GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 500,000 Max Cl/Cd: 104.56 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe399-il-500000.txt Download as CSV file: xf-goe399-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3568 0.08713 0.08498 -0.0277 1.0000 0.0196
-7.500 -0.3641 0.08493 0.08284 -0.0279 1.0000 0.0197
-7.250 -0.3654 0.08228 0.08023 -0.0283 1.0000 0.0197
-7.000 -0.3673 0.07966 0.07764 -0.0286 1.0000 0.0198
-6.750 -0.3595 0.07611 0.07409 -0.0313 0.9991 0.0198
-6.500 -0.3351 0.06796 0.06591 -0.0410 0.9950 0.0203
-6.250 -0.3122 0.06525 0.06318 -0.0431 0.9916 0.0211
-6.000 -0.2807 0.06095 0.05884 -0.0497 0.9871 0.0219
-5.750 -0.2441 0.05613 0.05395 -0.0578 0.9836 0.0231
-5.500 -0.1944 0.05031 0.04793 -0.0686 0.9771 0.0266
-4.750 -0.0972 0.03399 0.03106 -0.0842 0.9597 0.0291
-4.500 -0.0661 0.03173 0.02868 -0.0863 0.9520 0.0316
-4.250 -0.0393 0.01920 0.01487 -0.0871 0.9398 0.0272
-4.000 -0.0138 0.01827 0.01387 -0.0874 0.9274 0.0296
-3.750 0.0123 0.01772 0.01321 -0.0870 0.9135 0.0321
-3.500 0.0368 0.01520 0.01021 -0.0861 0.8992 0.0335
-3.250 0.0630 0.01426 0.00897 -0.0854 0.8848 0.0354
-3.000 0.0877 0.01256 0.00689 -0.0846 0.8701 0.0375
-2.750 0.1132 0.01163 0.00580 -0.0840 0.8551 0.0392
-2.500 0.1393 0.01125 0.00530 -0.0835 0.8403 0.0412
-2.250 0.1655 0.01088 0.00479 -0.0829 0.8265 0.0433
-2.000 0.1916 0.01035 0.00413 -0.0824 0.8138 0.0444
-1.750 0.2177 0.00993 0.00360 -0.0818 0.8015 0.0456
-1.500 0.2440 0.00965 0.00322 -0.0813 0.7898 0.0469
-1.250 0.2696 0.00920 0.00269 -0.0807 0.7787 0.0490
-1.000 0.2952 0.00886 0.00229 -0.0801 0.7685 0.0518
-0.750 0.3215 0.00871 0.00210 -0.0797 0.7582 0.0549
-0.500 0.3480 0.00859 0.00194 -0.0792 0.7480 0.0587
-0.250 0.3741 0.00840 0.00172 -0.0787 0.7382 0.0660
0.000 0.4002 0.00828 0.00160 -0.0782 0.7277 0.0829
0.250 0.4263 0.00815 0.00150 -0.0778 0.7160 0.1071
0.500 0.4517 0.00793 0.00148 -0.0773 0.7035 0.1847
0.750 0.5133 0.00601 0.00154 -0.0854 0.6887 1.0000
1.000 0.5388 0.00610 0.00153 -0.0848 0.6755 1.0000
1.250 0.5644 0.00618 0.00153 -0.0842 0.6631 1.0000
1.500 0.5899 0.00627 0.00155 -0.0836 0.6499 1.0000
1.750 0.6153 0.00637 0.00157 -0.0830 0.6359 1.0000
2.000 0.6404 0.00648 0.00160 -0.0823 0.6180 1.0000
2.250 0.6650 0.00662 0.00165 -0.0815 0.5959 1.0000
2.500 0.6898 0.00676 0.00170 -0.0808 0.5740 1.0000
2.750 0.7145 0.00693 0.00178 -0.0801 0.5528 1.0000
3.000 0.7389 0.00712 0.00187 -0.0794 0.5292 1.0000
3.250 0.7629 0.00735 0.00198 -0.0786 0.5027 1.0000
3.500 0.7868 0.00760 0.00213 -0.0778 0.4791 1.0000
3.750 0.8114 0.00782 0.00228 -0.0771 0.4622 1.0000
4.000 0.8360 0.00804 0.00245 -0.0765 0.4466 1.0000
4.250 0.8605 0.00826 0.00263 -0.0758 0.4315 1.0000
4.500 0.8851 0.00848 0.00283 -0.0752 0.4165 1.0000
4.750 0.9097 0.00870 0.00302 -0.0746 0.4014 1.0000
5.000 0.9338 0.00895 0.00323 -0.0739 0.3827 1.0000
5.250 0.9574 0.00924 0.00343 -0.0731 0.3509 1.0000
5.500 0.9797 0.00966 0.00369 -0.0722 0.3062 1.0000
5.750 0.9990 0.01038 0.00408 -0.0709 0.2433 1.0000
6.000 1.0111 0.01188 0.00488 -0.0686 0.1148 1.0000
6.250 1.0293 0.01280 0.00555 -0.0671 0.0716 1.0000
6.500 1.0509 0.01332 0.00605 -0.0661 0.0609 1.0000
6.750 1.0731 0.01377 0.00655 -0.0652 0.0527 1.0000
7.000 1.0945 0.01430 0.00708 -0.0642 0.0419 1.0000
7.250 1.1150 0.01492 0.00765 -0.0630 0.0287 1.0000
7.500 1.1339 0.01568 0.00841 -0.0615 0.0231 1.0000
7.750 1.1540 0.01628 0.00906 -0.0602 0.0203 1.0000
8.000 1.1679 0.01744 0.01030 -0.0580 0.0176 1.0000
8.250 1.1862 0.01813 0.01109 -0.0564 0.0167 1.0000
8.500 1.2024 0.01898 0.01203 -0.0546 0.0158 1.0000
8.750 1.2171 0.01991 0.01304 -0.0526 0.0149 1.0000
9.000 1.2307 0.02089 0.01410 -0.0504 0.0142 1.0000
9.250 1.2421 0.02202 0.01531 -0.0480 0.0137 1.0000
9.500 1.2461 0.02378 0.01718 -0.0446 0.0128 1.0000
9.750 1.2507 0.02579 0.01934 -0.0412 0.0123 1.0000
10.000 1.2634 0.02657 0.02022 -0.0391 0.0119 1.0000
10.250 1.2739 0.02784 0.02163 -0.0368 0.0115 1.0000
10.500 1.2837 0.02948 0.02341 -0.0346 0.0112 1.0000
10.750 1.2933 0.03108 0.02517 -0.0324 0.0109 1.0000
11.000 1.3018 0.03303 0.02729 -0.0303 0.0107 1.0000
11.250 1.3084 0.03498 0.02941 -0.0281 0.0104 1.0000
11.500 1.3128 0.03706 0.03169 -0.0260 0.0101 1.0000
11.750 1.3148 0.03955 0.03439 -0.0238 0.0100 1.0000
12.000 1.3152 0.04175 0.03674 -0.0219 0.0097 1.0000
12.250 1.3085 0.04536 0.04065 -0.0197 0.0098 1.0000
12.500 1.2986 0.04912 0.04469 -0.0180 0.0099 1.0000
12.750 1.2827 0.05371 0.04957 -0.0168 0.0099 1.0000
13.000 1.2545 0.06046 0.05670 -0.0164 0.0103 1.0000
13.250 1.2318 0.06645 0.06295 -0.0171 0.0105 1.0000
13.500 1.2066 0.07325 0.06998 -0.0190 0.0108 1.0000
13.750 1.1845 0.07992 0.07685 -0.0217 0.0109 1.0000
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Polar data table (+)
Polar graphs
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