GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 269 AIRFOIL (goe269-il) Reynolds number: 500,000 Max Cl/Cd: 102.87 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe269-il-500000-n5.txt Download as CSV file: xf-goe269-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 269 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3971 0.10907 0.10677 -0.0073 1.0000 0.0116
-9.250 -0.3943 0.10468 0.10238 -0.0093 1.0000 0.0123
-9.000 -0.3943 0.09961 0.09734 -0.0118 1.0000 0.0129
-8.750 -0.3855 0.09723 0.09497 -0.0130 1.0000 0.0131
-8.500 -0.3766 0.09489 0.09265 -0.0142 1.0000 0.0133
-8.250 -0.3689 0.09233 0.09010 -0.0155 1.0000 0.0136
-8.000 -0.3626 0.08965 0.08745 -0.0168 1.0000 0.0140
-7.750 -0.3566 0.08675 0.08457 -0.0186 1.0000 0.0147
-7.500 -0.3488 0.08152 0.07936 -0.0238 0.9964 0.0158
-7.250 -0.3270 0.07585 0.07367 -0.0321 0.9747 0.0166
-7.000 -0.3018 0.07322 0.07101 -0.0366 0.9555 0.0170
-6.750 -0.2777 0.07023 0.06796 -0.0412 0.9363 0.0176
-6.500 -0.2559 0.06682 0.06447 -0.0458 0.9192 0.0186
-6.250 -0.2265 0.05754 0.05502 -0.0588 0.9038 0.0207
-6.000 -0.2038 0.05545 0.05285 -0.0612 0.8902 0.0211
-5.750 -0.1811 0.05389 0.05122 -0.0628 0.8755 0.0216
-5.500 -0.1564 0.05176 0.04899 -0.0653 0.8592 0.0224
-5.250 -0.1278 0.04827 0.04535 -0.0696 0.8426 0.0232
-5.000 -0.0942 0.04332 0.04020 -0.0757 0.8259 0.0243
-4.750 -0.0528 0.03532 0.03180 -0.0842 0.8095 0.0261
-4.500 -0.0239 0.03272 0.02899 -0.0863 0.7886 0.0266
-4.000 0.0340 0.02855 0.02435 -0.0894 0.7469 0.0275
-3.750 0.0635 0.02666 0.02223 -0.0906 0.7300 0.0284
-3.250 0.1357 0.01316 0.00692 -0.0969 0.7091 0.0316
-3.000 0.1644 0.01248 0.00601 -0.0971 0.6981 0.0321
-2.750 0.1930 0.01182 0.00514 -0.0972 0.6880 0.0327
-2.500 0.2217 0.01121 0.00437 -0.0974 0.6782 0.0335
-2.250 0.2503 0.01091 0.00398 -0.0974 0.6694 0.0343
-2.000 0.2788 0.01068 0.00367 -0.0974 0.6606 0.0351
-1.750 0.3074 0.01047 0.00340 -0.0975 0.6522 0.0359
-1.500 0.3359 0.01029 0.00314 -0.0975 0.6437 0.0369
-1.250 0.3645 0.01010 0.00289 -0.0975 0.6359 0.0379
-1.000 0.3930 0.00995 0.00268 -0.0975 0.6275 0.0390
-0.750 0.4216 0.00982 0.00250 -0.0975 0.6189 0.0401
-0.500 0.4501 0.00970 0.00236 -0.0975 0.6106 0.0425
-0.250 0.4786 0.00967 0.00234 -0.0975 0.6018 0.0456
0.000 0.5070 0.00964 0.00227 -0.0975 0.5923 0.0488
0.250 0.5354 0.00963 0.00225 -0.0975 0.5815 0.0523
0.500 0.5638 0.00964 0.00226 -0.0975 0.5708 0.0561
0.750 0.5921 0.00967 0.00224 -0.0974 0.5587 0.0592
1.000 0.6203 0.00967 0.00223 -0.0974 0.5440 0.0624
1.250 0.6483 0.00972 0.00224 -0.0974 0.5257 0.0656
1.500 0.6760 0.00984 0.00226 -0.0973 0.5016 0.0689
1.750 0.7036 0.00995 0.00228 -0.0972 0.4751 0.0726
2.000 0.7311 0.01008 0.00233 -0.0972 0.4521 0.0760
2.250 0.7587 0.01021 0.00239 -0.0971 0.4335 0.0787
2.500 0.7863 0.01035 0.00247 -0.0970 0.4181 0.0810
2.750 0.8139 0.01049 0.00255 -0.0970 0.4023 0.0824
3.000 0.8414 0.01060 0.00262 -0.0969 0.3871 0.0854
3.250 0.8690 0.01072 0.00272 -0.0969 0.3745 0.0886
3.500 0.8966 0.01084 0.00283 -0.0968 0.3645 0.0926
3.750 0.9243 0.01094 0.00295 -0.0968 0.3555 0.0985
4.250 0.9799 0.01022 0.00345 -0.0975 0.3375 0.7270
4.500 1.0011 0.00985 0.00351 -0.0957 0.3292 1.0000
4.750 1.0283 0.01007 0.00369 -0.0956 0.3189 1.0000
5.000 1.0553 0.01029 0.00387 -0.0955 0.3060 1.0000
5.250 1.0822 0.01052 0.00406 -0.0953 0.2924 1.0000
5.500 1.1088 0.01079 0.00428 -0.0952 0.2771 1.0000
5.750 1.1348 0.01114 0.00454 -0.0949 0.2540 1.0000
6.000 1.1599 0.01163 0.00486 -0.0946 0.2208 1.0000
6.250 1.1839 0.01225 0.00527 -0.0942 0.1840 1.0000
6.500 1.2079 0.01286 0.00573 -0.0938 0.1560 1.0000
6.750 1.2326 0.01334 0.00613 -0.0934 0.1402 1.0000
7.000 1.2574 0.01379 0.00653 -0.0930 0.1286 1.0000
7.250 1.2822 0.01421 0.00694 -0.0927 0.1185 1.0000
7.500 1.3068 0.01462 0.00733 -0.0923 0.1088 1.0000
7.750 1.3310 0.01508 0.00776 -0.0918 0.0993 1.0000
8.000 1.3549 0.01554 0.00820 -0.0913 0.0891 1.0000
8.250 1.3783 0.01605 0.00866 -0.0908 0.0762 1.0000
8.500 1.4000 0.01676 0.00927 -0.0901 0.0580 1.0000
8.750 1.4192 0.01772 0.01009 -0.0890 0.0361 1.0000
9.000 1.4368 0.01883 0.01107 -0.0877 0.0189 1.0000
9.250 1.4571 0.01956 0.01183 -0.0867 0.0155 1.0000
9.500 1.4774 0.02025 0.01258 -0.0857 0.0139 1.0000
9.750 1.4961 0.02106 0.01346 -0.0845 0.0124 1.0000
10.000 1.5147 0.02183 0.01431 -0.0833 0.0115 1.0000
10.250 1.5331 0.02255 0.01512 -0.0821 0.0108 1.0000
10.500 1.5501 0.02336 0.01601 -0.0807 0.0101 1.0000
10.750 1.5654 0.02424 0.01697 -0.0791 0.0096 1.0000
11.000 1.5780 0.02526 0.01808 -0.0771 0.0091 1.0000
11.250 1.5855 0.02649 0.01941 -0.0745 0.0087 1.0000
11.500 1.5919 0.02761 0.02063 -0.0717 0.0084 1.0000
11.750 1.5993 0.02877 0.02189 -0.0693 0.0082 1.0000
12.000 1.6058 0.03009 0.02332 -0.0671 0.0079 1.0000
12.250 1.6116 0.03159 0.02493 -0.0652 0.0076 1.0000
12.500 1.6164 0.03328 0.02672 -0.0635 0.0073 1.0000
12.750 1.6203 0.03517 0.02872 -0.0621 0.0071 1.0000
13.000 1.6229 0.03731 0.03099 -0.0609 0.0069 1.0000
13.250 1.6239 0.03976 0.03355 -0.0600 0.0067 1.0000
13.500 1.6231 0.04257 0.03647 -0.0593 0.0066 1.0000
13.750 1.6198 0.04583 0.03985 -0.0590 0.0064 1.0000
14.000 1.6136 0.04961 0.04377 -0.0590 0.0063 1.0000
14.250 1.6041 0.05396 0.04825 -0.0593 0.0062 1.0000
14.500 1.5965 0.05819 0.05262 -0.0598 0.0061 1.0000
14.750 1.5892 0.06246 0.05702 -0.0604 0.0061 1.0000
15.000 1.5804 0.06706 0.06176 -0.0613 0.0060 1.0000
15.250 1.5705 0.07197 0.06681 -0.0624 0.0059 1.0000
15.500 1.5598 0.07719 0.07217 -0.0638 0.0059 1.0000
15.750 1.5482 0.08274 0.07786 -0.0655 0.0058 1.0000
16.000 1.5362 0.08851 0.08376 -0.0674 0.0058 1.0000
16.250 1.5238 0.09443 0.08982 -0.0694 0.0057 1.0000
16.500 1.5110 0.10051 0.09603 -0.0716 0.0057 1.0000
16.750 1.4984 0.10669 0.10233 -0.0740 0.0057 1.0000
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