GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 123 AIRFOIL (goe123-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.12 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe123-il-1000000.txt Download as CSV file: xf-goe123-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 123 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2759 0.08770 0.08611 -0.0362 0.9571 0.0128
-7.500 -0.2673 0.08524 0.08362 -0.0372 0.9461 0.0129
-7.250 -0.2554 0.08277 0.08112 -0.0390 0.9370 0.0132
-7.000 -0.2417 0.08018 0.07851 -0.0416 0.9284 0.0136
-6.750 -0.2257 0.07724 0.07553 -0.0449 0.9208 0.0143
-6.500 -0.2018 0.07332 0.07155 -0.0517 0.9125 0.0157
-6.250 -0.1745 0.06897 0.06714 -0.0598 0.9045 0.0159
-6.000 -0.1499 0.06504 0.06314 -0.0652 0.8972 0.0159
-5.750 -0.1300 0.06015 0.05820 -0.0693 0.8902 0.0161
-5.500 -0.1129 0.05785 0.05586 -0.0701 0.8833 0.0164
-5.250 -0.0906 0.05560 0.05357 -0.0724 0.8770 0.0168
-5.000 -0.0646 0.05298 0.05090 -0.0757 0.8707 0.0177
-4.750 -0.0209 0.04916 0.04691 -0.0834 0.8654 0.0197
-4.500 0.0123 0.04558 0.04324 -0.0878 0.8598 0.0198
-4.250 0.0445 0.04203 0.03958 -0.0914 0.8544 0.0199
-4.000 0.0685 0.03787 0.03531 -0.0942 0.8492 0.0204
-3.750 0.0940 0.03608 0.03348 -0.0956 0.8429 0.0208
-3.500 0.1217 0.03422 0.03152 -0.0971 0.8362 0.0215
-3.250 0.1518 0.03211 0.02932 -0.0990 0.8281 0.0226
-3.000 0.1905 0.02982 0.02680 -0.1010 0.8205 0.0247
-2.750 0.2229 0.02725 0.02408 -0.1025 0.8122 0.0248
-2.500 0.2550 0.02239 0.01891 -0.1049 0.8058 0.0254
-2.250 0.2823 0.02112 0.01757 -0.1056 0.7987 0.0259
-2.000 0.3101 0.01999 0.01633 -0.1062 0.7922 0.0264
-1.750 0.3388 0.01880 0.01504 -0.1067 0.7856 0.0271
0.000 0.5429 0.01146 0.00658 -0.1081 0.7292 0.0398
0.250 0.5713 0.00983 0.00472 -0.1084 0.7158 0.0433
0.500 0.5989 0.00961 0.00443 -0.1084 0.6998 0.0459
0.750 0.6269 0.00936 0.00407 -0.1083 0.6834 0.0486
1.000 0.6546 0.00951 0.00412 -0.1080 0.6642 0.0505
1.250 0.6836 0.00773 0.00200 -0.1076 0.6455 0.0320
1.500 0.7109 0.00757 0.00174 -0.1075 0.6211 0.0325
1.750 0.7381 0.00754 0.00160 -0.1074 0.5940 0.0329
2.000 0.7649 0.00760 0.00154 -0.1072 0.5640 0.0333
2.250 0.7916 0.00771 0.00153 -0.1071 0.5332 0.0345
2.500 0.8183 0.00785 0.00155 -0.1069 0.5046 0.0353
2.750 0.8452 0.00798 0.00159 -0.1067 0.4816 0.0362
3.000 0.8722 0.00811 0.00164 -0.1066 0.4587 0.0383
3.250 0.8989 0.00829 0.00171 -0.1064 0.4346 0.0421
3.500 0.9256 0.00840 0.00188 -0.1063 0.4097 0.1063
3.750 0.9519 0.00862 0.00206 -0.1062 0.3843 0.1446
4.000 0.9779 0.00887 0.00224 -0.1060 0.3565 0.1654
4.250 0.9994 0.00774 0.00257 -0.1052 0.3351 1.0000
4.500 1.0256 0.00801 0.00274 -0.1050 0.3161 1.0000
4.750 1.0517 0.00827 0.00291 -0.1048 0.2978 1.0000
5.000 1.0778 0.00853 0.00310 -0.1045 0.2801 1.0000
5.250 1.1037 0.00881 0.00329 -0.1043 0.2622 1.0000
5.500 1.1292 0.00912 0.00350 -0.1040 0.2412 1.0000
5.750 1.1541 0.00951 0.00376 -0.1037 0.2151 1.0000
6.000 1.1779 0.01002 0.00408 -0.1032 0.1801 1.0000
6.250 1.2012 0.01059 0.00446 -0.1026 0.1475 1.0000
6.500 1.2209 0.01159 0.00509 -0.1016 0.0865 1.0000
6.750 1.2441 0.01215 0.00557 -0.1010 0.0663 1.0000
7.000 1.2643 0.01308 0.00626 -0.0999 0.0299 1.0000
7.250 1.2882 0.01351 0.00671 -0.0994 0.0253 1.0000
7.500 1.3109 0.01409 0.00729 -0.0986 0.0213 1.0000
7.750 1.3343 0.01454 0.00779 -0.0980 0.0196 1.0000
8.000 1.3577 0.01496 0.00825 -0.0974 0.0180 1.0000
8.250 1.3798 0.01552 0.00881 -0.0966 0.0162 1.0000
8.500 1.4005 0.01623 0.00959 -0.0956 0.0148 1.0000
8.750 1.4228 0.01669 0.01009 -0.0949 0.0141 1.0000
9.000 1.4444 0.01721 0.01066 -0.0940 0.0133 1.0000
9.250 1.4652 0.01778 0.01126 -0.0931 0.0125 1.0000
9.500 1.4832 0.01860 0.01213 -0.0918 0.0117 1.0000
9.750 1.4960 0.01986 0.01351 -0.0896 0.0110 1.0000
10.000 1.5159 0.02037 0.01407 -0.0886 0.0107 1.0000
10.250 1.5340 0.02100 0.01476 -0.0873 0.0102 1.0000
10.500 1.5503 0.02173 0.01555 -0.0857 0.0098 1.0000
10.750 1.5641 0.02250 0.01639 -0.0838 0.0094 1.0000
11.000 1.5757 0.02330 0.01724 -0.0815 0.0090 1.0000
11.250 1.5851 0.02426 0.01826 -0.0791 0.0087 1.0000
11.500 1.5892 0.02565 0.01974 -0.0761 0.0084 1.0000
11.750 1.5814 0.02805 0.02230 -0.0720 0.0081 1.0000
12.000 1.5837 0.02979 0.02415 -0.0694 0.0079 1.0000
12.250 1.5917 0.03113 0.02558 -0.0677 0.0078 1.0000
12.500 1.5980 0.03266 0.02721 -0.0659 0.0077 1.0000
12.750 1.6024 0.03442 0.02908 -0.0641 0.0075 1.0000
13.000 1.6056 0.03636 0.03113 -0.0624 0.0074 1.0000
13.250 1.6080 0.03845 0.03332 -0.0609 0.0072 1.0000
13.500 1.6094 0.04071 0.03569 -0.0595 0.0071 1.0000
13.750 1.6113 0.04300 0.03809 -0.0584 0.0069 1.0000
14.000 1.6130 0.04539 0.04058 -0.0575 0.0067 1.0000
14.250 1.6138 0.04795 0.04324 -0.0568 0.0066 1.0000
14.500 1.6142 0.05065 0.04603 -0.0563 0.0064 1.0000
14.750 1.6122 0.05375 0.04923 -0.0560 0.0063 1.0000
15.000 1.6093 0.05705 0.05262 -0.0559 0.0062 1.0000
15.250 1.6035 0.06090 0.05659 -0.0561 0.0061 1.0000
15.500 1.5959 0.06520 0.06101 -0.0565 0.0060 1.0000
15.750 1.5863 0.06993 0.06586 -0.0573 0.0059 1.0000
16.000 1.5745 0.07515 0.07122 -0.0584 0.0059 1.0000
16.250 1.5586 0.08118 0.07739 -0.0599 0.0058 1.0000
16.500 1.5428 0.08734 0.08371 -0.0616 0.0057 1.0000
16.750 1.5227 0.09434 0.09088 -0.0637 0.0057 1.0000
17.000 1.5020 0.10172 0.09843 -0.0663 0.0056 1.0000
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Polar data table (+)
Polar graphs
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