GOE 587 AIRFOIL (goe587-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 587 AIRFOIL (goe587-il) Reynolds number: 50,000 Max Cl/Cd: 36.6 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe587-il-50000.txt Download as CSV file: xf-goe587-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 587 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4746 0.10402 0.09726 -0.0085 1.0000 0.1318
-8.000 -0.4828 0.10249 0.09584 -0.0110 1.0000 0.1352
-7.750 -0.4937 0.10170 0.09516 -0.0156 1.0000 0.1363
-7.500 -0.4737 0.09488 0.08836 -0.0114 1.0000 0.1462
-7.250 -0.4816 0.09389 0.08743 -0.0165 1.0000 0.1497
-7.000 -0.4671 0.08822 0.08181 -0.0133 1.0000 0.1581
-6.750 -0.4719 0.08685 0.08048 -0.0184 1.0000 0.1640
-6.500 -0.4610 0.08217 0.07577 -0.0163 1.0000 0.1754
-6.250 -0.4535 0.07824 0.07189 -0.0157 1.0000 0.1848
-6.000 -0.4479 0.07488 0.06857 -0.0161 1.0000 0.1967
-5.750 -0.4415 0.07164 0.06534 -0.0160 1.0000 0.2125
-5.500 -0.1092 0.04601 0.03882 -0.0137 1.0000 1.0000
-5.250 -0.0981 0.04369 0.03654 -0.0148 1.0000 1.0000
-5.000 -0.0870 0.04138 0.03427 -0.0160 1.0000 1.0000
-4.750 -0.1902 0.04761 0.04092 0.0086 1.0000 0.9049
-4.250 -0.4248 0.05248 0.04677 0.0045 1.0000 0.4450
-4.000 -0.4253 0.04942 0.04387 0.0117 1.0000 0.5006
-3.750 -0.4244 0.04668 0.04124 0.0172 1.0000 0.5446
-3.500 -0.4196 0.04372 0.03840 0.0228 1.0000 0.5837
-3.250 -0.4130 0.04079 0.03548 0.0253 1.0000 0.6058
-3.000 -0.3990 0.03764 0.03231 0.0233 1.0000 0.6080
-2.750 -0.2384 0.03514 0.02689 -0.0201 1.0000 0.2211
-2.500 -0.2051 0.03269 0.02369 -0.0201 1.0000 0.1749
-2.250 -0.1786 0.03021 0.02070 -0.0190 1.0000 0.1542
-2.000 -0.1537 0.02819 0.01820 -0.0178 1.0000 0.1441
-1.750 -0.1292 0.02640 0.01596 -0.0165 1.0000 0.1403
-1.500 -0.1066 0.02511 0.01428 -0.0153 1.0000 0.1508
-1.250 -0.0827 0.02363 0.01264 -0.0144 1.0000 0.1601
-1.000 -0.0535 0.02237 0.01106 -0.0140 1.0000 0.1702
-0.750 -0.0278 0.02143 0.01007 -0.0135 1.0000 0.1994
-0.500 -0.0067 0.02061 0.00926 -0.0123 1.0000 0.2228
-0.250 0.0594 0.01701 0.00759 -0.0176 1.0000 1.0000
0.000 0.0701 0.01741 0.00762 -0.0155 1.0000 1.0000
0.250 0.0808 0.01788 0.00783 -0.0137 1.0000 1.0000
0.500 0.0918 0.01840 0.00814 -0.0121 1.0000 1.0000
0.750 0.1033 0.01898 0.00851 -0.0108 1.0000 1.0000
1.000 0.1152 0.01962 0.00899 -0.0098 1.0000 1.0000
1.250 0.1454 0.02046 0.00968 -0.0123 0.9932 1.0000
1.500 0.1994 0.02141 0.01051 -0.0192 0.9752 1.0000
1.750 0.2522 0.02228 0.01132 -0.0255 0.9582 1.0000
2.000 0.3020 0.02302 0.01205 -0.0310 0.9413 1.0000
2.250 0.3457 0.02367 0.01274 -0.0351 0.9236 1.0000
2.500 0.3917 0.02428 0.01346 -0.0395 0.9068 1.0000
2.750 0.4391 0.02484 0.01422 -0.0438 0.8908 1.0000
3.000 0.4888 0.02531 0.01490 -0.0484 0.8753 1.0000
3.250 0.5237 0.02590 0.01569 -0.0502 0.8583 1.0000
3.500 0.5579 0.02649 0.01652 -0.0517 0.8416 1.0000
3.750 0.6204 0.02560 0.01616 -0.0549 0.8105 1.0000
4.000 0.6735 0.02374 0.01470 -0.0535 0.7676 1.0000
4.250 0.7005 0.02312 0.01438 -0.0500 0.7344 1.0000
4.500 0.7181 0.02078 0.01199 -0.0402 0.6566 1.0000
4.750 0.7228 0.01975 0.01089 -0.0313 0.5609 1.0000
5.000 0.7197 0.02048 0.01030 -0.0231 0.2896 1.0000
5.250 0.7250 0.02359 0.01201 -0.0201 0.1538 1.0000
5.500 0.7370 0.02574 0.01393 -0.0177 0.1276 1.0000
5.750 0.7529 0.02773 0.01585 -0.0153 0.1167 1.0000
6.000 0.7792 0.02953 0.01782 -0.0136 0.1097 1.0000
6.250 0.8104 0.03209 0.02036 -0.0130 0.1002 1.0000
6.500 0.8413 0.03465 0.02314 -0.0122 0.0951 1.0000
6.750 0.8703 0.03762 0.02652 -0.0111 0.0958 1.0000
7.000 0.8950 0.04091 0.03041 -0.0096 0.0985 1.0000
7.250 0.9180 0.04488 0.03472 -0.0083 0.1021 1.0000
7.500 0.9373 0.04882 0.03905 -0.0068 0.1043 1.0000
7.750 0.9438 0.05164 0.04290 -0.0037 0.1100 1.0000
8.000 0.9534 0.05605 0.04774 -0.0020 0.1143 1.0000
8.250 0.9541 0.06037 0.05276 -0.0001 0.1236 1.0000
8.500 0.9521 0.06547 0.05834 0.0010 0.1345 1.0000
9.250 0.8931 0.08374 0.07735 -0.0021 0.1717 1.0000
9.500 0.8528 0.09217 0.08571 -0.0091 0.1851 1.0000
9.750 0.8169 0.10164 0.09492 -0.0183 0.2014 1.0000
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Polar data table (+)
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