GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 500,000 Max Cl/Cd: 106.84 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe264-il-500000.txt Download as CSV file: xf-goe264-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3110 0.09615 0.09400 -0.0216 1.0000 0.0198
-7.750 -0.3059 0.09353 0.09140 -0.0225 1.0000 0.0205
-7.500 -0.3078 0.09151 0.08943 -0.0220 1.0000 0.0216
-7.250 -0.2075 0.07213 0.07020 -0.0413 0.9879 0.0227
-7.000 -0.2878 0.08554 0.08350 -0.0341 0.9954 0.0226
-6.750 -0.2573 0.08033 0.07827 -0.0428 0.9918 0.0227
-6.500 -0.2403 0.07460 0.07254 -0.0455 0.9886 0.0232
-6.250 -0.2150 0.07129 0.06921 -0.0489 0.9860 0.0238
-6.000 -0.1835 0.06765 0.06553 -0.0551 0.9832 0.0250
-5.750 -0.1513 0.06370 0.06154 -0.0621 0.9761 0.0273
-5.500 -0.0925 0.05793 0.05560 -0.0779 0.9701 0.0288
-5.250 -0.0705 0.05172 0.04933 -0.0827 0.9607 0.0295
-5.000 -0.0521 0.04978 0.04737 -0.0826 0.9521 0.0302
-4.750 -0.0298 0.04772 0.04526 -0.0838 0.9423 0.0315
-4.500 0.0170 0.04500 0.04232 -0.0904 0.9315 0.0366
-4.250 0.0495 0.04123 0.03838 -0.0938 0.9213 0.0368
-4.000 0.0725 0.03569 0.03271 -0.0969 0.9109 0.0382
-3.750 0.0943 0.03453 0.03150 -0.0968 0.8982 0.0395
-3.500 0.1211 0.03301 0.02988 -0.0976 0.8849 0.0426
-3.250 0.1635 0.03112 0.02765 -0.1000 0.8714 0.0469
-3.000 0.1961 0.02520 0.02139 -0.1037 0.8582 0.0487
-2.750 0.2209 0.02435 0.02046 -0.1038 0.8414 0.0500
-2.500 0.2484 0.02325 0.01920 -0.1042 0.8241 0.0519
-2.250 0.2791 0.02177 0.01749 -0.1050 0.8054 0.0558
-2.000 0.3156 0.01846 0.01363 -0.1069 0.7861 0.0616
-1.750 0.3531 0.01333 0.00765 -0.1088 0.7665 0.0497
-1.500 0.3824 0.01232 0.00633 -0.1090 0.7394 0.0498
-1.250 0.4106 0.01183 0.00560 -0.1090 0.7083 0.0509
-1.000 0.4387 0.01152 0.00506 -0.1090 0.6788 0.0525
-0.750 0.4671 0.01111 0.00444 -0.1090 0.6554 0.0537
-0.500 0.4955 0.01083 0.00398 -0.1090 0.6363 0.0551
-0.250 0.5238 0.01060 0.00361 -0.1091 0.6198 0.0564
0.000 0.5522 0.01042 0.00331 -0.1092 0.6049 0.0578
0.250 0.5806 0.01031 0.00312 -0.1092 0.5910 0.0591
0.500 0.6094 0.01000 0.00274 -0.1094 0.5773 0.0626
0.750 0.6379 0.00990 0.00261 -0.1096 0.5631 0.0662
1.000 0.6663 0.00986 0.00252 -0.1097 0.5490 0.0696
1.250 0.6947 0.00985 0.00246 -0.1098 0.5350 0.0730
1.500 0.7233 0.00980 0.00241 -0.1099 0.5208 0.0815
1.750 0.7515 0.00982 0.00244 -0.1100 0.5062 0.0982
2.000 0.7797 0.00986 0.00253 -0.1102 0.4913 0.1417
2.250 0.8077 0.00994 0.00261 -0.1102 0.4762 0.1680
2.500 0.8356 0.01003 0.00271 -0.1103 0.4616 0.1934
2.750 0.8637 0.01005 0.00285 -0.1105 0.4480 0.2633
3.000 0.8840 0.00880 0.00297 -0.1091 0.4365 1.0000
3.250 0.9116 0.00901 0.00308 -0.1091 0.4252 1.0000
3.500 0.9393 0.00920 0.00321 -0.1091 0.4149 1.0000
3.750 0.9669 0.00938 0.00336 -0.1091 0.4057 1.0000
4.000 0.9942 0.00961 0.00352 -0.1091 0.3971 1.0000
4.250 1.0219 0.00978 0.00369 -0.1091 0.3886 1.0000
4.500 1.0491 0.01000 0.00389 -0.1091 0.3809 1.0000
4.750 1.0764 0.01020 0.00407 -0.1090 0.3717 1.0000
5.000 1.1035 0.01040 0.00424 -0.1090 0.3585 1.0000
5.250 1.1303 0.01062 0.00442 -0.1089 0.3447 1.0000
5.500 1.1571 0.01085 0.00463 -0.1088 0.3311 1.0000
5.750 1.1838 0.01108 0.00485 -0.1087 0.3182 1.0000
6.000 1.2103 0.01134 0.00509 -0.1086 0.3046 1.0000
6.250 1.2363 0.01165 0.00536 -0.1084 0.2853 1.0000
6.500 1.2611 0.01213 0.00569 -0.1082 0.2513 1.0000
6.750 1.2721 0.01475 0.00726 -0.1064 0.0727 1.0000
7.000 1.2906 0.01619 0.00844 -0.1051 0.0293 1.0000
7.250 1.3129 0.01697 0.00927 -0.1043 0.0240 1.0000
7.500 1.3355 0.01763 0.00999 -0.1036 0.0213 1.0000
7.750 1.3544 0.01874 0.01120 -0.1023 0.0190 1.0000
8.000 1.3737 0.01969 0.01226 -0.1010 0.0181 1.0000
8.250 1.3928 0.02057 0.01323 -0.0997 0.0172 1.0000
8.500 1.4109 0.02149 0.01423 -0.0984 0.0162 1.0000
8.750 1.4278 0.02243 0.01524 -0.0969 0.0151 1.0000
9.000 1.4400 0.02374 0.01662 -0.0948 0.0143 1.0000
9.250 1.4418 0.02582 0.01883 -0.0911 0.0137 1.0000
9.500 1.4456 0.02755 0.02067 -0.0877 0.0134 1.0000
9.750 1.4530 0.02872 0.02193 -0.0847 0.0131 1.0000
10.000 1.4588 0.03010 0.02342 -0.0818 0.0129 1.0000
10.250 1.4641 0.03169 0.02512 -0.0790 0.0126 1.0000
10.500 1.4694 0.03344 0.02697 -0.0765 0.0123 1.0000
10.750 1.4751 0.03532 0.02897 -0.0742 0.0120 1.0000
11.000 1.4814 0.03722 0.03099 -0.0720 0.0117 1.0000
11.250 1.4877 0.03909 0.03296 -0.0702 0.0113 1.0000
11.500 1.4936 0.04094 0.03489 -0.0686 0.0110 1.0000
11.750 1.4981 0.04297 0.03701 -0.0671 0.0106 1.0000
12.000 1.5021 0.04518 0.03930 -0.0657 0.0103 1.0000
12.250 1.5060 0.04778 0.04200 -0.0640 0.0101 1.0000
12.500 1.5098 0.05079 0.04514 -0.0622 0.0099 1.0000
12.750 1.5116 0.05430 0.04884 -0.0604 0.0098 1.0000
13.000 1.5096 0.05806 0.05282 -0.0589 0.0098 1.0000
13.250 1.5039 0.06207 0.05705 -0.0577 0.0098 1.0000
13.500 1.4959 0.06619 0.06137 -0.0569 0.0098 1.0000
13.750 1.4860 0.07050 0.06589 -0.0566 0.0098 1.0000
14.000 1.4756 0.07490 0.07048 -0.0568 0.0098 1.0000
14.250 1.4631 0.07974 0.07552 -0.0575 0.0098 1.0000
14.500 1.4516 0.08453 0.08048 -0.0586 0.0099 1.0000
14.750 1.4373 0.09000 0.08614 -0.0603 0.0099 1.0000
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Polar data table (+)
Polar graphs
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