GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 415 AIRFOIL (goe415-il) Reynolds number: 100,000 Max Cl/Cd: 53.57 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe415-il-100000-n5.txt Download as CSV file: xf-goe415-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 415 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3896 0.10604 0.10144 -0.0104 1.0000 0.0329
-8.250 -0.3860 0.10305 0.09851 -0.0134 1.0000 0.0331
-8.000 -0.3823 0.09996 0.09549 -0.0163 1.0000 0.0333
-7.750 -0.3785 0.09677 0.09236 -0.0193 1.0000 0.0334
-7.500 -0.3709 0.09312 0.08876 -0.0234 1.0000 0.0335
-7.250 -0.3614 0.08918 0.08486 -0.0280 1.0000 0.0336
-7.000 -0.3505 0.08506 0.08074 -0.0325 1.0000 0.0337
-6.750 -0.3471 0.08030 0.07609 -0.0305 1.0000 0.0343
-6.500 -0.3407 0.07679 0.07259 -0.0294 1.0000 0.0350
-6.250 -0.3321 0.07337 0.06920 -0.0304 1.0000 0.0358
-6.000 -0.3229 0.06992 0.06577 -0.0321 1.0000 0.0365
-5.750 -0.3130 0.06641 0.06227 -0.0341 1.0000 0.0373
-5.500 -0.3020 0.06282 0.05868 -0.0361 1.0000 0.0381
-5.250 -0.2898 0.05919 0.05500 -0.0381 1.0000 0.0391
-5.000 -0.2755 0.05550 0.05122 -0.0401 1.0000 0.0408
-4.750 -0.2520 0.05094 0.04620 -0.0451 1.0000 0.0455
-4.500 -0.2300 0.04734 0.04277 -0.0467 0.9945 0.0497
-4.250 -0.1898 0.04277 0.03787 -0.0530 0.9859 0.0618
-4.000 -0.1430 0.03619 0.03069 -0.0569 0.9781 0.0283
-3.000 0.0166 0.02326 0.01543 -0.0664 0.9355 0.0246
-2.750 0.0527 0.02152 0.01342 -0.0678 0.9209 0.0274
-2.500 0.0880 0.01986 0.01140 -0.0684 0.9045 0.0284
-2.250 0.1213 0.01848 0.00976 -0.0686 0.8860 0.0301
-2.000 0.1510 0.01755 0.00862 -0.0682 0.8634 0.0343
-1.750 0.1781 0.01637 0.00743 -0.0676 0.8377 0.0377
-1.500 0.2052 0.01571 0.00657 -0.0668 0.8073 0.0438
-1.250 0.2325 0.01499 0.00563 -0.0661 0.7750 0.0524
-0.750 0.2849 0.01295 0.00459 -0.0648 0.7137 0.4481
-0.500 0.3200 0.01160 0.00422 -0.0650 0.6839 1.0000
-0.250 0.3466 0.01179 0.00401 -0.0644 0.6568 1.0000
0.250 0.3995 0.01220 0.00376 -0.0634 0.6097 1.0000
0.500 0.4259 0.01241 0.00370 -0.0629 0.5894 1.0000
0.750 0.4522 0.01264 0.00367 -0.0625 0.5714 1.0000
1.000 0.4786 0.01287 0.00367 -0.0621 0.5549 1.0000
1.250 0.5051 0.01311 0.00371 -0.0617 0.5392 1.0000
1.500 0.5315 0.01335 0.00379 -0.0614 0.5244 1.0000
1.750 0.5579 0.01360 0.00389 -0.0610 0.5103 1.0000
2.250 0.6107 0.01411 0.00418 -0.0604 0.4834 1.0000
2.500 0.6372 0.01436 0.00436 -0.0601 0.4706 1.0000
2.750 0.6636 0.01462 0.00455 -0.0599 0.4579 1.0000
3.000 0.6898 0.01488 0.00476 -0.0596 0.4454 1.0000
3.250 0.7160 0.01515 0.00500 -0.0593 0.4336 1.0000
3.500 0.7421 0.01544 0.00524 -0.0590 0.4226 1.0000
3.750 0.7683 0.01573 0.00552 -0.0587 0.4119 1.0000
4.000 0.7945 0.01604 0.00586 -0.0584 0.4013 1.0000
4.250 0.8204 0.01636 0.00618 -0.0581 0.3913 1.0000
4.500 0.8460 0.01669 0.00649 -0.0578 0.3811 1.0000
4.750 0.8717 0.01701 0.00689 -0.0574 0.3695 1.0000
5.000 0.8972 0.01735 0.00728 -0.0571 0.3586 1.0000
5.250 0.9224 0.01771 0.00766 -0.0567 0.3475 1.0000
5.500 0.9474 0.01808 0.00806 -0.0563 0.3369 1.0000
5.750 0.9726 0.01845 0.00858 -0.0560 0.3267 1.0000
6.000 0.9978 0.01886 0.00912 -0.0556 0.3183 1.0000
6.250 1.0227 0.01930 0.00964 -0.0552 0.3104 1.0000
6.500 1.0466 0.01966 0.01012 -0.0546 0.2960 1.0000
6.750 1.0692 0.01996 0.01054 -0.0540 0.2703 1.0000
7.000 1.0907 0.02039 0.01091 -0.0533 0.2342 1.0000
7.250 1.1120 0.02105 0.01148 -0.0526 0.1921 1.0000
7.750 1.1356 0.02532 0.01458 -0.0498 0.0280 1.0000
8.000 1.1515 0.02687 0.01627 -0.0484 0.0218 1.0000
8.250 1.1676 0.02829 0.01796 -0.0470 0.0196 1.0000
8.500 1.1802 0.03005 0.01999 -0.0454 0.0175 1.0000
8.750 1.1895 0.03202 0.02233 -0.0436 0.0160 1.0000
9.000 1.1993 0.03373 0.02433 -0.0419 0.0153 1.0000
9.250 1.2051 0.03566 0.02653 -0.0399 0.0149 1.0000
9.500 1.2061 0.03771 0.02881 -0.0377 0.0146 1.0000
9.750 1.2035 0.04000 0.03130 -0.0355 0.0144 1.0000
10.000 1.1992 0.04265 0.03415 -0.0340 0.0142 1.0000
10.250 1.1942 0.04567 0.03736 -0.0333 0.0140 1.0000
10.500 1.1896 0.04900 0.04085 -0.0332 0.0137 1.0000
10.750 1.1855 0.05255 0.04455 -0.0336 0.0134 1.0000
11.000 1.1825 0.05612 0.04826 -0.0341 0.0130 1.0000
11.250 1.1803 0.05964 0.05190 -0.0344 0.0125 1.0000
11.500 1.1791 0.06303 0.05539 -0.0346 0.0121 1.0000
11.750 1.1791 0.06627 0.05874 -0.0346 0.0116 1.0000
12.000 1.1808 0.06926 0.06183 -0.0341 0.0114 1.0000
12.250 1.1839 0.07215 0.06484 -0.0335 0.0112 1.0000
12.500 1.1862 0.07528 0.06810 -0.0330 0.0111 1.0000
12.750 1.1869 0.07876 0.07174 -0.0330 0.0110 1.0000
13.000 1.1855 0.08266 0.07582 -0.0334 0.0110 1.0000
13.250 1.1820 0.08697 0.08032 -0.0344 0.0110 1.0000
13.500 1.1762 0.09170 0.08524 -0.0359 0.0110 1.0000
13.750 1.1689 0.09677 0.09052 -0.0378 0.0110 1.0000
14.000 1.1603 0.10221 0.09615 -0.0401 0.0110 1.0000
14.250 1.1503 0.10809 0.10222 -0.0430 0.0111 1.0000
14.500 1.1393 0.11443 0.10876 -0.0464 0.0112 1.0000
14.750 1.1278 0.12118 0.11570 -0.0502 0.0112 1.0000
15.000 1.1158 0.12836 0.12307 -0.0545 0.0113 1.0000
15.250 1.1037 0.13595 0.13083 -0.0592 0.0114 1.0000
15.500 1.0914 0.14401 0.13905 -0.0642 0.0116 1.0000
15.750 1.0790 0.15260 0.14778 -0.0697 0.0117 1.0000
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