GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 265 AIRFOIL (goe265-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.7 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe265-il-1000000-n5.txt Download as CSV file: xf-goe265-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 265 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2621 0.10433 0.10184 -0.0184 0.7311 0.0064
-9.000 -0.2543 0.10125 0.09872 -0.0199 0.7195 0.0067
-8.750 -0.2478 0.09772 0.09515 -0.0217 0.7096 0.0069
-6.750 -0.0907 0.01602 0.01151 -0.1201 0.6598 0.0193
-6.500 -0.0631 0.01344 0.00860 -0.1212 0.6514 0.0202
-6.250 -0.0350 0.01273 0.00777 -0.1214 0.6426 0.0211
-6.000 -0.0068 0.01238 0.00733 -0.1214 0.6309 0.0219
-5.750 0.0215 0.01204 0.00685 -0.1213 0.6167 0.0227
-5.500 0.0497 0.01172 0.00639 -0.1213 0.6019 0.0235
-5.250 0.0780 0.01143 0.00597 -0.1212 0.5898 0.0242
-5.000 0.1064 0.01120 0.00560 -0.1211 0.5801 0.0246
-4.750 0.1348 0.01077 0.00504 -0.1211 0.5706 0.0254
-4.500 0.1633 0.01052 0.00472 -0.1211 0.5624 0.0262
-4.250 0.1917 0.01036 0.00449 -0.1210 0.5541 0.0270
-4.000 0.2202 0.01018 0.00423 -0.1209 0.5463 0.0277
-3.750 0.2487 0.00999 0.00394 -0.1208 0.5380 0.0284
-3.500 0.2772 0.00981 0.00367 -0.1207 0.5313 0.0290
-3.250 0.3058 0.00962 0.00340 -0.1206 0.5246 0.0295
-3.000 0.3343 0.00948 0.00316 -0.1205 0.5176 0.0299
-2.750 0.3628 0.00934 0.00295 -0.1204 0.5105 0.0301
-2.500 0.3913 0.00912 0.00265 -0.1203 0.5035 0.0312
-2.250 0.4199 0.00898 0.00246 -0.1202 0.4979 0.0322
-2.000 0.4484 0.00887 0.00232 -0.1201 0.4911 0.0330
-1.750 0.4768 0.00880 0.00219 -0.1200 0.4842 0.0338
-1.500 0.5053 0.00873 0.00207 -0.1199 0.4767 0.0347
-1.250 0.5336 0.00869 0.00197 -0.1197 0.4685 0.0357
-1.000 0.5619 0.00867 0.00189 -0.1196 0.4576 0.0365
-0.750 0.5901 0.00863 0.00180 -0.1195 0.4466 0.0385
-0.500 0.6183 0.00863 0.00176 -0.1194 0.4357 0.0411
-0.250 0.6464 0.00865 0.00173 -0.1192 0.4247 0.0441
0.000 0.6746 0.00865 0.00172 -0.1191 0.4145 0.0486
0.250 0.7026 0.00870 0.00172 -0.1190 0.4038 0.0530
0.750 0.7584 0.00882 0.00178 -0.1187 0.3812 0.0626
1.000 0.7862 0.00891 0.00181 -0.1186 0.3698 0.0660
1.250 0.8139 0.00901 0.00188 -0.1185 0.3587 0.0707
1.500 0.8416 0.00912 0.00195 -0.1183 0.3478 0.0745
1.750 0.8693 0.00922 0.00201 -0.1182 0.3387 0.0772
2.000 0.8968 0.00934 0.00210 -0.1180 0.3292 0.0827
2.250 0.9244 0.00945 0.00219 -0.1179 0.3197 0.0874
2.500 0.9519 0.00956 0.00227 -0.1177 0.3131 0.0897
2.750 0.9796 0.00964 0.00235 -0.1176 0.3076 0.0933
3.000 1.0071 0.00975 0.00245 -0.1175 0.3017 0.0977
3.250 1.0346 0.00985 0.00255 -0.1174 0.2968 0.1015
3.500 1.0621 0.00995 0.00264 -0.1172 0.2911 0.1046
3.750 1.0893 0.01009 0.00277 -0.1171 0.2853 0.1102
4.000 1.1167 0.01018 0.00288 -0.1170 0.2812 0.1160
4.250 1.1440 0.01029 0.00300 -0.1168 0.2765 0.1206
4.500 1.1711 0.01042 0.00314 -0.1167 0.2712 0.1289
4.750 1.1982 0.01055 0.00328 -0.1165 0.2670 0.1379
5.000 1.2253 0.01065 0.00343 -0.1164 0.2625 0.1522
5.250 1.2521 0.01080 0.00361 -0.1163 0.2565 0.1732
5.500 1.2788 0.01092 0.00381 -0.1161 0.2505 0.2303
6.000 1.3289 0.01025 0.00433 -0.1154 0.2381 1.0000
6.250 1.3554 0.01045 0.00451 -0.1152 0.2316 1.0000
6.500 1.3811 0.01072 0.00474 -0.1150 0.2229 1.0000
6.750 1.4070 0.01096 0.00495 -0.1147 0.2148 1.0000
7.000 1.4322 0.01127 0.00522 -0.1144 0.2040 1.0000
7.250 1.4559 0.01175 0.00558 -0.1139 0.1837 1.0000
7.500 1.4764 0.01258 0.00618 -0.1130 0.1472 1.0000
7.750 1.4975 0.01330 0.00676 -0.1121 0.1256 1.0000
8.000 1.5206 0.01377 0.00719 -0.1115 0.1176 1.0000
8.250 1.5443 0.01416 0.00756 -0.1110 0.1121 1.0000
8.500 1.5686 0.01446 0.00789 -0.1106 0.1099 1.0000
8.750 1.5921 0.01482 0.00826 -0.1100 0.1064 1.0000
9.000 1.6148 0.01524 0.00867 -0.1094 0.1025 1.0000
9.250 1.6372 0.01568 0.00911 -0.1088 0.0979 1.0000
9.500 1.6606 0.01598 0.00945 -0.1082 0.0950 1.0000
9.750 1.6825 0.01642 0.00989 -0.1075 0.0896 1.0000
10.000 1.7027 0.01697 0.01040 -0.1066 0.0809 1.0000
10.250 1.7121 0.01840 0.01156 -0.1043 0.0497 1.0000
10.500 1.7121 0.02040 0.01337 -0.1008 0.0183 1.0000
10.750 1.7234 0.02131 0.01430 -0.0986 0.0137 1.0000
11.000 1.7331 0.02216 0.01518 -0.0962 0.0117 1.0000
11.250 1.7439 0.02298 0.01606 -0.0941 0.0108 1.0000
11.500 1.7529 0.02398 0.01712 -0.0920 0.0098 1.0000
11.750 1.7604 0.02519 0.01838 -0.0900 0.0089 1.0000
12.000 1.7692 0.02640 0.01966 -0.0884 0.0084 1.0000
12.250 1.7769 0.02779 0.02111 -0.0870 0.0078 1.0000
12.500 1.7832 0.02941 0.02279 -0.0857 0.0073 1.0000
12.750 1.7879 0.03129 0.02475 -0.0846 0.0068 1.0000
13.000 1.7919 0.03336 0.02689 -0.0836 0.0064 1.0000
13.250 1.7965 0.03547 0.02909 -0.0830 0.0062 1.0000
13.500 1.7996 0.03783 0.03153 -0.0824 0.0060 1.0000
13.750 1.8011 0.04042 0.03422 -0.0819 0.0057 1.0000
14.000 1.8012 0.04323 0.03711 -0.0815 0.0055 1.0000
14.250 1.7993 0.04631 0.04028 -0.0812 0.0053 1.0000
14.500 1.7959 0.04962 0.04367 -0.0810 0.0051 1.0000
14.750 1.7902 0.05325 0.04741 -0.0809 0.0050 1.0000
15.000 1.7827 0.05715 0.05141 -0.0809 0.0048 1.0000
15.250 1.7733 0.06146 0.05582 -0.0811 0.0047 1.0000
15.500 1.7662 0.06552 0.05998 -0.0813 0.0046 1.0000
15.750 1.7586 0.06974 0.06430 -0.0818 0.0045 1.0000
16.000 1.7500 0.07420 0.06887 -0.0823 0.0044 1.0000
16.250 1.7408 0.07880 0.07357 -0.0830 0.0043 1.0000
16.500 1.7307 0.08360 0.07847 -0.0838 0.0043 1.0000
16.750 1.7201 0.08856 0.08354 -0.0847 0.0042 1.0000
17.000 1.7091 0.09363 0.08871 -0.0857 0.0041 1.0000
17.250 1.6977 0.09881 0.09400 -0.0869 0.0040 1.0000
17.500 1.6863 0.10407 0.09935 -0.0882 0.0039 1.0000
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