GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 500,000 Max Cl/Cd: 101.1 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe479-il-500000.txt Download as CSV file: xf-goe479-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3608 0.09400 0.09164 -0.0389 1.0000 0.0386
-9.500 -0.3669 0.09128 0.08895 -0.0384 1.0000 0.0393
-9.250 -0.4957 0.05594 0.05359 -0.0694 0.9924 0.0362
-9.000 -0.4785 0.05175 0.04931 -0.0742 0.9876 0.0356
-8.750 -0.5091 0.03359 0.03015 -0.0859 0.9757 0.0344
-8.500 -0.4946 0.02712 0.02285 -0.0886 0.9715 0.0352
-8.250 -0.4725 0.02505 0.02029 -0.0889 0.9664 0.0360
-8.000 -0.4488 0.02229 0.01729 -0.0897 0.9622 0.0367
-7.750 -0.4158 0.02123 0.01617 -0.0913 0.9600 0.0375
-7.500 -0.3806 0.02022 0.01507 -0.0932 0.9584 0.0383
-7.250 -0.3450 0.01924 0.01395 -0.0951 0.9567 0.0393
-7.000 -0.3202 0.01829 0.01283 -0.0946 0.9502 0.0402
-6.750 -0.2896 0.01729 0.01164 -0.0953 0.9459 0.0409
-6.500 -0.2559 0.01654 0.01071 -0.0964 0.9426 0.0416
-6.250 -0.2308 0.01516 0.00922 -0.0960 0.9354 0.0425
-6.000 -0.2013 0.01444 0.00848 -0.0963 0.9283 0.0435
-5.750 -0.1734 0.01394 0.00794 -0.0962 0.9196 0.0446
-5.500 -0.1448 0.01339 0.00731 -0.0961 0.9104 0.0457
-5.250 -0.1194 0.01289 0.00675 -0.0953 0.8989 0.0466
-5.000 -0.0918 0.01247 0.00623 -0.0950 0.8887 0.0477
-4.750 -0.0654 0.01200 0.00567 -0.0945 0.8775 0.0487
-4.500 -0.0411 0.01138 0.00504 -0.0937 0.8647 0.0504
-4.250 -0.0151 0.01108 0.00470 -0.0931 0.8515 0.0521
-4.000 0.0110 0.01080 0.00435 -0.0925 0.8377 0.0538
-3.750 0.0370 0.01057 0.00404 -0.0919 0.8235 0.0555
-3.500 0.0617 0.01018 0.00358 -0.0911 0.8087 0.0579
-3.000 0.1128 0.00983 0.00311 -0.0897 0.7791 0.0643
-2.750 0.1377 0.00957 0.00282 -0.0890 0.7655 0.0692
-2.500 0.1636 0.00945 0.00264 -0.0884 0.7534 0.0747
-2.250 0.1891 0.00927 0.00245 -0.0877 0.7421 0.0844
-2.000 0.2144 0.00909 0.00231 -0.0871 0.7308 0.1042
-1.750 0.2396 0.00889 0.00223 -0.0865 0.7204 0.1462
-1.500 0.2651 0.00876 0.00217 -0.0859 0.7110 0.1842
-1.250 0.2908 0.00861 0.00214 -0.0854 0.7017 0.2242
-1.000 0.3163 0.00849 0.00211 -0.0848 0.6931 0.2718
-0.750 0.3412 0.00829 0.00209 -0.0842 0.6838 0.3343
-0.500 0.3639 0.00792 0.00209 -0.0832 0.6756 0.4628
-0.250 0.3836 0.00743 0.00215 -0.0815 0.6670 0.6359
0.000 0.4018 0.00702 0.00221 -0.0791 0.6593 0.7966
0.250 0.4760 0.00688 0.00236 -0.0885 0.6486 0.9619
0.500 0.5335 0.00702 0.00241 -0.0946 0.6364 0.9907
0.750 0.5832 0.00711 0.00239 -0.0992 0.6227 1.0000
1.000 0.6056 0.00719 0.00238 -0.0980 0.6116 1.0000
1.250 0.6287 0.00725 0.00240 -0.0969 0.6012 1.0000
1.500 0.6515 0.00735 0.00243 -0.0958 0.5912 1.0000
1.750 0.6745 0.00743 0.00246 -0.0947 0.5798 1.0000
2.000 0.6976 0.00752 0.00250 -0.0936 0.5682 1.0000
2.250 0.7204 0.00764 0.00255 -0.0925 0.5571 1.0000
2.500 0.7431 0.00776 0.00261 -0.0913 0.5445 1.0000
2.750 0.7660 0.00787 0.00268 -0.0902 0.5311 1.0000
3.000 0.7888 0.00800 0.00276 -0.0890 0.5177 1.0000
3.250 0.8110 0.00816 0.00285 -0.0878 0.5024 1.0000
3.500 0.8330 0.00833 0.00295 -0.0865 0.4863 1.0000
3.750 0.8550 0.00852 0.00306 -0.0852 0.4716 1.0000
4.000 0.8770 0.00872 0.00319 -0.0840 0.4579 1.0000
4.250 0.8989 0.00894 0.00334 -0.0827 0.4443 1.0000
4.500 0.9207 0.00915 0.00350 -0.0815 0.4311 1.0000
4.750 0.9433 0.00934 0.00365 -0.0804 0.4185 1.0000
5.000 0.9655 0.00955 0.00383 -0.0792 0.4062 1.0000
5.250 0.9874 0.00977 0.00400 -0.0780 0.3934 1.0000
5.500 1.0090 0.01000 0.00419 -0.0768 0.3797 1.0000
5.750 1.0304 0.01024 0.00439 -0.0755 0.3632 1.0000
6.000 1.0516 0.01049 0.00458 -0.0742 0.3448 1.0000
6.250 1.0720 0.01078 0.00481 -0.0728 0.3241 1.0000
6.500 1.0909 0.01116 0.00507 -0.0711 0.3001 1.0000
6.750 1.1086 0.01160 0.00538 -0.0693 0.2729 1.0000
7.000 1.1258 0.01208 0.00574 -0.0674 0.2473 1.0000
7.250 1.1421 0.01261 0.00613 -0.0654 0.2239 1.0000
7.500 1.1571 0.01320 0.00658 -0.0632 0.1965 1.0000
7.750 1.1677 0.01402 0.00714 -0.0603 0.1530 1.0000
8.000 1.1621 0.01551 0.00811 -0.0548 0.0772 1.0000
8.250 1.1675 0.01643 0.00889 -0.0511 0.0582 1.0000
8.500 1.1805 0.01701 0.00948 -0.0486 0.0542 1.0000
8.750 1.1920 0.01768 0.01017 -0.0460 0.0511 1.0000
9.000 1.2045 0.01832 0.01084 -0.0436 0.0492 1.0000
9.250 1.2181 0.01891 0.01149 -0.0415 0.0478 1.0000
9.500 1.2306 0.01957 0.01220 -0.0394 0.0464 1.0000
9.750 1.2413 0.02036 0.01303 -0.0371 0.0451 1.0000
10.000 1.2498 0.02129 0.01400 -0.0346 0.0440 1.0000
10.250 1.2547 0.02247 0.01523 -0.0318 0.0429 1.0000
10.500 1.2609 0.02363 0.01646 -0.0294 0.0422 1.0000
10.750 1.2716 0.02456 0.01746 -0.0277 0.0416 1.0000
11.000 1.2808 0.02562 0.01860 -0.0259 0.0410 1.0000
11.250 1.2891 0.02681 0.01985 -0.0241 0.0402 1.0000
11.500 1.2969 0.02808 0.02118 -0.0225 0.0394 1.0000
11.750 1.3031 0.02952 0.02269 -0.0210 0.0388 1.0000
12.000 1.3089 0.03108 0.02430 -0.0195 0.0382 1.0000
12.250 1.3134 0.03280 0.02608 -0.0182 0.0376 1.0000
12.500 1.3146 0.03489 0.02821 -0.0169 0.0369 1.0000
12.750 1.3133 0.03725 0.03063 -0.0154 0.0363 1.0000
13.000 1.3170 0.03924 0.03268 -0.0144 0.0358 1.0000
13.250 1.3242 0.04096 0.03449 -0.0137 0.0354 1.0000
13.500 1.3308 0.04277 0.03639 -0.0130 0.0349 1.0000
13.750 1.3366 0.04469 0.03838 -0.0124 0.0344 1.0000
14.000 1.3421 0.04667 0.04044 -0.0119 0.0338 1.0000
14.250 1.3472 0.04874 0.04258 -0.0115 0.0331 1.0000
14.500 1.3521 0.05086 0.04476 -0.0111 0.0326 1.0000
14.750 1.3562 0.05307 0.04702 -0.0108 0.0321 1.0000
15.000 1.3606 0.05527 0.04926 -0.0105 0.0316 1.0000
15.250 1.3651 0.05740 0.05141 -0.0099 0.0311 1.0000
15.500 1.3709 0.05929 0.05332 -0.0088 0.0303 1.0000
15.750 1.3737 0.06187 0.05603 -0.0090 0.0300 1.0000
16.000 1.3757 0.06461 0.05888 -0.0094 0.0295 1.0000
16.250 1.3788 0.06719 0.06157 -0.0095 0.0290 1.0000
16.500 1.3812 0.06989 0.06436 -0.0098 0.0286 1.0000
16.750 1.3835 0.07265 0.06721 -0.0102 0.0281 1.0000
17.000 1.3850 0.07557 0.07021 -0.0107 0.0277 1.0000
17.250 1.3860 0.07860 0.07332 -0.0113 0.0272 1.0000
17.500 1.3875 0.08160 0.07638 -0.0121 0.0268 1.0000
17.750 1.3904 0.08431 0.07912 -0.0126 0.0264 1.0000
18.000 1.3978 0.08602 0.08083 -0.0116 0.0256 1.0000
18.250 1.3934 0.09009 0.08506 -0.0131 0.0254 1.0000
18.500 1.3870 0.09463 0.08976 -0.0151 0.0251 1.0000
18.750 1.3823 0.09891 0.09418 -0.0168 0.0247 1.0000
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