GOE 587 AIRFOIL (goe587-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 587 AIRFOIL (goe587-il) Reynolds number: 500,000 Max Cl/Cd: 77.78 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe587-il-500000.txt Download as CSV file: xf-goe587-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4577 0.09457 0.09233 -0.0141 1.0000 0.0111
-8.000 -0.4568 0.09139 0.08917 -0.0155 1.0000 0.0111
-7.750 -0.4582 0.08828 0.08609 -0.0169 1.0000 0.0111
-7.500 -0.4542 0.08473 0.08254 -0.0189 1.0000 0.0111
-7.250 -0.4485 0.08117 0.07899 -0.0207 1.0000 0.0111
-7.000 -0.4494 0.07566 0.07348 -0.0226 1.0000 0.0113
-6.750 -0.4477 0.07101 0.06882 -0.0237 1.0000 0.0117
-6.500 -0.4409 0.06773 0.06553 -0.0240 1.0000 0.0120
-6.250 -0.4323 0.06462 0.06240 -0.0243 1.0000 0.0123
-6.000 -0.4223 0.06144 0.05919 -0.0247 1.0000 0.0126
-5.750 -0.4110 0.05827 0.05595 -0.0251 1.0000 0.0130
-5.500 -0.3986 0.05509 0.05271 -0.0254 1.0000 0.0134
-5.250 -0.3855 0.05191 0.04946 -0.0253 1.0000 0.0141
-5.000 -0.3717 0.04876 0.04623 -0.0250 1.0000 0.0147
-4.750 -0.3575 0.04564 0.04301 -0.0242 1.0000 0.0159
-4.500 -0.3291 0.04312 0.04033 -0.0243 0.9994 0.0181
-4.250 -0.2902 0.03913 0.03610 -0.0273 0.9959 0.0185
-4.000 -0.2556 0.03449 0.03118 -0.0295 0.9916 0.0186
-3.750 -0.2304 0.02763 0.02400 -0.0321 0.9854 0.0207
-3.500 -0.1973 0.02634 0.02259 -0.0342 0.9805 0.0255
-3.250 -0.1589 0.02555 0.02148 -0.0346 0.9736 0.0290
-3.000 -0.1323 0.01658 0.01168 -0.0337 0.9657 0.0175
-2.750 -0.0999 0.01339 0.00797 -0.0341 0.9577 0.0171
-2.500 -0.0639 0.01239 0.00673 -0.0354 0.9481 0.0186
-2.250 -0.0282 0.01033 0.00446 -0.0370 0.9382 0.0227
-2.000 0.0108 0.00963 0.00366 -0.0393 0.9245 0.0270
-1.750 0.0454 0.00879 0.00269 -0.0406 0.9061 0.0331
-1.500 0.0765 0.00871 0.00252 -0.0412 0.8847 0.0414
-1.250 0.1020 0.00828 0.00200 -0.0406 0.8619 0.0505
-1.000 0.1273 0.00815 0.00176 -0.0400 0.8386 0.0573
-0.750 0.1520 0.00798 0.00152 -0.0392 0.8154 0.0668
-0.500 0.1761 0.00778 0.00135 -0.0383 0.7923 0.1034
-0.250 0.1960 0.00708 0.00127 -0.0370 0.7697 0.3487
0.000 0.1990 0.00559 0.00140 -0.0313 0.7510 0.9124
0.250 0.2271 0.00576 0.00150 -0.0307 0.7316 0.9513
0.500 0.2771 0.00607 0.00165 -0.0351 0.7048 0.9719
0.750 0.3919 0.00650 0.00180 -0.0540 0.6632 0.9965
1.000 0.4307 0.00652 0.00169 -0.0566 0.6364 1.0000
1.250 0.4533 0.00661 0.00167 -0.0556 0.6141 1.0000
1.500 0.4757 0.00670 0.00166 -0.0545 0.5904 1.0000
1.750 0.4981 0.00681 0.00169 -0.0535 0.5666 1.0000
2.000 0.5203 0.00694 0.00172 -0.0524 0.5425 1.0000
2.250 0.5416 0.00714 0.00176 -0.0512 0.5068 1.0000
2.500 0.5637 0.00729 0.00181 -0.0501 0.4741 1.0000
2.750 0.5849 0.00752 0.00187 -0.0489 0.4222 1.0000
3.000 0.6005 0.00838 0.00210 -0.0468 0.2720 1.0000
3.250 0.6118 0.00990 0.00270 -0.0443 0.0545 1.0000
3.500 0.6326 0.01024 0.00304 -0.0429 0.0438 1.0000
3.750 0.6530 0.01060 0.00349 -0.0415 0.0393 1.0000
4.000 0.6733 0.01094 0.00389 -0.0400 0.0354 1.0000
4.250 0.6916 0.01148 0.00449 -0.0382 0.0308 1.0000
4.500 0.7063 0.01237 0.00549 -0.0357 0.0268 1.0000
4.750 0.7252 0.01277 0.00598 -0.0339 0.0237 1.0000
5.000 0.7437 0.01320 0.00643 -0.0322 0.0201 1.0000
5.250 0.7563 0.01432 0.00760 -0.0293 0.0179 1.0000
5.500 0.7690 0.01589 0.00924 -0.0264 0.0165 1.0000
5.750 0.7884 0.01678 0.01021 -0.0246 0.0155 1.0000
6.000 0.8078 0.01832 0.01185 -0.0228 0.0150 1.0000
6.250 0.8289 0.01904 0.01266 -0.0215 0.0132 1.0000
6.500 0.8498 0.02016 0.01390 -0.0203 0.0122 1.0000
6.750 0.8704 0.02180 0.01568 -0.0189 0.0116 1.0000
7.000 0.8900 0.02390 0.01797 -0.0174 0.0111 1.0000
7.750 0.9112 0.04429 0.03978 -0.0081 0.0169 1.0000
8.000 0.9191 0.04746 0.04323 -0.0059 0.0169 1.0000
8.250 0.9250 0.05056 0.04660 -0.0037 0.0169 1.0000
8.500 0.9286 0.05350 0.04979 -0.0015 0.0168 1.0000
8.750 0.9315 0.05585 0.05239 0.0008 0.0166 1.0000
9.000 0.9470 0.05548 0.05229 0.0034 0.0150 1.0000
9.250 0.9445 0.05862 0.05564 0.0055 0.0143 1.0000
9.500 0.9380 0.06163 0.05882 0.0076 0.0134 1.0000
9.750 0.9214 0.06458 0.06189 0.0104 0.0135 1.0000
10.000 0.9042 0.06771 0.06513 0.0116 0.0132 1.0000
10.250 0.8824 0.07225 0.06978 0.0106 0.0138 1.0000
10.500 0.8634 0.07739 0.07502 0.0075 0.0136 1.0000
10.750 0.8431 0.08416 0.08186 0.0026 0.0143 1.0000
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Polar data table (+)
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