GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 500,000 Max Cl/Cd: 105.31 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417-il-500000.txt Download as CSV file: xf-goe417-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2962 0.10326 0.10112 -0.0216 1.0000 0.0130
-8.250 -0.3003 0.10161 0.09951 -0.0195 1.0000 0.0131
-8.000 -0.3043 0.10007 0.09801 -0.0178 0.9999 0.0132
-7.750 -0.2856 0.09647 0.09441 -0.0220 0.9976 0.0134
-7.500 -0.2655 0.09286 0.09079 -0.0268 0.9949 0.0142
-7.250 -0.2472 0.08931 0.08725 -0.0313 0.9908 0.0152
-7.000 -0.2248 0.08556 0.08349 -0.0373 0.9865 0.0158
-6.750 -0.1853 0.08127 0.07917 -0.0514 0.9821 0.0162
-6.500 -0.1557 0.07720 0.07507 -0.0604 0.9762 0.0163
-6.250 -0.1332 0.07215 0.07002 -0.0641 0.9737 0.0164
-6.000 -0.1109 0.06826 0.06612 -0.0666 0.9720 0.0166
-5.750 -0.0792 0.06442 0.06226 -0.0724 0.9704 0.0171
-5.500 -0.0521 0.06109 0.05890 -0.0773 0.9647 0.0177
-5.250 -0.0157 0.05717 0.05493 -0.0845 0.9610 0.0189
-5.000 0.0448 0.05255 0.05016 -0.0984 0.9574 0.0205
-4.750 0.0810 0.04883 0.04633 -0.1041 0.9506 0.0206
-4.500 0.1018 0.04428 0.04175 -0.1065 0.9441 0.0210
-4.250 0.1237 0.04183 0.03926 -0.1076 0.9364 0.0215
-4.000 0.1495 0.03938 0.03674 -0.1094 0.9286 0.0222
-3.750 0.1764 0.03691 0.03417 -0.1113 0.9204 0.0235
-3.500 0.2208 0.03404 0.03103 -0.1152 0.9137 0.0261
-3.250 0.2520 0.03122 0.02799 -0.1165 0.9055 0.0263
-3.000 0.2721 0.02737 0.02406 -0.1176 0.8981 0.0272
-2.750 0.2950 0.02584 0.02247 -0.1177 0.8884 0.0281
-2.500 0.3221 0.02409 0.02057 -0.1181 0.8800 0.0297
-2.250 0.3562 0.02272 0.01885 -0.1180 0.8710 0.0335
-2.000 0.3821 0.01912 0.01494 -0.1185 0.8614 0.0350
-1.750 0.4071 0.01793 0.01367 -0.1184 0.8515 0.0362
-1.500 0.4332 0.01690 0.01249 -0.1182 0.8404 0.0383
-1.250 0.4615 0.01654 0.01186 -0.1175 0.8277 0.0430
-1.000 0.4872 0.01446 0.00952 -0.1173 0.8149 0.0464
-0.750 0.5128 0.01384 0.00881 -0.1170 0.8008 0.0497
-0.500 0.5407 0.01466 0.00941 -0.1161 0.7849 0.0561
1.500 0.7414 0.00989 0.00298 -0.1094 0.5801 0.0440
1.750 0.7657 0.00979 0.00277 -0.1086 0.5526 0.0438
2.000 0.7894 0.00974 0.00257 -0.1077 0.5201 0.0441
2.250 0.8129 0.00978 0.00246 -0.1068 0.4848 0.0448
2.500 0.8367 0.00988 0.00241 -0.1060 0.4530 0.0470
2.750 0.8610 0.01006 0.00245 -0.1053 0.4271 0.0476
3.000 0.8856 0.01023 0.00252 -0.1046 0.4060 0.0489
3.250 0.9104 0.01041 0.00261 -0.1040 0.3891 0.0518
3.500 0.9354 0.01056 0.00272 -0.1034 0.3755 0.0662
3.750 0.9650 0.00928 0.00309 -0.1044 0.3636 1.0000
4.000 0.9899 0.00951 0.00325 -0.1038 0.3535 1.0000
4.250 1.0148 0.00974 0.00341 -0.1032 0.3441 1.0000
4.500 1.0400 0.00994 0.00358 -0.1027 0.3357 1.0000
4.750 1.0644 0.01020 0.00378 -0.1021 0.3275 1.0000
5.000 1.0898 0.01038 0.00398 -0.1017 0.3197 1.0000
5.250 1.1142 0.01064 0.00420 -0.1011 0.3120 1.0000
5.500 1.1394 0.01082 0.00440 -0.1006 0.3040 1.0000
5.750 1.1639 0.01106 0.00461 -0.1000 0.2934 1.0000
6.000 1.1880 0.01130 0.00483 -0.0994 0.2776 1.0000
6.250 1.2120 0.01157 0.00505 -0.0988 0.2614 1.0000
6.500 1.2358 0.01185 0.00529 -0.0981 0.2464 1.0000
6.750 1.2585 0.01223 0.00557 -0.0973 0.2241 1.0000
7.000 1.2804 0.01268 0.00592 -0.0964 0.2000 1.0000
7.250 1.3020 0.01316 0.00631 -0.0955 0.1799 1.0000
7.500 1.3231 0.01367 0.00675 -0.0945 0.1624 1.0000
7.750 1.3434 0.01425 0.00723 -0.0934 0.1448 1.0000
8.000 1.3629 0.01491 0.00777 -0.0922 0.1211 1.0000
8.250 1.3719 0.01659 0.00896 -0.0895 0.0463 1.0000
8.500 1.3851 0.01784 0.01007 -0.0873 0.0223 1.0000
8.750 1.4032 0.01856 0.01088 -0.0857 0.0192 1.0000
9.000 1.4196 0.01937 0.01177 -0.0839 0.0172 1.0000
9.250 1.4323 0.02047 0.01299 -0.0816 0.0156 1.0000
9.500 1.4434 0.02151 0.01418 -0.0790 0.0148 1.0000
9.750 1.4543 0.02238 0.01515 -0.0763 0.0143 1.0000
10.000 1.4624 0.02337 0.01625 -0.0733 0.0138 1.0000
10.250 1.4686 0.02448 0.01748 -0.0702 0.0133 1.0000
10.500 1.4735 0.02570 0.01880 -0.0671 0.0129 1.0000
10.750 1.4773 0.02703 0.02022 -0.0641 0.0123 1.0000
11.000 1.4786 0.02859 0.02187 -0.0611 0.0118 1.0000
11.250 1.4764 0.03051 0.02389 -0.0581 0.0114 1.0000
11.500 1.4681 0.03309 0.02661 -0.0549 0.0110 1.0000
11.750 1.4576 0.03617 0.02982 -0.0520 0.0108 1.0000
12.000 1.4557 0.03868 0.03245 -0.0500 0.0106 1.0000
12.250 1.4574 0.04095 0.03483 -0.0486 0.0105 1.0000
12.500 1.4602 0.04314 0.03715 -0.0474 0.0103 1.0000
12.750 1.4610 0.04571 0.03984 -0.0464 0.0102 1.0000
13.000 1.4615 0.04843 0.04269 -0.0456 0.0100 1.0000
13.250 1.4614 0.05132 0.04571 -0.0449 0.0098 1.0000
13.500 1.4608 0.05443 0.04896 -0.0444 0.0097 1.0000
13.750 1.4597 0.05771 0.05237 -0.0441 0.0096 1.0000
14.000 1.4580 0.06117 0.05599 -0.0440 0.0095 1.0000
14.250 1.4554 0.06490 0.05988 -0.0441 0.0094 1.0000
14.500 1.4515 0.06891 0.06404 -0.0445 0.0092 1.0000
14.750 1.4466 0.07318 0.06848 -0.0452 0.0091 1.0000
15.000 1.4411 0.07764 0.07309 -0.0464 0.0090 1.0000
15.250 1.4339 0.08250 0.07812 -0.0479 0.0089 1.0000
15.500 1.4260 0.08765 0.08342 -0.0497 0.0088 1.0000
15.750 1.4171 0.09316 0.08909 -0.0519 0.0087 1.0000
16.000 1.4083 0.09878 0.09486 -0.0545 0.0086 1.0000
16.250 1.3975 0.10496 0.10120 -0.0574 0.0086 1.0000
16.500 1.3878 0.11110 0.10749 -0.0606 0.0085 1.0000
16.750 1.3757 0.11797 0.11452 -0.0644 0.0085 1.0000
17.000 1.3587 0.12620 0.12296 -0.0691 0.0086 1.0000
17.250 1.3427 0.13450 0.13145 -0.0741 0.0087 1.0000
17.500 1.3241 0.14374 0.14090 -0.0799 0.0089 1.0000
17.750 1.3077 0.15277 0.15009 -0.0857 0.0090 1.0000
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