GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.91 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe264-il-1000000.txt Download as CSV file: xf-goe264-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3253 0.09617 0.09464 -0.0220 1.0000 0.0136
-8.000 -0.3211 0.09300 0.09150 -0.0234 1.0000 0.0136
-7.750 -0.3156 0.08972 0.08823 -0.0255 0.9975 0.0137
-7.500 -0.3002 0.08529 0.08380 -0.0295 0.9928 0.0142
-7.250 -0.2794 0.08229 0.08080 -0.0337 0.9863 0.0145
-7.000 -0.2590 0.07907 0.07757 -0.0383 0.9782 0.0151
-6.750 -0.2400 0.07574 0.07422 -0.0427 0.9685 0.0163
-6.500 -0.2150 0.07043 0.06886 -0.0518 0.9561 0.0176
-6.250 -0.1952 0.06585 0.06423 -0.0568 0.9451 0.0177
-6.000 -0.1815 0.06252 0.06086 -0.0583 0.9352 0.0168
-5.750 -0.1569 0.05765 0.05591 -0.0642 0.9247 0.0161
-5.500 -0.1231 0.05023 0.04835 -0.0737 0.9136 0.0168
-5.250 -0.0879 0.04396 0.04193 -0.0815 0.9023 0.0185
-5.000 -0.0647 0.04358 0.04149 -0.0817 0.8893 0.0192
-4.750 -0.0335 0.04021 0.03799 -0.0855 0.8762 0.0203
-4.500 0.0124 0.03141 0.02882 -0.0945 0.8650 0.0236
-4.250 0.0359 0.03198 0.02935 -0.0940 0.8498 0.0243
-4.000 0.0935 0.01505 0.01120 -0.1057 0.8423 0.0303
-3.750 0.1209 0.01521 0.01130 -0.1056 0.8266 0.0310
-3.500 0.1483 0.01534 0.01137 -0.1055 0.8104 0.0318
-3.250 0.1773 0.01459 0.01043 -0.1059 0.7936 0.0330
-3.000 0.2085 0.01262 0.00804 -0.1069 0.7746 0.0343
-2.750 0.2377 0.01190 0.00705 -0.1072 0.7499 0.0353
-2.500 0.2661 0.01178 0.00674 -0.1073 0.7163 0.0362
-2.000 0.3239 0.01077 0.00515 -0.1078 0.6512 0.0372
-1.750 0.3535 0.00972 0.00383 -0.1084 0.6320 0.0382
-1.500 0.3824 0.00937 0.00338 -0.1086 0.6164 0.0393
-1.250 0.4111 0.00923 0.00316 -0.1088 0.6026 0.0404
-0.750 0.4686 0.00902 0.00282 -0.1091 0.5774 0.0432
-0.500 0.4974 0.00890 0.00264 -0.1093 0.5651 0.0444
-0.250 0.5261 0.00879 0.00247 -0.1094 0.5523 0.0453
0.000 0.5548 0.00873 0.00234 -0.1096 0.5395 0.0462
0.250 0.5834 0.00871 0.00228 -0.1097 0.5265 0.0469
0.500 0.6125 0.00848 0.00196 -0.1100 0.5128 0.0496
0.750 0.6412 0.00845 0.00188 -0.1102 0.4974 0.0530
1.000 0.6696 0.00848 0.00185 -0.1103 0.4801 0.0558
1.250 0.6980 0.00853 0.00183 -0.1104 0.4640 0.0581
1.500 0.7264 0.00859 0.00183 -0.1106 0.4501 0.0603
1.750 0.7549 0.00861 0.00182 -0.1107 0.4382 0.0685
2.000 0.7833 0.00866 0.00188 -0.1109 0.4262 0.0861
2.250 0.8116 0.00870 0.00198 -0.1110 0.4142 0.1289
2.500 0.8398 0.00877 0.00207 -0.1112 0.4040 0.1479
2.750 0.8679 0.00886 0.00216 -0.1113 0.3948 0.1643
3.000 0.8961 0.00893 0.00227 -0.1114 0.3854 0.1893
3.250 0.9246 0.00891 0.00242 -0.1117 0.3770 0.2839
3.500 0.9470 0.00774 0.00261 -0.1109 0.3688 1.0000
3.750 0.9751 0.00786 0.00271 -0.1110 0.3613 1.0000
4.000 1.0029 0.00803 0.00283 -0.1110 0.3537 1.0000
4.250 1.0307 0.00818 0.00295 -0.1111 0.3434 1.0000
4.500 1.0583 0.00836 0.00309 -0.1111 0.3313 1.0000
4.750 1.0857 0.00856 0.00323 -0.1112 0.3180 1.0000
5.000 1.1130 0.00877 0.00339 -0.1112 0.3058 1.0000
5.250 1.1402 0.00899 0.00357 -0.1112 0.2941 1.0000
5.500 1.1672 0.00923 0.00375 -0.1111 0.2793 1.0000
5.750 1.1939 0.00951 0.00396 -0.1111 0.2606 1.0000
6.000 1.2198 0.00990 0.00422 -0.1109 0.2341 1.0000
6.250 1.2384 0.01153 0.00518 -0.1100 0.1168 1.0000
6.500 1.2578 0.01299 0.00618 -0.1091 0.0357 1.0000
6.750 1.2817 0.01365 0.00675 -0.1086 0.0200 1.0000
7.000 1.3066 0.01409 0.00721 -0.1082 0.0172 1.0000
7.250 1.3311 0.01457 0.00772 -0.1077 0.0153 1.0000
7.500 1.3538 0.01531 0.00854 -0.1070 0.0134 1.0000
7.750 1.3781 0.01574 0.00901 -0.1065 0.0128 1.0000
8.000 1.4017 0.01623 0.00953 -0.1060 0.0119 1.0000
8.250 1.4246 0.01678 0.01013 -0.1053 0.0111 1.0000
8.500 1.4454 0.01755 0.01096 -0.1044 0.0103 1.0000
8.750 1.4603 0.01894 0.01250 -0.1025 0.0096 1.0000
9.000 1.4814 0.01953 0.01315 -0.1016 0.0093 1.0000
9.250 1.5008 0.02026 0.01394 -0.1004 0.0090 1.0000
9.500 1.5184 0.02109 0.01484 -0.0990 0.0087 1.0000
9.750 1.5347 0.02197 0.01580 -0.0974 0.0083 1.0000
10.000 1.5509 0.02278 0.01668 -0.0959 0.0079 1.0000
10.250 1.5663 0.02358 0.01751 -0.0942 0.0076 1.0000
10.500 1.5773 0.02458 0.01856 -0.0919 0.0073 1.0000
10.750 1.5756 0.02616 0.02024 -0.0876 0.0070 1.0000
11.000 1.5625 0.02864 0.02287 -0.0823 0.0068 1.0000
11.250 1.5620 0.03055 0.02490 -0.0792 0.0067 1.0000
11.500 1.5689 0.03197 0.02641 -0.0773 0.0066 1.0000
11.750 1.5734 0.03372 0.02826 -0.0754 0.0064 1.0000
12.000 1.5769 0.03567 0.03033 -0.0736 0.0063 1.0000
12.250 1.5787 0.03792 0.03268 -0.0721 0.0062 1.0000
12.500 1.5799 0.04033 0.03521 -0.0707 0.0061 1.0000
12.750 1.5800 0.04299 0.03798 -0.0696 0.0060 1.0000
13.000 1.5797 0.04580 0.04090 -0.0687 0.0059 1.0000
13.250 1.5785 0.04879 0.04402 -0.0679 0.0058 1.0000
13.500 1.5769 0.05196 0.04730 -0.0675 0.0057 1.0000
13.750 1.5746 0.05530 0.05076 -0.0672 0.0056 1.0000
14.000 1.5712 0.05885 0.05443 -0.0671 0.0055 1.0000
14.250 1.5680 0.06250 0.05820 -0.0673 0.0054 1.0000
14.500 1.5627 0.06647 0.06230 -0.0675 0.0054 1.0000
14.750 1.5578 0.07049 0.06643 -0.0681 0.0053 1.0000
15.000 1.5513 0.07485 0.07092 -0.0688 0.0052 1.0000
15.250 1.5454 0.07928 0.07546 -0.0699 0.0051 1.0000
15.500 1.5374 0.08404 0.08035 -0.0710 0.0051 1.0000
15.750 1.5301 0.08887 0.08529 -0.0724 0.0050 1.0000
16.000 1.5204 0.09413 0.09068 -0.0739 0.0050 1.0000
16.250 1.5118 0.09940 0.09607 -0.0757 0.0050 1.0000
16.500 1.5011 0.10504 0.10184 -0.0777 0.0049 1.0000
16.750 1.4909 0.11077 0.10768 -0.0799 0.0049 1.0000
17.000 1.4792 0.11690 0.11394 -0.0824 0.0048 1.0000
17.250 1.4670 0.12330 0.12047 -0.0853 0.0048 1.0000
17.500 1.4542 0.12992 0.12722 -0.0884 0.0048 1.0000
17.750 1.4401 0.13702 0.13446 -0.0920 0.0048 1.0000
18.000 1.4259 0.14440 0.14198 -0.0959 0.0047 1.0000
18.250 1.4115 0.15216 0.14988 -0.1004 0.0047 1.0000
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