GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 415 AIRFOIL (goe415-il) Reynolds number: 500,000 Max Cl/Cd: 90.88 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe415-il-500000-n5.txt Download as CSV file: xf-goe415-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3807 0.09322 0.09117 -0.0105 1.0000 0.0073
-7.750 -0.3751 0.08970 0.08768 -0.0125 1.0000 0.0074
-7.500 -0.3701 0.08622 0.08423 -0.0145 1.0000 0.0074
-7.250 -0.3640 0.08260 0.08063 -0.0173 1.0000 0.0074
-5.750 -0.2407 0.05153 0.04930 -0.0548 0.9284 0.0071
-5.250 -0.1933 0.04156 0.03896 -0.0627 0.8975 0.0065
-4.750 -0.1398 0.03199 0.02877 -0.0667 0.8676 0.0070
-4.500 -0.1154 0.02817 0.02461 -0.0676 0.8495 0.0066
-4.250 -0.0901 0.02471 0.02075 -0.0677 0.8263 0.0063
-4.000 -0.0648 0.02154 0.01707 -0.0672 0.7892 0.0061
-3.750 -0.0396 0.01872 0.01365 -0.0662 0.7454 0.0060
-3.500 -0.0135 0.01622 0.01056 -0.0653 0.7087 0.0061
-3.250 0.0130 0.01416 0.00799 -0.0645 0.6771 0.0066
-3.000 0.0395 0.01290 0.00633 -0.0638 0.6447 0.0071
-2.750 0.0657 0.01220 0.00535 -0.0634 0.6118 0.0081
-2.500 0.0924 0.01188 0.00485 -0.0631 0.5814 0.0089
-2.250 0.1192 0.01137 0.00414 -0.0627 0.5584 0.0097
-2.000 0.1463 0.01092 0.00353 -0.0624 0.5410 0.0108
-1.500 0.2009 0.01018 0.00253 -0.0620 0.5136 0.0155
-1.250 0.2286 0.01000 0.00225 -0.0618 0.5019 0.0189
-1.000 0.2564 0.00997 0.00214 -0.0617 0.4915 0.0225
-0.750 0.2840 0.00977 0.00185 -0.0616 0.4816 0.0278
-0.500 0.3118 0.00972 0.00171 -0.0615 0.4714 0.0329
-0.250 0.3396 0.00964 0.00156 -0.0614 0.4611 0.0409
0.000 0.3661 0.00902 0.00149 -0.0615 0.4503 0.2555
0.250 0.3929 0.00874 0.00149 -0.0615 0.4386 0.3817
0.500 0.4198 0.00854 0.00151 -0.0614 0.4270 0.4847
0.750 0.4423 0.00782 0.00157 -0.0604 0.4166 0.7573
1.250 0.5072 0.00756 0.00157 -0.0621 0.3904 1.0000
1.500 0.5344 0.00771 0.00161 -0.0619 0.3756 1.0000
1.750 0.5616 0.00786 0.00165 -0.0618 0.3620 1.0000
2.000 0.5888 0.00801 0.00171 -0.0617 0.3503 1.0000
2.250 0.6159 0.00817 0.00179 -0.0615 0.3391 1.0000
2.500 0.6431 0.00831 0.00188 -0.0614 0.3289 1.0000
2.750 0.6702 0.00848 0.00197 -0.0613 0.3191 1.0000
3.000 0.6972 0.00866 0.00209 -0.0612 0.3088 1.0000
3.250 0.7243 0.00881 0.00221 -0.0611 0.2996 1.0000
3.500 0.7514 0.00898 0.00234 -0.0609 0.2913 1.0000
3.750 0.7783 0.00915 0.00249 -0.0608 0.2834 1.0000
4.000 0.8054 0.00932 0.00264 -0.0607 0.2773 1.0000
4.250 0.8323 0.00950 0.00280 -0.0606 0.2696 1.0000
4.500 0.8591 0.00968 0.00298 -0.0605 0.2620 1.0000
4.750 0.8859 0.00987 0.00318 -0.0603 0.2554 1.0000
5.000 0.9126 0.01007 0.00338 -0.0602 0.2477 1.0000
5.250 0.9388 0.01033 0.00359 -0.0600 0.2319 1.0000
5.500 0.9647 0.01063 0.00384 -0.0598 0.2146 1.0000
5.750 0.9900 0.01102 0.00413 -0.0596 0.1898 1.0000
6.000 1.0116 0.01198 0.00469 -0.0590 0.1229 1.0000
6.250 1.0286 0.01371 0.00586 -0.0579 0.0255 1.0000
6.500 1.0525 0.01432 0.00648 -0.0574 0.0123 1.0000
6.750 1.0770 0.01482 0.00711 -0.0569 0.0087 1.0000
7.000 1.1015 0.01530 0.00769 -0.0565 0.0075 1.0000
7.250 1.1251 0.01589 0.00838 -0.0560 0.0065 1.0000
7.500 1.1477 0.01661 0.00922 -0.0553 0.0056 1.0000
7.750 1.1706 0.01725 0.00995 -0.0547 0.0049 1.0000
8.000 1.1923 0.01802 0.01082 -0.0540 0.0044 1.0000
8.250 1.2128 0.01891 0.01183 -0.0531 0.0041 1.0000
8.500 1.2290 0.02028 0.01334 -0.0518 0.0038 1.0000
8.750 1.2467 0.02138 0.01457 -0.0506 0.0036 1.0000
9.000 1.2622 0.02263 0.01596 -0.0491 0.0035 1.0000
9.250 1.2772 0.02382 0.01727 -0.0477 0.0032 1.0000
9.500 1.2924 0.02490 0.01845 -0.0463 0.0029 1.0000
9.750 1.3063 0.02600 0.01965 -0.0449 0.0027 1.0000
10.000 1.3165 0.02734 0.02108 -0.0432 0.0025 1.0000
10.250 1.3201 0.02890 0.02274 -0.0406 0.0024 1.0000
10.500 1.3178 0.03093 0.02488 -0.0378 0.0024 1.0000
10.750 1.3143 0.03332 0.02740 -0.0356 0.0023 1.0000
11.000 1.3143 0.03566 0.02988 -0.0341 0.0023 1.0000
11.250 1.3131 0.03834 0.03271 -0.0330 0.0022 1.0000
11.500 1.3111 0.04135 0.03588 -0.0323 0.0021 1.0000
11.750 1.3089 0.04461 0.03930 -0.0319 0.0021 1.0000
12.000 1.3060 0.04808 0.04292 -0.0316 0.0020 1.0000
12.250 1.3029 0.05170 0.04670 -0.0316 0.0020 1.0000
12.500 1.2988 0.05554 0.05075 -0.0316 0.0019 1.0000
12.750 1.2938 0.05962 0.05500 -0.0320 0.0019 1.0000
13.000 1.2873 0.06399 0.05954 -0.0327 0.0019 1.0000
13.250 1.2795 0.06869 0.06441 -0.0339 0.0019 1.0000
13.500 1.2702 0.07370 0.06959 -0.0354 0.0019 1.0000
13.750 1.2595 0.07901 0.07506 -0.0372 0.0019 1.0000
14.000 1.2477 0.08466 0.08088 -0.0394 0.0019 1.0000
14.250 1.2355 0.09054 0.08692 -0.0420 0.0019 1.0000
14.500 1.2227 0.09677 0.09330 -0.0448 0.0019 1.0000
14.750 1.2100 0.10325 0.09992 -0.0480 0.0019 1.0000
15.000 1.1967 0.11003 0.10685 -0.0514 0.0019 1.0000
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Polar data table (+)
Polar graphs
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