GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 673 AIRFOIL (goe673-il) Reynolds number: 200,000 Max Cl/Cd: 74.99 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe673-il-200000.txt Download as CSV file: xf-goe673-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 673 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4284 0.09326 0.08982 -0.0403 1.0000 0.0470
-9.000 -0.4346 0.08873 0.08536 -0.0434 1.0000 0.0489
-8.750 -0.4495 0.08383 0.08058 -0.0476 1.0000 0.0500
-8.500 -0.3735 0.07353 0.07055 -0.0415 1.0000 0.0559
-8.250 -0.3880 0.07058 0.06766 -0.0402 1.0000 0.0568
-8.000 -0.4075 0.06765 0.06481 -0.0386 1.0000 0.0572
-7.750 -0.4330 0.06490 0.06214 -0.0367 1.0000 0.0568
-7.500 -0.5468 0.06688 0.06338 -0.0473 1.0000 0.0508
-7.250 -0.5561 0.06002 0.05656 -0.0468 1.0000 0.0520
-7.000 -0.5482 0.05801 0.05470 -0.0446 1.0000 0.0535
-6.750 -0.5437 0.05598 0.05267 -0.0431 1.0000 0.0556
-6.500 -0.5324 0.05003 0.04589 -0.0482 0.9969 0.0644
-6.250 -0.5051 0.04667 0.04277 -0.0500 0.9947 0.0679
-6.000 -0.4781 0.04246 0.03814 -0.0539 0.9901 0.0794
-5.750 -0.4481 0.03979 0.03533 -0.0567 0.9863 0.0933
-5.500 -0.4147 0.03779 0.03329 -0.0596 0.9835 0.1102
-5.250 -0.3693 0.02566 0.01893 -0.0588 0.9819 0.0366
-5.000 -0.3364 0.02294 0.01580 -0.0596 0.9781 0.0343
-4.750 -0.2999 0.02098 0.01354 -0.0611 0.9749 0.0337
-4.500 -0.2617 0.01954 0.01192 -0.0631 0.9722 0.0352
-4.250 -0.2211 0.01860 0.01085 -0.0656 0.9700 0.0383
-4.000 -0.1905 0.01726 0.00947 -0.0663 0.9645 0.0401
-3.750 -0.1533 0.01621 0.00837 -0.0686 0.9605 0.0454
-3.500 -0.1122 0.01542 0.00750 -0.0714 0.9575 0.0609
-3.250 -0.0723 0.01344 0.00690 -0.0752 0.9559 0.3530
-3.000 -0.0437 0.01295 0.00683 -0.0757 0.9484 0.4733
-2.750 -0.0058 0.01243 0.00670 -0.0778 0.9447 0.5810
-2.500 0.0338 0.01207 0.00663 -0.0799 0.9421 0.6803
-2.250 0.0612 0.01190 0.00653 -0.0795 0.9338 0.7279
-2.000 0.0970 0.01161 0.00630 -0.0807 0.9297 0.7730
-1.750 0.1241 0.01142 0.00616 -0.0800 0.9221 0.8140
-1.500 0.1537 0.01117 0.00597 -0.0796 0.9165 0.8573
-1.250 0.1810 0.01103 0.00586 -0.0786 0.9093 0.9033
-1.000 0.2186 0.01086 0.00564 -0.0800 0.9035 0.9485
-0.750 0.2711 0.01064 0.00534 -0.0848 0.9004 0.9829
-0.500 0.3150 0.01051 0.00514 -0.0884 0.8919 1.0000
-0.250 0.3410 0.01035 0.00489 -0.0881 0.8831 1.0000
0.000 0.3670 0.01022 0.00468 -0.0876 0.8736 1.0000
0.250 0.3917 0.01017 0.00455 -0.0870 0.8626 1.0000
0.500 0.4179 0.01010 0.00442 -0.0865 0.8522 1.0000
0.750 0.4452 0.01001 0.00428 -0.0862 0.8425 1.0000
1.000 0.4716 0.00997 0.00418 -0.0858 0.8313 1.0000
1.250 0.4976 0.00996 0.00413 -0.0853 0.8190 1.0000
1.500 0.5240 0.00996 0.00409 -0.0849 0.8066 1.0000
1.750 0.5507 0.00997 0.00408 -0.0845 0.7938 1.0000
2.000 0.5774 0.00999 0.00407 -0.0841 0.7805 1.0000
2.250 0.6041 0.01003 0.00407 -0.0838 0.7667 1.0000
2.500 0.6308 0.01009 0.00412 -0.0834 0.7522 1.0000
2.750 0.6574 0.01016 0.00417 -0.0831 0.7371 1.0000
3.000 0.6840 0.01025 0.00424 -0.0827 0.7218 1.0000
3.250 0.7107 0.01037 0.00434 -0.0824 0.7064 1.0000
3.500 0.7373 0.01052 0.00449 -0.0821 0.6910 1.0000
3.750 0.7636 0.01069 0.00466 -0.0817 0.6751 1.0000
4.000 0.7898 0.01088 0.00488 -0.0814 0.6588 1.0000
4.250 0.8154 0.01107 0.00508 -0.0809 0.6392 1.0000
4.500 0.8380 0.01124 0.00515 -0.0795 0.6040 1.0000
4.750 0.8601 0.01147 0.00529 -0.0782 0.5659 1.0000
5.000 0.8806 0.01179 0.00547 -0.0767 0.5159 1.0000
5.250 0.8984 0.01235 0.00576 -0.0747 0.4447 1.0000
5.500 0.8934 0.01492 0.00677 -0.0695 0.1843 1.0000
5.750 0.8969 0.01749 0.00847 -0.0659 0.0481 1.0000
6.000 0.9154 0.01847 0.00961 -0.0643 0.0406 1.0000
6.250 0.9312 0.01960 0.01084 -0.0623 0.0367 1.0000
6.500 0.9405 0.02129 0.01259 -0.0593 0.0341 1.0000
6.750 0.9587 0.02220 0.01359 -0.0578 0.0316 1.0000
7.000 0.9745 0.02349 0.01495 -0.0558 0.0299 1.0000
7.250 0.9923 0.02498 0.01647 -0.0541 0.0288 1.0000
7.500 1.0141 0.02669 0.01823 -0.0530 0.0281 1.0000
7.750 1.0414 0.02876 0.02043 -0.0527 0.0279 1.0000
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Polar data table (+)
Polar graphs
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