GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 459 AIRFOIL (goe459-il) Reynolds number: 50,000 Max Cl/Cd: 27.75 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe459-il-50000-n5.txt Download as CSV file: xf-goe459-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 459 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7100 0.09935 0.09148 -0.0323 1.0000 0.0904
-12.750 -0.7542 0.08714 0.07926 -0.0397 1.0000 0.0897
-12.500 -0.7981 0.07742 0.06947 -0.0450 1.0000 0.0887
-12.250 -0.8353 0.07036 0.06226 -0.0475 1.0000 0.0879
-12.000 -0.8672 0.06510 0.05680 -0.0477 1.0000 0.0880
-11.750 -0.8944 0.06105 0.05252 -0.0460 1.0000 0.0888
-11.500 -0.9187 0.05776 0.04896 -0.0429 1.0000 0.0898
-11.250 -0.9428 0.05495 0.04581 -0.0383 1.0000 0.0912
-11.000 -0.9290 0.05375 0.04475 -0.0370 1.0000 0.0952
-10.750 -0.9300 0.05167 0.04251 -0.0344 1.0000 0.0978
-10.500 -0.9323 0.04934 0.03991 -0.0314 1.0000 0.1004
-10.250 -0.9347 0.04699 0.03717 -0.0282 1.0000 0.1031
-10.000 -0.9278 0.04499 0.03497 -0.0259 1.0000 0.1060
-9.750 -0.9140 0.04337 0.03328 -0.0243 1.0000 0.1088
-9.500 -0.9008 0.04160 0.03127 -0.0225 1.0000 0.1114
-9.250 -0.8873 0.03988 0.02929 -0.0207 1.0000 0.1145
-9.000 -0.8747 0.03826 0.02731 -0.0186 1.0000 0.1185
-8.750 -0.8559 0.03699 0.02611 -0.0175 1.0000 0.1222
-8.500 -0.8380 0.03571 0.02471 -0.0161 1.0000 0.1263
-8.250 -0.8182 0.03437 0.02315 -0.0148 1.0000 0.1307
-8.000 -0.7981 0.03316 0.02185 -0.0136 1.0000 0.1352
-7.750 -0.7800 0.03208 0.02075 -0.0121 1.0000 0.1412
-7.500 -0.7623 0.03104 0.01962 -0.0105 1.0000 0.1494
-7.250 -0.7465 0.03004 0.01864 -0.0087 1.0000 0.1591
-7.000 -0.7315 0.02902 0.01768 -0.0067 1.0000 0.1706
-6.750 -0.7174 0.02803 0.01672 -0.0045 1.0000 0.1848
-6.500 -0.7043 0.02710 0.01587 -0.0022 1.0000 0.2029
-6.250 -0.6916 0.02626 0.01510 0.0002 1.0000 0.2248
-6.000 -0.6796 0.02549 0.01442 0.0028 1.0000 0.2508
-5.750 -0.6675 0.02476 0.01380 0.0053 1.0000 0.2788
-5.500 -0.6550 0.02408 0.01320 0.0078 1.0000 0.3086
-5.250 -0.6423 0.02344 0.01271 0.0104 1.0000 0.3393
-5.000 -0.6309 0.02285 0.01235 0.0132 1.0000 0.3783
-4.750 -0.6206 0.02236 0.01214 0.0164 1.0000 0.4259
-4.500 -0.6097 0.02198 0.01198 0.0196 1.0000 0.4744
-4.250 -0.5969 0.02167 0.01181 0.0227 1.0000 0.5187
-4.000 -0.5816 0.02145 0.01174 0.0253 1.0000 0.5575
-3.750 -0.5650 0.02130 0.01167 0.0278 1.0000 0.5931
-3.500 -0.5476 0.02120 0.01159 0.0300 1.0000 0.6251
-3.250 -0.5302 0.02114 0.01155 0.0323 1.0000 0.6563
-3.000 -0.5121 0.02113 0.01156 0.0344 1.0000 0.6864
-2.750 -0.4929 0.02116 0.01161 0.0364 1.0000 0.7162
-2.500 -0.4720 0.02127 0.01173 0.0381 1.0000 0.7464
-2.250 -0.4489 0.02145 0.01193 0.0394 1.0000 0.7768
-2.000 -0.4240 0.02168 0.01214 0.0402 1.0000 0.8060
-1.750 -0.3886 0.02203 0.01245 0.0390 0.9987 0.8311
-1.500 -0.3389 0.02244 0.01277 0.0347 0.9911 0.8534
-1.250 -0.2839 0.02290 0.01313 0.0294 0.9843 0.8715
-1.000 -0.2293 0.02328 0.01343 0.0241 0.9769 0.8884
-0.750 -0.1682 0.02373 0.01381 0.0177 0.9707 0.9049
-0.500 -0.1088 0.02406 0.01409 0.0115 0.9632 0.9205
-0.250 -0.0545 0.02421 0.01421 0.0058 0.9539 0.9338
0.000 0.0000 0.02426 0.01424 0.0000 0.9446 0.9446
0.250 0.0545 0.02421 0.01421 -0.0058 0.9338 0.9539
0.500 0.1087 0.02407 0.01409 -0.0115 0.9205 0.9632
0.750 0.1681 0.02373 0.01381 -0.0177 0.9050 0.9708
1.000 0.2292 0.02328 0.01343 -0.0241 0.8884 0.9769
1.250 0.2840 0.02289 0.01312 -0.0294 0.8715 0.9844
1.500 0.3389 0.02243 0.01276 -0.0347 0.8534 0.9911
1.750 0.3887 0.02203 0.01245 -0.0390 0.8312 0.9988
2.000 0.4238 0.02168 0.01215 -0.0402 0.8061 1.0000
2.250 0.4488 0.02146 0.01193 -0.0394 0.7771 1.0000
2.500 0.4719 0.02128 0.01174 -0.0381 0.7470 1.0000
2.750 0.4928 0.02116 0.01162 -0.0364 0.7165 1.0000
3.000 0.5121 0.02113 0.01156 -0.0344 0.6867 1.0000
3.250 0.5302 0.02114 0.01155 -0.0323 0.6565 1.0000
3.500 0.5476 0.02120 0.01159 -0.0300 0.6255 1.0000
3.750 0.5650 0.02130 0.01167 -0.0278 0.5932 1.0000
4.000 0.5815 0.02145 0.01173 -0.0253 0.5576 1.0000
4.250 0.5969 0.02167 0.01181 -0.0227 0.5189 1.0000
4.500 0.6095 0.02197 0.01195 -0.0196 0.4742 1.0000
4.750 0.6206 0.02236 0.01214 -0.0164 0.4259 1.0000
5.000 0.6309 0.02285 0.01234 -0.0132 0.3784 1.0000
5.250 0.6422 0.02343 0.01270 -0.0104 0.3392 1.0000
5.500 0.6550 0.02407 0.01320 -0.0078 0.3087 1.0000
5.750 0.6675 0.02476 0.01379 -0.0053 0.2789 1.0000
6.000 0.6796 0.02549 0.01441 -0.0028 0.2507 1.0000
6.250 0.6916 0.02625 0.01509 -0.0002 0.2248 1.0000
6.500 0.7043 0.02710 0.01586 0.0022 0.2030 1.0000
6.750 0.7174 0.02803 0.01672 0.0045 0.1849 1.0000
7.000 0.7315 0.02902 0.01767 0.0067 0.1706 1.0000
7.250 0.7466 0.03004 0.01863 0.0087 0.1593 1.0000
7.500 0.7625 0.03103 0.01962 0.0105 0.1496 1.0000
7.750 0.7801 0.03208 0.02075 0.0121 0.1413 1.0000
8.000 0.7982 0.03316 0.02185 0.0136 0.1353 1.0000
8.250 0.8184 0.03437 0.02315 0.0148 0.1308 1.0000
8.500 0.8381 0.03570 0.02470 0.0160 0.1264 1.0000
8.750 0.8561 0.03700 0.02612 0.0174 0.1223 1.0000
9.000 0.8748 0.03826 0.02731 0.0186 0.1184 1.0000
9.250 0.8876 0.03987 0.02929 0.0206 0.1146 1.0000
9.500 0.9010 0.04160 0.03127 0.0225 0.1114 1.0000
9.750 0.9141 0.04337 0.03327 0.0243 0.1088 1.0000
10.000 0.9279 0.04499 0.03497 0.0259 0.1060 1.0000
10.250 0.9351 0.04699 0.03717 0.0281 0.1032 1.0000
10.500 0.9326 0.04934 0.03991 0.0313 0.1004 1.0000
10.750 0.9303 0.05170 0.04254 0.0343 0.0979 1.0000
11.000 0.9295 0.05373 0.04474 0.0370 0.0951 1.0000
11.250 0.9435 0.05498 0.04584 0.0382 0.0913 1.0000
11.500 0.9194 0.05778 0.04898 0.0428 0.0899 1.0000
11.750 0.8943 0.06109 0.05256 0.0460 0.0887 1.0000
12.000 0.8674 0.06512 0.05683 0.0476 0.0879 1.0000
12.250 0.8360 0.07035 0.06224 0.0474 0.0878 1.0000
12.500 0.7979 0.07754 0.06959 0.0448 0.0886 1.0000
12.750 0.7552 0.08715 0.07928 0.0395 0.0897 1.0000
13.000 0.7096 0.09965 0.09178 0.0320 0.0903 1.0000
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