GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 265 AIRFOIL (goe265-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.53 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe265-il-1000000.txt Download as CSV file: xf-goe265-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2847 0.11214 0.11061 -0.0109 1.0000 0.0137
-9.250 -0.2781 0.10834 0.10682 -0.0132 1.0000 0.0147
-9.000 -0.2723 0.10482 0.10331 -0.0156 1.0000 0.0148
-8.750 -0.2593 0.10097 0.09945 -0.0194 0.9606 0.0148
-8.500 -0.2533 0.09742 0.09574 -0.0202 0.9032 0.0150
-8.250 -0.2446 0.09543 0.09363 -0.0200 0.8711 0.0152
-8.000 -0.2352 0.09337 0.09145 -0.0206 0.8413 0.0154
-7.750 -0.2254 0.09112 0.08908 -0.0216 0.8107 0.0157
-7.500 -0.2155 0.08868 0.08653 -0.0230 0.7823 0.0161
-7.250 -0.2054 0.08609 0.08385 -0.0249 0.7597 0.0167
-7.000 -0.1882 0.08076 0.07845 -0.0334 0.7435 0.0181
-6.750 -0.1705 0.07692 0.07453 -0.0380 0.7282 0.0181
-6.500 -0.1551 0.07264 0.07018 -0.0419 0.7147 0.0184
-6.250 -0.1371 0.07070 0.06818 -0.0433 0.7007 0.0186
-6.000 -0.1166 0.06851 0.06595 -0.0458 0.6893 0.0190
-5.750 -0.0942 0.06606 0.06344 -0.0491 0.6794 0.0198
-5.500 -0.0543 0.05947 0.05675 -0.0614 0.6710 0.0218
-5.250 0.0356 0.01451 0.01003 -0.1116 0.6742 0.0267
-5.000 0.0636 0.01408 0.00952 -0.1116 0.6644 0.0276
-4.750 0.0919 0.01381 0.00918 -0.1116 0.6543 0.0283
-4.500 0.1203 0.01308 0.00827 -0.1117 0.6447 0.0291
-4.000 0.1773 0.01212 0.00698 -0.1118 0.6246 0.0308
-3.750 0.2058 0.01135 0.00596 -0.1119 0.6154 0.0315
-3.500 0.2342 0.01049 0.00490 -0.1120 0.6053 0.0326
-3.250 0.2626 0.01029 0.00465 -0.1119 0.5957 0.0336
-3.000 0.2910 0.01008 0.00433 -0.1117 0.5864 0.0345
-2.750 0.3196 0.00980 0.00395 -0.1116 0.5778 0.0354
-2.500 0.3481 0.00958 0.00362 -0.1115 0.5691 0.0362
-2.250 0.3766 0.00940 0.00336 -0.1114 0.5604 0.0369
-2.000 0.4050 0.00901 0.00285 -0.1113 0.5525 0.0382
-1.750 0.4336 0.00881 0.00261 -0.1112 0.5449 0.0396
-1.500 0.4619 0.00871 0.00246 -0.1111 0.5373 0.0410
-1.250 0.4904 0.00861 0.00231 -0.1109 0.5297 0.0425
-1.000 0.5187 0.00856 0.00219 -0.1108 0.5220 0.0438
-0.750 0.5473 0.00837 0.00198 -0.1107 0.5149 0.0466
-0.500 0.5755 0.00836 0.00193 -0.1105 0.5065 0.0498
-0.250 0.6039 0.00833 0.00187 -0.1104 0.4977 0.0525
0.000 0.6322 0.00829 0.00182 -0.1102 0.4888 0.0587
0.250 0.6605 0.00829 0.00179 -0.1101 0.4804 0.0634
0.500 0.6887 0.00832 0.00182 -0.1100 0.4723 0.0693
0.750 0.7169 0.00839 0.00187 -0.1098 0.4630 0.0729
1.000 0.7450 0.00839 0.00185 -0.1097 0.4529 0.0788
1.250 0.7729 0.00847 0.00190 -0.1096 0.4423 0.0828
1.500 0.8010 0.00855 0.00194 -0.1095 0.4316 0.0855
1.750 0.8289 0.00856 0.00193 -0.1093 0.4203 0.0907
2.000 0.8567 0.00867 0.00200 -0.1092 0.4080 0.0953
2.250 0.8843 0.00880 0.00207 -0.1090 0.3954 0.0990
2.500 0.9119 0.00887 0.00210 -0.1089 0.3834 0.1030
2.750 0.9396 0.00895 0.00217 -0.1088 0.3728 0.1082
3.000 0.9671 0.00908 0.00226 -0.1086 0.3626 0.1125
3.250 0.9945 0.00921 0.00235 -0.1085 0.3525 0.1162
3.500 1.0221 0.00929 0.00243 -0.1083 0.3440 0.1234
3.750 1.0492 0.00945 0.00256 -0.1082 0.3353 0.1291
4.000 1.0768 0.00953 0.00265 -0.1081 0.3284 0.1383
4.250 1.1039 0.00968 0.00279 -0.1079 0.3210 0.1486
4.500 1.1314 0.00975 0.00292 -0.1078 0.3155 0.1664
4.750 1.1587 0.00982 0.00309 -0.1077 0.3094 0.2334
5.000 1.1827 0.00884 0.00340 -0.1073 0.3040 1.0000
5.250 1.2101 0.00897 0.00352 -0.1071 0.2996 1.0000
5.500 1.2371 0.00914 0.00367 -0.1069 0.2944 1.0000
5.750 1.2637 0.00936 0.00385 -0.1067 0.2889 1.0000
6.000 1.2909 0.00949 0.00399 -0.1066 0.2847 1.0000
6.250 1.3176 0.00967 0.00416 -0.1064 0.2789 1.0000
6.500 1.3440 0.00989 0.00435 -0.1062 0.2734 1.0000
6.750 1.3708 0.01004 0.00452 -0.1060 0.2683 1.0000
7.000 1.3969 0.01027 0.00473 -0.1058 0.2615 1.0000
7.250 1.4232 0.01048 0.00493 -0.1056 0.2534 1.0000
7.500 1.4487 0.01077 0.00517 -0.1053 0.2432 1.0000
7.750 1.4740 0.01107 0.00542 -0.1050 0.2309 1.0000
8.000 1.4985 0.01144 0.00573 -0.1046 0.2150 1.0000
8.250 1.5214 0.01200 0.00614 -0.1040 0.1888 1.0000
8.500 1.5401 0.01302 0.00687 -0.1029 0.1462 1.0000
8.750 1.5614 0.01371 0.00746 -0.1021 0.1296 1.0000
9.000 1.5833 0.01428 0.00798 -0.1014 0.1204 1.0000
9.250 1.6071 0.01463 0.00836 -0.1009 0.1172 1.0000
9.500 1.6299 0.01506 0.00880 -0.1003 0.1133 1.0000
9.750 1.6516 0.01558 0.00931 -0.0995 0.1081 1.0000
10.000 1.6748 0.01593 0.00969 -0.0990 0.1049 1.0000
10.250 1.6972 0.01632 0.01011 -0.0984 0.1006 1.0000
10.500 1.7171 0.01693 0.01069 -0.0974 0.0934 1.0000
10.750 1.7380 0.01740 0.01114 -0.0966 0.0839 1.0000
11.000 1.7436 0.01913 0.01253 -0.0939 0.0467 1.0000
11.250 1.7393 0.02137 0.01457 -0.0900 0.0188 1.0000
11.500 1.7454 0.02245 0.01570 -0.0871 0.0160 1.0000
11.750 1.7529 0.02349 0.01680 -0.0846 0.0146 1.0000
12.000 1.7603 0.02463 0.01802 -0.0824 0.0137 1.0000
12.250 1.7651 0.02609 0.01954 -0.0804 0.0129 1.0000
12.500 1.7671 0.02795 0.02150 -0.0786 0.0121 1.0000
12.750 1.7714 0.02978 0.02342 -0.0772 0.0117 1.0000
13.000 1.7765 0.03167 0.02540 -0.0763 0.0113 1.0000
13.250 1.7797 0.03388 0.02770 -0.0755 0.0110 1.0000
13.500 1.7817 0.03636 0.03028 -0.0749 0.0106 1.0000
13.750 1.7815 0.03917 0.03318 -0.0745 0.0103 1.0000
14.000 1.7787 0.04235 0.03646 -0.0743 0.0099 1.0000
14.250 1.7719 0.04610 0.04032 -0.0741 0.0096 1.0000
14.500 1.7597 0.05059 0.04494 -0.0742 0.0094 1.0000
14.750 1.7460 0.05539 0.04987 -0.0744 0.0092 1.0000
15.000 1.7404 0.05917 0.05375 -0.0746 0.0091 1.0000
15.250 1.7331 0.06325 0.05794 -0.0750 0.0089 1.0000
15.500 1.7238 0.06773 0.06253 -0.0755 0.0088 1.0000
15.750 1.7130 0.07252 0.06743 -0.0762 0.0087 1.0000
16.000 1.7021 0.07744 0.07246 -0.0771 0.0086 1.0000
16.250 1.6901 0.08260 0.07773 -0.0781 0.0085 1.0000
16.500 1.6771 0.08799 0.08323 -0.0793 0.0084 1.0000
16.750 1.6641 0.09349 0.08884 -0.0806 0.0083 1.0000
17.000 1.6512 0.09904 0.09450 -0.0820 0.0082 1.0000
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