GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il) Reynolds number: 500,000 Max Cl/Cd: 107.72 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe155-il-500000.txt Download as CSV file: xf-goe155-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 155 (SSW D.1) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3997 0.12840 0.12621 -0.0038 1.0000 0.0142
-10.250 -0.3949 0.12543 0.12326 -0.0066 1.0000 0.0142
-10.000 -0.3899 0.12230 0.12015 -0.0092 1.0000 0.0142
-9.750 -0.3799 0.11729 0.11515 -0.0088 1.0000 0.0144
-9.500 -0.3712 0.11376 0.11162 -0.0093 1.0000 0.0146
-9.250 -0.3629 0.11060 0.10848 -0.0105 1.0000 0.0147
-9.000 -0.3545 0.10751 0.10541 -0.0121 1.0000 0.0150
-8.750 -0.3459 0.10442 0.10232 -0.0139 1.0000 0.0153
-8.500 -0.3369 0.10129 0.09921 -0.0160 1.0000 0.0157
-8.250 -0.3277 0.09810 0.09604 -0.0183 1.0000 0.0162
-8.000 -0.3181 0.09486 0.09282 -0.0209 1.0000 0.0169
-7.750 -0.3022 0.09113 0.08910 -0.0267 0.9789 0.0179
-7.500 -0.2926 0.08805 0.08599 -0.0323 0.9574 0.0181
-7.250 -0.2825 0.08477 0.08267 -0.0368 0.9414 0.0182
-7.000 -0.2690 0.08111 0.07897 -0.0409 0.9286 0.0182
-6.750 -0.2518 0.07722 0.07503 -0.0454 0.9170 0.0183
-6.500 -0.2494 0.07327 0.07108 -0.0428 0.9082 0.0187
-6.250 -0.2369 0.07052 0.06827 -0.0435 0.8990 0.0190
-6.000 -0.2192 0.06740 0.06512 -0.0462 0.8885 0.0195
-5.750 -0.1992 0.06414 0.06178 -0.0497 0.8789 0.0201
-5.500 -0.1765 0.06065 0.05820 -0.0537 0.8700 0.0212
-5.250 -0.1308 0.05570 0.05308 -0.0643 0.8605 0.0232
-5.000 -0.0988 0.05145 0.04865 -0.0693 0.8529 0.0234
-4.750 -0.0762 0.04561 0.04270 -0.0732 0.8447 0.0239
-4.500 -0.0561 0.04331 0.04032 -0.0740 0.8369 0.0244
-4.250 -0.0317 0.04096 0.03787 -0.0755 0.8286 0.0252
-4.000 -0.0034 0.03826 0.03503 -0.0777 0.8213 0.0266
-3.750 0.0382 0.03505 0.03150 -0.0808 0.8146 0.0299
-3.500 0.0678 0.02936 0.02547 -0.0835 0.8092 0.0310
-3.250 0.0927 0.02776 0.02382 -0.0843 0.8025 0.0319
-3.000 0.1193 0.02622 0.02213 -0.0850 0.7968 0.0333
-2.750 0.1491 0.02421 0.01992 -0.0857 0.7908 0.0360
-2.500 0.1814 0.02080 0.01603 -0.0866 0.7849 0.0405
-2.250 0.2077 0.02004 0.01524 -0.0869 0.7787 0.0424
-2.000 0.2388 0.01884 0.01359 -0.0871 0.7717 0.0503
-1.750 0.2650 0.01746 0.01221 -0.0875 0.7648 0.0527
-1.500 0.2947 0.01840 0.01296 -0.0871 0.7567 0.0607
-1.250 0.3216 0.01577 0.01021 -0.0879 0.7500 0.0650
-1.000 0.3511 0.01669 0.01096 -0.0875 0.7416 0.0733
-0.750 0.3783 0.01435 0.00856 -0.0882 0.7344 0.0792
-0.500 0.4115 0.01165 0.00522 -0.0873 0.7270 0.0460
-0.250 0.4403 0.01061 0.00397 -0.0870 0.7191 0.0415
0.000 0.4687 0.01017 0.00345 -0.0869 0.7101 0.0410
0.250 0.4970 0.00982 0.00307 -0.0869 0.7018 0.0408
0.500 0.5251 0.00955 0.00275 -0.0869 0.6933 0.0410
0.750 0.5535 0.00929 0.00250 -0.0869 0.6835 0.0423
1.000 0.5818 0.00912 0.00230 -0.0869 0.6737 0.0426
1.250 0.6100 0.00900 0.00214 -0.0869 0.6633 0.0428
1.500 0.6384 0.00890 0.00203 -0.0870 0.6513 0.0436
1.750 0.6667 0.00885 0.00195 -0.0870 0.6380 0.0456
2.000 0.6948 0.00883 0.00189 -0.0870 0.6228 0.0489
2.250 0.7228 0.00883 0.00190 -0.0870 0.6050 0.0730
2.500 0.7506 0.00876 0.00197 -0.0871 0.5836 0.1618
2.750 0.7753 0.00723 0.00213 -0.0868 0.5604 1.0000
3.000 0.8025 0.00745 0.00220 -0.0867 0.5334 1.0000
3.250 0.8294 0.00771 0.00232 -0.0867 0.5071 1.0000
3.500 0.8563 0.00798 0.00245 -0.0866 0.4840 1.0000
3.750 0.8832 0.00824 0.00261 -0.0865 0.4633 1.0000
4.000 0.9097 0.00854 0.00279 -0.0864 0.4412 1.0000
4.250 0.9364 0.00881 0.00299 -0.0864 0.4217 1.0000
4.500 0.9630 0.00909 0.00319 -0.0863 0.4035 1.0000
4.750 0.9894 0.00938 0.00340 -0.0862 0.3838 1.0000
5.000 1.0159 0.00965 0.00362 -0.0861 0.3627 1.0000
5.250 1.0416 0.01001 0.00386 -0.0859 0.3343 1.0000
5.500 1.0668 0.01043 0.00413 -0.0857 0.3025 1.0000
5.750 1.0918 0.01088 0.00444 -0.0855 0.2755 1.0000
6.000 1.1166 0.01134 0.00480 -0.0852 0.2534 1.0000
6.250 1.1410 0.01182 0.00517 -0.0849 0.2290 1.0000
6.500 1.1641 0.01247 0.00562 -0.0845 0.1886 1.0000
6.750 1.1744 0.01489 0.00714 -0.0826 0.0403 1.0000
7.000 1.1967 0.01561 0.00790 -0.0819 0.0320 1.0000
7.250 1.2187 0.01633 0.00869 -0.0811 0.0279 1.0000
7.500 1.2372 0.01746 0.00994 -0.0798 0.0245 1.0000
7.750 1.2589 0.01809 0.01064 -0.0790 0.0231 1.0000
8.000 1.2793 0.01882 0.01145 -0.0780 0.0213 1.0000
8.250 1.2982 0.01964 0.01231 -0.0770 0.0196 1.0000
8.500 1.3090 0.02121 0.01400 -0.0748 0.0182 1.0000
8.750 1.3199 0.02263 0.01552 -0.0725 0.0175 1.0000
9.000 1.3353 0.02355 0.01653 -0.0709 0.0169 1.0000
9.250 1.3472 0.02466 0.01773 -0.0688 0.0163 1.0000
9.500 1.3556 0.02583 0.01898 -0.0663 0.0157 1.0000
9.750 1.3649 0.02698 0.02020 -0.0640 0.0150 1.0000
10.000 1.3747 0.02813 0.02142 -0.0621 0.0143 1.0000
10.250 1.3823 0.02954 0.02287 -0.0602 0.0137 1.0000
10.500 1.3848 0.03171 0.02510 -0.0577 0.0132 1.0000
10.750 1.3905 0.03459 0.02806 -0.0551 0.0127 1.0000
11.000 1.4004 0.03598 0.02959 -0.0536 0.0125 1.0000
11.250 1.4102 0.03766 0.03140 -0.0520 0.0122 1.0000
11.500 1.4198 0.03956 0.03345 -0.0503 0.0120 1.0000
11.750 1.4288 0.04171 0.03577 -0.0486 0.0117 1.0000
12.000 1.4364 0.04415 0.03839 -0.0469 0.0115 1.0000
12.250 1.4417 0.04687 0.04131 -0.0452 0.0113 1.0000
12.500 1.4437 0.04957 0.04420 -0.0436 0.0110 1.0000
12.750 1.4431 0.05243 0.04725 -0.0421 0.0108 1.0000
13.000 1.4407 0.05523 0.05020 -0.0410 0.0105 1.0000
13.250 1.4375 0.05813 0.05324 -0.0402 0.0103 1.0000
13.500 1.4316 0.06157 0.05685 -0.0395 0.0102 1.0000
13.750 1.4201 0.06615 0.06167 -0.0388 0.0102 1.0000
14.000 1.3981 0.07249 0.06835 -0.0385 0.0104 1.0000
14.250 1.3754 0.07899 0.07513 -0.0392 0.0107 1.0000
14.500 1.3535 0.08549 0.08186 -0.0405 0.0109 1.0000
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