GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 595 AIRFOIL (goe595-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.06 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe595-il-1000000-n5.txt Download as CSV file: xf-goe595-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 595 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4248 0.10775 0.10608 -0.0318 1.0000 0.0035
-10.750 -0.4282 0.10323 0.10157 -0.0328 1.0000 0.0035
-10.250 -0.6828 0.02607 0.02330 -0.0838 0.9781 0.0035
-10.000 -0.6690 0.02271 0.01954 -0.0840 0.9724 0.0036
-9.750 -0.6458 0.02084 0.01744 -0.0847 0.9690 0.0037
-9.500 -0.6180 0.01950 0.01592 -0.0859 0.9669 0.0038
-9.250 -0.5939 0.01822 0.01444 -0.0861 0.9627 0.0039
-9.000 -0.5677 0.01723 0.01328 -0.0865 0.9586 0.0041
-8.750 -0.5395 0.01624 0.01213 -0.0873 0.9554 0.0043
-8.500 -0.5122 0.01528 0.01101 -0.0878 0.9516 0.0044
-8.250 -0.4868 0.01446 0.01003 -0.0877 0.9463 0.0046
-8.000 -0.4589 0.01378 0.00923 -0.0881 0.9420 0.0048
-7.750 -0.4318 0.01309 0.00840 -0.0883 0.9377 0.0050
-7.500 -0.4059 0.01259 0.00779 -0.0881 0.9318 0.0052
-7.250 -0.3801 0.01180 0.00685 -0.0880 0.9260 0.0056
-7.000 -0.3550 0.01129 0.00624 -0.0876 0.9193 0.0059
-6.750 -0.3288 0.01090 0.00575 -0.0874 0.9129 0.0062
-6.500 -0.3029 0.01055 0.00534 -0.0871 0.9073 0.0066
-6.250 -0.2775 0.01019 0.00490 -0.0866 0.9011 0.0069
-6.000 -0.2514 0.00986 0.00447 -0.0863 0.8957 0.0073
-5.750 -0.2259 0.00960 0.00415 -0.0859 0.8895 0.0077
-5.500 -0.2006 0.00922 0.00369 -0.0854 0.8834 0.0086
-5.250 -0.1746 0.00901 0.00347 -0.0850 0.8776 0.0097
-5.000 -0.1486 0.00881 0.00322 -0.0847 0.8711 0.0107
-4.750 -0.1224 0.00861 0.00296 -0.0843 0.8646 0.0113
-4.500 -0.0969 0.00836 0.00267 -0.0838 0.8563 0.0133
-4.250 -0.0708 0.00822 0.00253 -0.0834 0.8475 0.0152
-4.000 -0.0445 0.00814 0.00239 -0.0831 0.8382 0.0168
-3.750 -0.0187 0.00794 0.00217 -0.0826 0.8288 0.0193
-3.500 0.0076 0.00782 0.00201 -0.0823 0.8206 0.0216
-3.250 0.0338 0.00774 0.00187 -0.0819 0.8108 0.0239
-3.000 0.0601 0.00767 0.00176 -0.0815 0.7995 0.0250
-2.750 0.0857 0.00760 0.00162 -0.0810 0.7850 0.0260
-2.500 0.1107 0.00751 0.00143 -0.0804 0.7685 0.0284
-2.250 0.1359 0.00746 0.00130 -0.0798 0.7519 0.0302
-2.000 0.1614 0.00742 0.00119 -0.0792 0.7364 0.0317
-1.750 0.1869 0.00740 0.00110 -0.0787 0.7215 0.0328
-1.500 0.2123 0.00740 0.00103 -0.0781 0.7044 0.0342
-1.250 0.2377 0.00739 0.00097 -0.0776 0.6878 0.0419
-1.000 0.2622 0.00732 0.00093 -0.0769 0.6687 0.0739
-0.750 0.2868 0.00735 0.00090 -0.0763 0.6454 0.0865
-0.500 0.3103 0.00732 0.00088 -0.0754 0.6172 0.1257
-0.250 0.3341 0.00731 0.00088 -0.0746 0.5903 0.1632
0.000 0.3574 0.00731 0.00090 -0.0738 0.5607 0.2121
0.250 0.3800 0.00735 0.00095 -0.0728 0.5257 0.2672
0.500 0.4035 0.00737 0.00099 -0.0720 0.4980 0.3149
0.750 0.4251 0.00714 0.00104 -0.0710 0.4770 0.4503
1.000 0.4484 0.00708 0.00111 -0.0702 0.4581 0.5229
1.250 0.4711 0.00697 0.00117 -0.0693 0.4424 0.6061
1.500 0.4897 0.00663 0.00126 -0.0673 0.4313 0.7582
1.750 0.5299 0.00633 0.00147 -0.0699 0.4201 0.9556
2.000 0.5773 0.00653 0.00159 -0.0745 0.4019 0.9766
2.250 0.6111 0.00669 0.00167 -0.0760 0.3865 0.9832
2.500 0.6448 0.00684 0.00177 -0.0774 0.3732 0.9897
2.750 0.6816 0.00700 0.00187 -0.0796 0.3585 0.9962
3.000 0.7194 0.00719 0.00197 -0.0820 0.3363 0.9998
3.250 0.7404 0.00749 0.00211 -0.0807 0.3000 1.0000
3.500 0.7594 0.00783 0.00228 -0.0791 0.2633 1.0000
3.750 0.7801 0.00809 0.00245 -0.0777 0.2431 1.0000
4.000 0.8014 0.00832 0.00262 -0.0764 0.2273 1.0000
4.500 0.8445 0.00879 0.00296 -0.0740 0.1993 1.0000
4.750 0.8666 0.00900 0.00313 -0.0729 0.1864 1.0000
5.000 0.8884 0.00924 0.00332 -0.0718 0.1716 1.0000
5.250 0.9075 0.00966 0.00357 -0.0702 0.1360 1.0000
5.500 0.9175 0.01074 0.00422 -0.0671 0.0511 1.0000
5.750 0.9384 0.01106 0.00451 -0.0658 0.0411 1.0000
6.000 0.9604 0.01131 0.00476 -0.0647 0.0375 1.0000
6.250 0.9820 0.01159 0.00504 -0.0636 0.0340 1.0000
6.500 1.0036 0.01187 0.00532 -0.0625 0.0304 1.0000
6.750 1.0260 0.01209 0.00557 -0.0616 0.0289 1.0000
7.000 1.0475 0.01238 0.00586 -0.0605 0.0247 1.0000
7.250 1.0681 0.01273 0.00619 -0.0593 0.0186 1.0000
7.500 1.0882 0.01311 0.00654 -0.0580 0.0131 1.0000
7.750 1.1081 0.01350 0.00692 -0.0566 0.0106 1.0000
8.000 1.1280 0.01389 0.00733 -0.0553 0.0089 1.0000
8.250 1.1478 0.01426 0.00774 -0.0540 0.0079 1.0000
8.500 1.1666 0.01469 0.00818 -0.0525 0.0069 1.0000
8.750 1.1846 0.01517 0.00870 -0.0509 0.0061 1.0000
9.000 1.2029 0.01557 0.00916 -0.0493 0.0057 1.0000
9.250 1.2192 0.01600 0.00964 -0.0474 0.0054 1.0000
9.500 1.2346 0.01646 0.01014 -0.0453 0.0050 1.0000
9.750 1.2489 0.01698 0.01070 -0.0431 0.0046 1.0000
10.000 1.2616 0.01762 0.01139 -0.0407 0.0043 1.0000
10.250 1.2755 0.01819 0.01203 -0.0385 0.0041 1.0000
10.500 1.2891 0.01879 0.01269 -0.0364 0.0039 1.0000
10.750 1.3028 0.01939 0.01335 -0.0344 0.0037 1.0000
11.000 1.3145 0.02011 0.01415 -0.0321 0.0036 1.0000
11.250 1.3287 0.02070 0.01480 -0.0303 0.0033 1.0000
11.500 1.3399 0.02147 0.01564 -0.0282 0.0032 1.0000
11.750 1.3500 0.02234 0.01658 -0.0261 0.0031 1.0000
12.000 1.3589 0.02330 0.01761 -0.0239 0.0029 1.0000
12.250 1.3659 0.02443 0.01883 -0.0216 0.0028 1.0000
12.500 1.3693 0.02584 0.02034 -0.0191 0.0027 1.0000
12.750 1.3757 0.02710 0.02169 -0.0171 0.0027 1.0000
13.000 1.3823 0.02839 0.02308 -0.0152 0.0026 1.0000
13.250 1.3880 0.02980 0.02459 -0.0135 0.0025 1.0000
13.500 1.3921 0.03141 0.02630 -0.0119 0.0025 1.0000
13.750 1.3939 0.03329 0.02831 -0.0103 0.0024 1.0000
14.000 1.3969 0.03516 0.03028 -0.0090 0.0023 1.0000
14.250 1.4000 0.03711 0.03233 -0.0080 0.0022 1.0000
14.500 1.3977 0.03969 0.03503 -0.0070 0.0022 1.0000
14.750 1.3982 0.04212 0.03758 -0.0064 0.0022 1.0000
15.000 1.3956 0.04502 0.04059 -0.0061 0.0021 1.0000
15.250 1.3949 0.04783 0.04350 -0.0060 0.0021 1.0000
15.500 1.3839 0.05210 0.04793 -0.0063 0.0021 1.0000
15.750 1.3798 0.05570 0.05165 -0.0070 0.0021 1.0000
16.000 1.3735 0.05978 0.05584 -0.0079 0.0020 1.0000
16.250 1.3757 0.06278 0.05892 -0.0088 0.0019 1.0000
16.500 1.3560 0.06919 0.06551 -0.0109 0.0020 1.0000
16.750 1.3554 0.07281 0.06920 -0.0122 0.0019 1.0000
17.000 1.3263 0.08106 0.07766 -0.0153 0.0020 1.0000
17.250 1.3247 0.08506 0.08173 -0.0170 0.0019 1.0000
17.500 1.3116 0.09099 0.08779 -0.0195 0.0019 1.0000
17.750 1.2969 0.09733 0.09424 -0.0222 0.0019 1.0000
18.000 1.2763 0.10496 0.10201 -0.0257 0.0019 1.0000
18.250 1.2631 0.11142 0.10858 -0.0287 0.0019 1.0000
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