GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 500,000 Max Cl/Cd: 88.15 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe363-il-500000-n5.txt Download as CSV file: xf-goe363-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2512 0.11569 0.11344 -0.0396 0.9925 0.0088
-10.750 -0.2429 0.11108 0.10882 -0.0428 0.9856 0.0089
-9.250 -0.3867 0.02222 0.01831 -0.1176 0.8776 0.0123
-9.000 -0.3624 0.02100 0.01692 -0.1179 0.8703 0.0128
-8.750 -0.3362 0.02042 0.01624 -0.1180 0.8635 0.0132
-8.250 -0.2842 0.01902 0.01455 -0.1181 0.8512 0.0143
-8.000 -0.2588 0.01794 0.01322 -0.1182 0.8453 0.0151
-7.750 -0.2332 0.01680 0.01179 -0.1182 0.8403 0.0160
-7.500 -0.2057 0.01660 0.01155 -0.1181 0.8346 0.0166
-7.250 -0.1781 0.01650 0.01140 -0.1181 0.8295 0.0172
-7.000 -0.1506 0.01622 0.01103 -0.1180 0.8251 0.0180
-6.750 -0.1235 0.01564 0.01029 -0.1180 0.8198 0.0190
-6.500 -0.0964 0.01504 0.00947 -0.1178 0.8144 0.0200
-6.250 -0.0692 0.01451 0.00882 -0.1178 0.8095 0.0209
-6.000 -0.0416 0.01428 0.00856 -0.1177 0.8041 0.0217
-5.750 -0.0140 0.01402 0.00823 -0.1176 0.7986 0.0226
-5.500 0.0136 0.01366 0.00777 -0.1175 0.7930 0.0235
-5.250 0.0413 0.01333 0.00733 -0.1174 0.7862 0.0247
-5.000 0.0690 0.01308 0.00694 -0.1172 0.7795 0.0256
-4.750 0.0969 0.01283 0.00660 -0.1170 0.7715 0.0261
-4.500 0.1235 0.01204 0.00569 -0.1168 0.7638 0.0275
-4.250 0.1510 0.01168 0.00529 -0.1167 0.7542 0.0285
-4.000 0.1785 0.01138 0.00491 -0.1165 0.7442 0.0294
-3.750 0.2060 0.01110 0.00455 -0.1162 0.7332 0.0302
-3.500 0.2336 0.01086 0.00424 -0.1160 0.7206 0.0313
-3.250 0.2609 0.01064 0.00392 -0.1157 0.7045 0.0321
-3.000 0.2877 0.01046 0.00361 -0.1153 0.6814 0.0327
-2.750 0.3136 0.01037 0.00335 -0.1148 0.6475 0.0332
-2.500 0.3386 0.01041 0.00314 -0.1140 0.6049 0.0337
-2.250 0.3635 0.01046 0.00297 -0.1134 0.5671 0.0344
-2.000 0.3893 0.01044 0.00279 -0.1129 0.5411 0.0361
-1.750 0.4156 0.01046 0.00268 -0.1125 0.5209 0.0377
-1.500 0.4425 0.01047 0.00259 -0.1122 0.5061 0.0391
-1.250 0.4697 0.01047 0.00252 -0.1120 0.4936 0.0408
-1.000 0.4968 0.01049 0.00246 -0.1118 0.4807 0.0428
-0.750 0.5239 0.01050 0.00242 -0.1115 0.4665 0.0488
-0.500 0.5505 0.01037 0.00243 -0.1113 0.4504 0.1039
-0.250 0.5771 0.01046 0.00248 -0.1111 0.4297 0.1249
0.000 0.6031 0.01063 0.00254 -0.1107 0.4017 0.1380
0.250 0.6283 0.01088 0.00262 -0.1102 0.3679 0.1470
0.500 0.6535 0.01113 0.00272 -0.1098 0.3392 0.1526
0.750 0.6788 0.01137 0.00284 -0.1093 0.3156 0.1592
1.000 0.7044 0.01158 0.00295 -0.1089 0.2968 0.1671
1.250 0.7304 0.01175 0.00306 -0.1086 0.2826 0.1788
1.750 0.7830 0.01190 0.00333 -0.1082 0.2643 0.2550
2.000 0.8093 0.01192 0.00348 -0.1080 0.2570 0.3257
2.250 0.8323 0.01117 0.00373 -0.1076 0.2512 0.7456
2.750 0.8854 0.01107 0.00398 -0.1068 0.2403 1.0000
3.000 0.9115 0.01128 0.00412 -0.1065 0.2360 1.0000
3.250 0.9378 0.01145 0.00426 -0.1062 0.2325 1.0000
3.500 0.9639 0.01164 0.00441 -0.1059 0.2290 1.0000
3.750 0.9898 0.01184 0.00457 -0.1056 0.2256 1.0000
4.000 1.0153 0.01207 0.00475 -0.1052 0.2223 1.0000
4.250 1.0411 0.01227 0.00494 -0.1049 0.2198 1.0000
4.500 1.0669 0.01246 0.00512 -0.1046 0.2166 1.0000
4.750 1.0924 0.01266 0.00531 -0.1042 0.2132 1.0000
5.000 1.1176 0.01289 0.00552 -0.1039 0.2102 1.0000
5.250 1.1424 0.01314 0.00574 -0.1034 0.2071 1.0000
5.500 1.1673 0.01338 0.00597 -0.1030 0.2044 1.0000
5.750 1.1924 0.01358 0.00619 -0.1026 0.2015 1.0000
6.000 1.2171 0.01381 0.00643 -0.1022 0.1978 1.0000
6.250 1.2412 0.01408 0.00668 -0.1017 0.1934 1.0000
6.500 1.2649 0.01436 0.00695 -0.1011 0.1877 1.0000
6.750 1.2880 0.01468 0.00723 -0.1005 0.1775 1.0000
7.000 1.3096 0.01510 0.00755 -0.0996 0.1594 1.0000
7.250 1.3267 0.01585 0.00807 -0.0982 0.1322 1.0000
7.500 1.3459 0.01640 0.00858 -0.0970 0.1228 1.0000
7.750 1.3654 0.01687 0.00903 -0.0958 0.1178 1.0000
8.000 1.3832 0.01739 0.00953 -0.0943 0.1123 1.0000
8.250 1.4023 0.01782 0.00998 -0.0931 0.1085 1.0000
8.500 1.4206 0.01830 0.01048 -0.0918 0.1043 1.0000
8.750 1.4361 0.01898 0.01112 -0.0901 0.0978 1.0000
9.000 1.4539 0.01949 0.01164 -0.0888 0.0904 1.0000
9.500 1.4535 0.02307 0.01484 -0.0819 0.0151 1.0000
9.750 1.4675 0.02389 0.01573 -0.0803 0.0132 1.0000
10.000 1.4816 0.02471 0.01663 -0.0789 0.0121 1.0000
10.250 1.4944 0.02565 0.01765 -0.0774 0.0111 1.0000
10.500 1.5052 0.02676 0.01885 -0.0757 0.0103 1.0000
10.750 1.5172 0.02780 0.01997 -0.0743 0.0098 1.0000
11.000 1.5283 0.02892 0.02118 -0.0729 0.0093 1.0000
11.250 1.5383 0.03017 0.02253 -0.0715 0.0088 1.0000
11.500 1.5471 0.03154 0.02399 -0.0701 0.0084 1.0000
11.750 1.5539 0.03313 0.02565 -0.0687 0.0079 1.0000
12.000 1.5574 0.03506 0.02769 -0.0671 0.0075 1.0000
12.250 1.5639 0.03675 0.02949 -0.0660 0.0073 1.0000
12.500 1.5680 0.03871 0.03155 -0.0648 0.0071 1.0000
12.750 1.5706 0.04089 0.03383 -0.0637 0.0068 1.0000
13.000 1.5717 0.04330 0.03635 -0.0627 0.0066 1.0000
13.250 1.5710 0.04597 0.03914 -0.0618 0.0064 1.0000
13.500 1.5689 0.04891 0.04221 -0.0612 0.0063 1.0000
13.750 1.5655 0.05219 0.04560 -0.0608 0.0061 1.0000
14.000 1.5604 0.05582 0.04935 -0.0608 0.0060 1.0000
14.250 1.5534 0.05990 0.05356 -0.0610 0.0059 1.0000
14.500 1.5438 0.06454 0.05834 -0.0617 0.0058 1.0000
14.750 1.5315 0.06978 0.06373 -0.0627 0.0057 1.0000
15.000 1.5160 0.07564 0.06973 -0.0640 0.0056 1.0000
15.250 1.4981 0.08202 0.07627 -0.0656 0.0056 1.0000
15.500 1.4780 0.08890 0.08331 -0.0676 0.0056 1.0000
15.750 1.4573 0.09600 0.09057 -0.0697 0.0056 1.0000
16.000 1.4358 0.10347 0.09819 -0.0721 0.0055 1.0000
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