GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 415 AIRFOIL (goe415-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.85 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe415-il-1000000-n5.txt Download as CSV file: xf-goe415-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3915 0.09544 0.09396 -0.0063 1.0000 0.0046
-8.000 -0.3861 0.09188 0.09042 -0.0083 1.0000 0.0046
-7.750 -0.3810 0.08830 0.08687 -0.0103 1.0000 0.0046
-7.500 -0.3731 0.08449 0.08307 -0.0134 0.9816 0.0046
-7.250 -0.3594 0.08004 0.07856 -0.0187 0.9379 0.0046
-6.250 -0.2998 0.05754 0.05574 -0.0440 0.8710 0.0030
-6.000 -0.2760 0.05169 0.04978 -0.0505 0.8557 0.0030
-5.750 -0.2512 0.04645 0.04437 -0.0557 0.8357 0.0031
-5.500 -0.2265 0.04183 0.03950 -0.0594 0.8025 0.0032
-5.250 -0.2018 0.03729 0.03460 -0.0621 0.7540 0.0033
-5.000 -0.1765 0.03290 0.02983 -0.0640 0.7156 0.0034
-4.750 -0.1505 0.02847 0.02500 -0.0652 0.6876 0.0035
-4.500 -0.1247 0.02520 0.02136 -0.0655 0.6584 0.0038
-4.250 -0.0984 0.02161 0.01731 -0.0655 0.6295 0.0040
-4.000 -0.0719 0.01718 0.01224 -0.0648 0.6018 0.0038
-3.750 -0.0464 0.01172 0.00590 -0.0635 0.5790 0.0041
-3.500 -0.0198 0.01086 0.00475 -0.0631 0.5537 0.0044
-3.250 0.0073 0.01035 0.00403 -0.0629 0.5335 0.0047
-3.000 0.0343 0.00975 0.00325 -0.0626 0.5181 0.0051
-2.750 0.0619 0.00951 0.00293 -0.0625 0.5059 0.0055
-2.500 0.0897 0.00936 0.00271 -0.0624 0.4949 0.0062
-2.250 0.1175 0.00919 0.00246 -0.0623 0.4844 0.0071
-2.000 0.1454 0.00892 0.00209 -0.0622 0.4758 0.0078
-1.750 0.1733 0.00872 0.00182 -0.0621 0.4669 0.0094
-1.500 0.2014 0.00863 0.00170 -0.0621 0.4578 0.0111
-1.250 0.2294 0.00851 0.00150 -0.0620 0.4481 0.0138
-1.000 0.2573 0.00845 0.00139 -0.0619 0.4371 0.0188
-0.750 0.2853 0.00845 0.00134 -0.0619 0.4254 0.0221
-0.500 0.3133 0.00842 0.00124 -0.0619 0.4146 0.0243
-0.250 0.3412 0.00838 0.00115 -0.0618 0.4038 0.0296
0.000 0.3691 0.00839 0.00109 -0.0618 0.3925 0.0345
0.250 0.3964 0.00812 0.00104 -0.0618 0.3792 0.1503
0.500 0.4233 0.00785 0.00107 -0.0618 0.3635 0.2929
0.750 0.4507 0.00778 0.00109 -0.0618 0.3495 0.3552
1.000 0.4780 0.00770 0.00115 -0.0618 0.3382 0.4319
1.250 0.5054 0.00763 0.00119 -0.0617 0.3276 0.4989
1.500 0.5282 0.00692 0.00130 -0.0609 0.3184 0.8032
2.000 0.5912 0.00676 0.00140 -0.0624 0.2997 1.0000
2.250 0.6186 0.00690 0.00147 -0.0623 0.2895 1.0000
2.500 0.6459 0.00705 0.00155 -0.0622 0.2790 1.0000
2.750 0.6734 0.00717 0.00162 -0.0621 0.2718 1.0000
3.000 0.7008 0.00730 0.00172 -0.0620 0.2653 1.0000
3.250 0.7283 0.00741 0.00181 -0.0620 0.2597 1.0000
3.500 0.7556 0.00755 0.00191 -0.0619 0.2535 1.0000
3.750 0.7830 0.00768 0.00203 -0.0618 0.2482 1.0000
4.000 0.8102 0.00783 0.00214 -0.0617 0.2404 1.0000
4.250 0.8375 0.00798 0.00227 -0.0617 0.2344 1.0000
4.500 0.8647 0.00812 0.00241 -0.0616 0.2286 1.0000
4.750 0.8913 0.00835 0.00258 -0.0615 0.2143 1.0000
5.000 0.9178 0.00859 0.00276 -0.0614 0.1994 1.0000
5.250 0.9437 0.00894 0.00299 -0.0612 0.1750 1.0000
5.500 0.9668 0.00972 0.00346 -0.0607 0.1202 1.0000
5.750 0.9915 0.01023 0.00386 -0.0604 0.0968 1.0000
6.000 1.0112 0.01159 0.00480 -0.0594 0.0138 1.0000
6.250 1.0370 0.01192 0.00516 -0.0592 0.0087 1.0000
6.500 1.0627 0.01226 0.00554 -0.0589 0.0070 1.0000
6.750 1.0880 0.01265 0.00597 -0.0586 0.0056 1.0000
7.000 1.1132 0.01300 0.00636 -0.0584 0.0047 1.0000
7.250 1.1377 0.01349 0.00689 -0.0579 0.0039 1.0000
7.500 1.1623 0.01393 0.00738 -0.0576 0.0035 1.0000
7.750 1.1866 0.01440 0.00791 -0.0571 0.0032 1.0000
8.000 1.2105 0.01491 0.00850 -0.0567 0.0028 1.0000
8.250 1.2337 0.01548 0.00913 -0.0562 0.0026 1.0000
8.500 1.2551 0.01630 0.01004 -0.0554 0.0023 1.0000
8.750 1.2780 0.01685 0.01066 -0.0549 0.0021 1.0000
9.000 1.2998 0.01753 0.01142 -0.0542 0.0019 1.0000
9.250 1.3204 0.01831 0.01229 -0.0534 0.0018 1.0000
9.500 1.3403 0.01911 0.01318 -0.0525 0.0017 1.0000
9.750 1.3595 0.01994 0.01409 -0.0515 0.0016 1.0000
10.000 1.3780 0.02079 0.01502 -0.0506 0.0015 1.0000
10.250 1.3947 0.02176 0.01608 -0.0494 0.0014 1.0000
10.500 1.4058 0.02319 0.01764 -0.0475 0.0013 1.0000
10.750 1.4134 0.02478 0.01937 -0.0453 0.0013 1.0000
11.000 1.4212 0.02611 0.02086 -0.0431 0.0012 1.0000
11.250 1.4235 0.02759 0.02247 -0.0403 0.0012 1.0000
11.500 1.4226 0.02945 0.02446 -0.0378 0.0011 1.0000
11.750 1.4200 0.03170 0.02686 -0.0359 0.0011 1.0000
12.000 1.4156 0.03446 0.02977 -0.0347 0.0011 1.0000
12.250 1.4099 0.03775 0.03321 -0.0342 0.0011 1.0000
12.500 1.4031 0.04162 0.03723 -0.0347 0.0010 1.0000
12.750 1.3956 0.04592 0.04168 -0.0356 0.0010 1.0000
13.000 1.3867 0.05056 0.04648 -0.0368 0.0010 1.0000
13.250 1.3766 0.05547 0.05153 -0.0381 0.0010 1.0000
13.500 1.3654 0.06052 0.05674 -0.0394 0.0010 1.0000
13.750 1.3530 0.06573 0.06209 -0.0407 0.0009 1.0000
14.000 1.3389 0.07118 0.06769 -0.0419 0.0009 1.0000
14.250 1.3243 0.07678 0.07344 -0.0433 0.0009 1.0000
14.500 1.3086 0.08273 0.07954 -0.0448 0.0009 1.0000
14.750 1.2934 0.08888 0.08584 -0.0466 0.0009 1.0000
15.000 1.2789 0.09516 0.09227 -0.0488 0.0009 1.0000
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Polar data table (+)
Polar graphs
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