3301 0.0312
3.750 0.9752 0.00990 0.00252 -0.0975 0.3254 0.0325
4.000 1.0025 0.00999 0.00261 -0.0975 0.3211 0.0336
4.250 1.0299 0.01008 0.00270 -0.0975 0.3176 0.0359
4.500 1.0574 0.01015 0.00281 -0.0976 0.3143 0.0425
4.750 1.0806 0.00871 0.00316 -0.0972 0.3107 1.0000
5.000 1.1075 0.00887 0.00329 -0.0972 0.3065 1.0000
5.250 1.1345 0.00903 0.00343 -0.0972 0.3028 1.0000
5.500 1.1615 0.00916 0.00357 -0.0972 0.2985 1.0000
5.750 1.1878 0.00939 0.00374 -0.0971 0.2904 1.0000
6.000 1.2144 0.00955 0.00390 -0.0971 0.2842 1.0000
6.250 1.2408 0.00975 0.00407 -0.0971 0.2782 1.0000
6.500 1.2669 0.00996 0.00427 -0.0970 0.2716 1.0000
6.750 1.2925 0.01020 0.00448 -0.0968 0.2618 1.0000
7.000 1.3183 0.01043 0.00469 -0.0967 0.2535 1.0000
7.250 1.3430 0.01075 0.00495 -0.0964 0.2402 1.0000
7.500 1.3671 0.01112 0.00524 -0.0961 0.2249 1.0000
7.750 1.3889 0.01169 0.00567 -0.0955 0.1993 1.0000
8.000 1.3924 0.01394 0.00723 -0.0924 0.0944 1.0000
8.250 1.4006 0.01563 0.00855 -0.0898 0.0308 1.0000
8.500 1.4186 0.01638 0.00923 -0.0886 0.0174 1.0000
8.750 1.4394 0.01685 0.00973 -0.0878 0.0148 1.0000
9.000 1.4593 0.01736 0.01025 -0.0869 0.0133 1.0000
9.250 1.4780 0.01792 0.01083 -0.0858 0.0117 1.0000
9.500 1.4970 0.01840 0.01135 -0.0848 0.0111 1.0000
9.750 1.5131 0.01894 0.01192 -0.0832 0.0103 1.0000
10.000 1.5276 0.01955 0.01258 -0.0815 0.0096 1.0000
10.250 1.5407 0.02028 0.01334 -0.0797 0.0090 1.0000
10.500 1.5529 0.02108 0.01420 -0.0780 0.0085 1.0000
10.750 1.5661 0.02188 0.01504 -0.0765 0.0082 1.0000
11.000 1.5784 0.02277 0.01599 -0.0750 0.0079 1.0000
11.250 1.5899 0.02375 0.01703 -0.0736 0.0075 1.0000
11.500 1.6005 0.02486 0.01819 -0.0722 0.0071 1.0000
11.750 1.6098 0.02610 0.01947 -0.0709 0.0068 1.0000
12.000 1.6172 0.02756 0.02099 -0.0695 0.0064 1.0000
12.250 1.6224 0.02926 0.02277 -0.0682 0.0061 1.0000
12.500 1.6294 0.03088 0.02447 -0.0671 0.0060 1.0000
12.750 1.6352 0.03269 0.02636 -0.0661 0.0059 1.0000
13.000 1.6395 0.03471 0.02846 -0.0652 0.0057 1.0000
13.250 1.6426 0.03695 0.03079 -0.0645 0.0056 1.0000
13.500 1.6445 0.03942 0.03335 -0.0639 0.0054 1.0000
13.750 1.6451 0.04212 0.03613 -0.0635 0.0053 1.0000
14.000 1.6444 0.04505 0.03915 -0.0632 0.0051 1.0000
14.250 1.6424 0.04822 0.04241 -0.0631 0.0050 1.0000
14.500 1.6387 0.05163 0.04591 -0.0630 0.0049 1.0000
14.750 1.6339 0.05527 0.04965 -0.0631 0.0048 1.0000
15.000 1.6278 0.05916 0.05363 -0.0633 0.0047 1.0000
15.250 1.6197 0.06337 0.05795 -0.0636 0.0047 1.0000
15.500 1.6103 0.06783 0.06250 -0.0641 0.0046 1.0000
15.750 1.5995 0.07260 0.06738 -0.0647 0.0045 1.0000
16.000 1.5874 0.07765 0.07254 -0.0655 0.0044 1.0000
16.250 1.5741 0.08295 0.07795 -0.0664 0.0044 1.0000
16.500 1.5610 0.08833 0.08344 -0.0674 0.0043 1.0000
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