GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 265 AIRFOIL (goe265-il) Reynolds number: 200,000 Max Cl/Cd: 79.26 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe265-il-200000.txt Download as CSV file: xf-goe265-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2402 0.10526 0.10197 -0.0183 1.0000 0.0361
-8.250 -0.2369 0.10408 0.10086 -0.0218 1.0000 0.0369
-8.000 -0.2412 0.10380 0.10069 -0.0250 1.0000 0.0371
-7.750 -0.2245 0.09760 0.09450 -0.0231 1.0000 0.0376
-7.500 -0.2167 0.09473 0.09168 -0.0225 1.0000 0.0383
-7.250 -0.2194 0.09324 0.09031 -0.0211 1.0000 0.0389
-7.000 -0.1964 0.08963 0.08672 -0.0263 0.9880 0.0402
-6.750 -0.1635 0.08538 0.08244 -0.0348 0.9706 0.0425
-6.500 -0.1082 0.08197 0.07892 -0.0581 0.9425 0.0441
-6.250 -0.0990 0.07683 0.07378 -0.0531 0.9269 0.0447
-6.000 -0.0837 0.07375 0.07065 -0.0526 0.9060 0.0459
-5.750 -0.0665 0.07121 0.06804 -0.0543 0.8836 0.0480
-5.500 -0.0389 0.06864 0.06533 -0.0607 0.8632 0.0513
-5.250 0.0023 0.06502 0.06151 -0.0731 0.8451 0.0526
-5.000 0.0098 0.06180 0.05826 -0.0697 0.8293 0.0533
-4.750 0.0259 0.05925 0.05563 -0.0695 0.8136 0.0546
-4.500 0.0493 0.05685 0.05311 -0.0716 0.7979 0.0577
-4.250 0.1099 0.05337 0.04929 -0.0861 0.7827 0.0623
-4.000 0.1214 0.05034 0.04623 -0.0841 0.7687 0.0632
-3.750 0.1410 0.04803 0.04385 -0.0841 0.7557 0.0649
-3.500 0.2013 0.04696 0.04233 -0.0941 0.7434 0.0729
-3.250 0.2235 0.04272 0.03799 -0.0956 0.7331 0.0740
-3.000 0.2422 0.04033 0.03559 -0.0952 0.7217 0.0753
-2.750 0.2670 0.03847 0.03363 -0.0958 0.7116 0.0778
-2.500 0.3215 0.03689 0.03152 -0.1024 0.7014 0.0864
-2.250 0.3416 0.03400 0.02867 -0.1025 0.6914 0.0877
-2.000 0.3661 0.03231 0.02688 -0.1027 0.6825 0.0898
-1.750 0.4124 0.03244 0.02648 -0.1057 0.6719 0.1000
-1.500 0.4346 0.02891 0.02300 -0.1064 0.6636 0.1019
-1.250 0.4606 0.02740 0.02144 -0.1067 0.6540 0.1043
-1.000 0.5003 0.02761 0.02110 -0.1079 0.6447 0.1148
-0.750 0.5244 0.02468 0.01823 -0.1086 0.6363 0.1173
-0.500 0.5673 0.02015 0.01278 -0.1103 0.6285 0.0857
-0.250 0.5971 0.01832 0.01061 -0.1107 0.6201 0.0873
0.000 0.6237 0.01821 0.01058 -0.1106 0.6100 0.0923
0.250 0.6533 0.01726 0.00927 -0.1105 0.6019 0.0964
0.500 0.6825 0.01642 0.00818 -0.1104 0.5920 0.1022
0.750 0.7098 0.01628 0.00800 -0.1101 0.5830 0.1096
1.000 0.7381 0.01580 0.00731 -0.1099 0.5733 0.1170
1.250 0.7654 0.01567 0.00716 -0.1096 0.5631 0.1256
1.500 0.7930 0.01542 0.00674 -0.1093 0.5541 0.1332
1.750 0.8204 0.01529 0.00661 -0.1090 0.5432 0.1413
2.000 0.8477 0.01511 0.00636 -0.1087 0.5334 0.1482
2.250 0.8748 0.01507 0.00624 -0.1084 0.5237 0.1563
2.500 0.9017 0.01491 0.00611 -0.1080 0.5123 0.1626
2.750 0.9285 0.01490 0.00607 -0.1077 0.5011 0.1718
3.000 0.9551 0.01485 0.00597 -0.1073 0.4904 0.1805
3.250 0.9817 0.01481 0.00596 -0.1069 0.4784 0.1902
3.500 1.0083 0.01483 0.00602 -0.1066 0.4674 0.2040
3.750 1.0347 0.01487 0.00606 -0.1062 0.4582 0.2227
4.000 1.0610 0.01487 0.00619 -0.1058 0.4481 0.2568
4.250 1.0868 0.01395 0.00629 -0.1053 0.4395 1.0000
4.500 1.1132 0.01420 0.00642 -0.1049 0.4307 1.0000
4.750 1.1395 0.01448 0.00665 -0.1046 0.4222 1.0000
5.000 1.1655 0.01477 0.00684 -0.1042 0.4143 1.0000
5.250 1.1916 0.01506 0.00713 -0.1038 0.4063 1.0000
5.500 1.2175 0.01537 0.00739 -0.1035 0.3994 1.0000
5.750 1.2434 0.01571 0.00772 -0.1031 0.3926 1.0000
6.000 1.2690 0.01601 0.00803 -0.1027 0.3855 1.0000
6.250 1.2945 0.01638 0.00836 -0.1023 0.3791 1.0000
6.500 1.3197 0.01668 0.00870 -0.1019 0.3716 1.0000
6.750 1.3450 0.01708 0.00904 -0.1015 0.3654 1.0000
7.000 1.3698 0.01739 0.00947 -0.1011 0.3584 1.0000
7.250 1.3946 0.01778 0.00981 -0.1006 0.3521 1.0000
7.500 1.4192 0.01815 0.01028 -0.1001 0.3457 1.0000
7.750 1.4436 0.01851 0.01071 -0.0996 0.3394 1.0000
8.000 1.4679 0.01897 0.01116 -0.0991 0.3336 1.0000
8.250 1.4915 0.01932 0.01165 -0.0985 0.3267 1.0000
8.500 1.5153 0.01978 0.01207 -0.0980 0.3204 1.0000
8.750 1.5379 0.02015 0.01263 -0.0973 0.3130 1.0000
9.000 1.5605 0.02057 0.01306 -0.0966 0.3055 1.0000
9.250 1.5814 0.02091 0.01357 -0.0956 0.2954 1.0000
9.500 1.6014 0.02129 0.01403 -0.0946 0.2839 1.0000
9.750 1.6203 0.02170 0.01448 -0.0934 0.2713 1.0000
10.000 1.6382 0.02217 0.01502 -0.0921 0.2576 1.0000
10.250 1.6549 0.02271 0.01564 -0.0907 0.2412 1.0000
10.500 1.6698 0.02338 0.01637 -0.0891 0.2231 1.0000
10.750 1.6822 0.02425 0.01724 -0.0873 0.2059 1.0000
11.000 1.6925 0.02527 0.01824 -0.0852 0.1910 1.0000
11.250 1.6991 0.02637 0.01934 -0.0827 0.1787 1.0000
11.500 1.7037 0.02763 0.02062 -0.0801 0.1685 1.0000
11.750 1.7058 0.02918 0.02216 -0.0777 0.1604 1.0000
12.000 1.7105 0.03070 0.02378 -0.0758 0.1526 1.0000
12.250 1.7100 0.03275 0.02584 -0.0740 0.1455 1.0000
12.500 1.7110 0.03486 0.02803 -0.0726 0.1376 1.0000
12.750 1.7091 0.03739 0.03061 -0.0715 0.1313 1.0000
13.000 1.7086 0.03995 0.03328 -0.0707 0.1245 1.0000
13.250 1.7037 0.04310 0.03649 -0.0701 0.1182 1.0000
13.500 1.7002 0.04628 0.03980 -0.0698 0.1098 1.0000
13.750 1.6953 0.04977 0.04341 -0.0698 0.0991 1.0000
14.000 1.6866 0.05389 0.04758 -0.0701 0.0822 1.0000
14.250 1.6686 0.05923 0.05284 -0.0706 0.0615 1.0000
14.500 1.6465 0.06520 0.05876 -0.0714 0.0518 1.0000
14.750 1.6263 0.07111 0.06471 -0.0722 0.0456 1.0000
15.000 1.6071 0.07714 0.07080 -0.0734 0.0415 1.0000
15.250 1.5902 0.08301 0.07676 -0.0746 0.0386 1.0000
15.500 1.5726 0.08917 0.08301 -0.0760 0.0366 1.0000
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Polar data table (+)
Polar graphs
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