GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 265 AIRFOIL (goe265-il) Reynolds number: 500,000 Max Cl/Cd: 111.23 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe265-il-500000.txt Download as CSV file: xf-goe265-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2490 0.10202 0.09994 -0.0191 1.0000 0.0218
-8.250 -0.2454 0.09933 0.09730 -0.0220 1.0000 0.0218
-8.000 -0.2388 0.09582 0.09383 -0.0235 0.9967 0.0220
-7.750 -0.2162 0.09179 0.08978 -0.0255 0.9652 0.0223
-7.500 -0.1978 0.08877 0.08668 -0.0281 0.9226 0.0227
-7.250 -0.1892 0.08653 0.08433 -0.0287 0.8870 0.0232
-7.000 -0.1783 0.08405 0.08173 -0.0303 0.8587 0.0239
-6.750 -0.1642 0.08111 0.07870 -0.0333 0.8327 0.0251
-6.500 -0.1340 0.07638 0.07382 -0.0475 0.8088 0.0262
-6.250 -0.1251 0.07302 0.07039 -0.0455 0.7893 0.0265
-6.000 -0.1098 0.07071 0.06798 -0.0460 0.7704 0.0269
-5.750 -0.0905 0.06827 0.06544 -0.0483 0.7529 0.0276
-5.500 -0.0681 0.06550 0.06257 -0.0518 0.7370 0.0288
-5.250 -0.0156 0.05978 0.05665 -0.0680 0.7242 0.0312
-5.000 -0.0027 0.05657 0.05339 -0.0675 0.7125 0.0317
-4.750 0.0163 0.05489 0.05164 -0.0676 0.7012 0.0325
-4.500 0.0429 0.05257 0.04926 -0.0705 0.6906 0.0341
-4.250 0.0989 0.04614 0.04257 -0.0840 0.6820 0.0375
-4.000 0.1183 0.04446 0.04086 -0.0838 0.6717 0.0381
-3.750 0.1421 0.04301 0.03935 -0.0846 0.6620 0.0394
-3.500 0.1994 0.03901 0.03504 -0.0938 0.6528 0.0440
-3.250 0.2217 0.03570 0.03168 -0.0954 0.6439 0.0451
-3.000 0.2461 0.03455 0.03045 -0.0957 0.6348 0.0462
-2.750 0.2764 0.03295 0.02876 -0.0974 0.6253 0.0493
-2.500 0.3437 0.01653 0.01095 -0.1097 0.6211 0.0438
-2.250 0.3744 0.01335 0.00712 -0.1110 0.6130 0.0454
-2.000 0.4025 0.01316 0.00685 -0.1108 0.6041 0.0468
-1.750 0.4312 0.01257 0.00611 -0.1108 0.5956 0.0483
-1.500 0.4597 0.01202 0.00534 -0.1107 0.5871 0.0499
-1.250 0.4883 0.01157 0.00473 -0.1106 0.5783 0.0515
-1.000 0.5165 0.01106 0.00404 -0.1105 0.5704 0.0539
-0.750 0.5449 0.01094 0.00393 -0.1104 0.5622 0.0564
-0.500 0.5729 0.01083 0.00372 -0.1102 0.5543 0.0594
-0.250 0.6013 0.01063 0.00344 -0.1100 0.5458 0.0625
0.000 0.6292 0.01053 0.00332 -0.1098 0.5378 0.0671
0.250 0.6574 0.01056 0.00332 -0.1096 0.5295 0.0722
0.500 0.6853 0.01049 0.00321 -0.1095 0.5214 0.0781
0.750 0.7133 0.01053 0.00323 -0.1093 0.5117 0.0836
1.000 0.7411 0.01045 0.00310 -0.1091 0.5020 0.0891
1.250 0.7688 0.01053 0.00316 -0.1089 0.4920 0.0946
1.500 0.7967 0.01059 0.00318 -0.1087 0.4819 0.0994
1.750 0.8243 0.01051 0.00309 -0.1085 0.4720 0.1052
2.000 0.8519 0.01057 0.00312 -0.1083 0.4612 0.1108
2.250 0.8796 0.01062 0.00313 -0.1082 0.4508 0.1146
2.500 0.9070 0.01058 0.00309 -0.1080 0.4403 0.1208
2.750 0.9343 0.01066 0.00313 -0.1078 0.4289 0.1262
3.000 0.9617 0.01071 0.00315 -0.1076 0.4172 0.1311
3.250 0.9889 0.01077 0.00322 -0.1074 0.4059 0.1384
3.500 1.0159 0.01091 0.00331 -0.1072 0.3953 0.1453
3.750 1.0430 0.01099 0.00341 -0.1070 0.3852 0.1546
4.000 1.0701 0.01110 0.00353 -0.1068 0.3763 0.1665
4.250 1.0967 0.01126 0.00369 -0.1066 0.3670 0.1865
4.500 1.1238 0.01122 0.00392 -0.1066 0.3584 0.3155
4.750 1.1475 0.01041 0.00413 -0.1059 0.3509 1.0000
5.000 1.1745 0.01058 0.00428 -0.1057 0.3441 1.0000
5.250 1.2007 0.01084 0.00449 -0.1054 0.3374 1.0000
5.500 1.2273 0.01105 0.00469 -0.1051 0.3315 1.0000
5.750 1.2536 0.01127 0.00489 -0.1049 0.3257 1.0000
6.000 1.2793 0.01158 0.00515 -0.1045 0.3202 1.0000
6.250 1.3059 0.01175 0.00536 -0.1043 0.3148 1.0000
6.500 1.3319 0.01199 0.00560 -0.1040 0.3092 1.0000
6.750 1.3573 0.01230 0.00589 -0.1036 0.3040 1.0000
7.000 1.3836 0.01247 0.00612 -0.1034 0.2987 1.0000
7.250 1.4091 0.01274 0.00638 -0.1031 0.2929 1.0000
7.500 1.4343 0.01302 0.00667 -0.1027 0.2876 1.0000
7.750 1.4602 0.01323 0.00694 -0.1024 0.2815 1.0000
8.000 1.4845 0.01357 0.00725 -0.1020 0.2738 1.0000
8.250 1.5101 0.01377 0.00750 -0.1017 0.2647 1.0000
8.500 1.5345 0.01408 0.00782 -0.1012 0.2547 1.0000
8.750 1.5582 0.01445 0.00817 -0.1007 0.2427 1.0000
9.000 1.5815 0.01485 0.00855 -0.1002 0.2279 1.0000
9.250 1.6032 0.01540 0.00901 -0.0995 0.2052 1.0000
9.500 1.6208 0.01633 0.00974 -0.0983 0.1712 1.0000
9.750 1.6368 0.01738 0.01061 -0.0969 0.1461 1.0000
10.000 1.6543 0.01822 0.01139 -0.0957 0.1352 1.0000
10.250 1.6730 0.01889 0.01209 -0.0946 0.1291 1.0000
10.500 1.6899 0.01967 0.01289 -0.0933 0.1234 1.0000
10.750 1.7069 0.02039 0.01365 -0.0920 0.1176 1.0000
11.000 1.7227 0.02115 0.01444 -0.0905 0.1117 1.0000
11.250 1.7358 0.02203 0.01534 -0.0888 0.1053 1.0000
11.500 1.7490 0.02273 0.01609 -0.0869 0.0977 1.0000
11.750 1.7585 0.02367 0.01702 -0.0847 0.0848 1.0000
12.000 1.7508 0.02590 0.01898 -0.0812 0.0539 1.0000
12.250 1.7350 0.02913 0.02209 -0.0780 0.0321 1.0000
12.500 1.7255 0.03230 0.02525 -0.0761 0.0234 1.0000
12.750 1.7226 0.03512 0.02816 -0.0751 0.0208 1.0000
13.000 1.7179 0.03836 0.03149 -0.0745 0.0191 1.0000
13.250 1.7160 0.04142 0.03468 -0.0741 0.0182 1.0000
13.500 1.7122 0.04477 0.03816 -0.0738 0.0175 1.0000
13.750 1.7057 0.04853 0.04204 -0.0738 0.0168 1.0000
14.000 1.6968 0.05267 0.04632 -0.0738 0.0164 1.0000
14.250 1.6852 0.05723 0.05100 -0.0741 0.0159 1.0000
14.500 1.6710 0.06224 0.05614 -0.0746 0.0156 1.0000
14.750 1.6553 0.06758 0.06162 -0.0753 0.0153 1.0000
15.000 1.6385 0.07328 0.06745 -0.0762 0.0150 1.0000
15.250 1.6282 0.07818 0.07248 -0.0771 0.0149 1.0000
15.500 1.6164 0.08337 0.07780 -0.0781 0.0147 1.0000
15.750 1.6040 0.08877 0.08333 -0.0793 0.0145 1.0000
16.000 1.5916 0.09427 0.08895 -0.0806 0.0143 1.0000
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