GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 546 AIRFOIL (goe546-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.67 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe546-il-1000000-n5.txt Download as CSV file: xf-goe546-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 546 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9838 0.04190 0.03940 -0.0847 1.0000 0.0069
-14.250 -1.0306 0.03438 0.03164 -0.0899 1.0000 0.0068
-14.000 -1.0441 0.03157 0.02867 -0.0880 1.0000 0.0069
-13.750 -1.0449 0.02921 0.02615 -0.0868 0.9998 0.0070
-13.500 -1.0249 0.02689 0.02365 -0.0890 0.9979 0.0072
-13.250 -1.0020 0.02506 0.02166 -0.0908 0.9957 0.0074
-13.000 -0.9781 0.02357 0.02003 -0.0921 0.9936 0.0077
-12.750 -0.9545 0.02226 0.01859 -0.0929 0.9907 0.0079
-12.500 -0.9288 0.02108 0.01727 -0.0940 0.9881 0.0082
-12.250 -0.9015 0.02001 0.01607 -0.0951 0.9861 0.0084
-12.000 -0.8776 0.01909 0.01503 -0.0953 0.9823 0.0087
-11.750 -0.8517 0.01825 0.01407 -0.0958 0.9784 0.0089
-11.250 -0.8003 0.01653 0.01217 -0.0965 0.9680 0.0098
-10.750 -0.7398 0.01517 0.01064 -0.0986 0.9571 0.0109
-10.500 -0.7053 0.01456 0.00994 -0.1006 0.9528 0.0114
-10.250 -0.6708 0.01394 0.00925 -0.1025 0.9473 0.0123
-10.000 -0.6358 0.01343 0.00869 -0.1044 0.9406 0.0131
-9.750 -0.6013 0.01298 0.00815 -0.1061 0.9329 0.0141
-9.500 -0.5691 0.01257 0.00764 -0.1073 0.9234 0.0148
-9.250 -0.5403 0.01224 0.00725 -0.1078 0.9144 0.0157
-9.000 -0.5120 0.01200 0.00696 -0.1080 0.9065 0.0166
-8.750 -0.4854 0.01179 0.00670 -0.1078 0.8984 0.0176
-8.500 -0.4587 0.01159 0.00640 -0.1077 0.8910 0.0185
-8.250 -0.4329 0.01132 0.00607 -0.1073 0.8845 0.0191
-8.000 -0.4067 0.01109 0.00581 -0.1071 0.8790 0.0200
-7.750 -0.3800 0.01092 0.00560 -0.1069 0.8744 0.0207
-7.500 -0.3533 0.01077 0.00542 -0.1067 0.8694 0.0216
-7.250 -0.3268 0.01058 0.00518 -0.1064 0.8643 0.0224
-7.000 -0.3001 0.01042 0.00495 -0.1062 0.8599 0.0231
-6.750 -0.2733 0.01025 0.00475 -0.1060 0.8556 0.0235
-6.500 -0.2474 0.00994 0.00438 -0.1056 0.8510 0.0242
-6.250 -0.2213 0.00967 0.00407 -0.1053 0.8463 0.0251
-6.000 -0.1946 0.00949 0.00387 -0.1051 0.8418 0.0259
-5.750 -0.1678 0.00931 0.00367 -0.1049 0.8368 0.0267
-5.500 -0.1411 0.00912 0.00344 -0.1046 0.8322 0.0274
-5.250 -0.1142 0.00896 0.00323 -0.1044 0.8276 0.0281
-5.000 -0.0873 0.00879 0.00303 -0.1041 0.8222 0.0287
-4.750 -0.0606 0.00863 0.00282 -0.1038 0.8162 0.0292
-4.500 -0.0338 0.00849 0.00264 -0.1036 0.8096 0.0295
-4.250 -0.0077 0.00830 0.00238 -0.1032 0.8001 0.0303
-4.000 0.0187 0.00811 0.00216 -0.1028 0.7902 0.0315
-3.750 0.0452 0.00799 0.00199 -0.1024 0.7811 0.0324
-3.500 0.0721 0.00787 0.00184 -0.1022 0.7722 0.0334
-3.250 0.0989 0.00777 0.00171 -0.1019 0.7633 0.0344
-3.000 0.1256 0.00769 0.00158 -0.1015 0.7530 0.0355
-2.750 0.1524 0.00762 0.00147 -0.1012 0.7413 0.0366
-2.500 0.1789 0.00755 0.00136 -0.1008 0.7282 0.0389
-2.250 0.2051 0.00750 0.00127 -0.1004 0.7137 0.0428
-2.000 0.2313 0.00746 0.00120 -0.1000 0.6984 0.0476
-1.750 0.2573 0.00743 0.00114 -0.0995 0.6826 0.0564
-1.500 0.2832 0.00740 0.00109 -0.0991 0.6676 0.0691
-1.250 0.3091 0.00735 0.00105 -0.0986 0.6535 0.0894
-1.000 0.3347 0.00723 0.00101 -0.0982 0.6405 0.1338
-0.750 0.3598 0.00704 0.00098 -0.0977 0.6285 0.2059
-0.500 0.3854 0.00692 0.00098 -0.0973 0.6166 0.2667
-0.250 0.4117 0.00683 0.00099 -0.0970 0.6072 0.3099
0.250 0.4630 0.00652 0.00107 -0.0962 0.5914 0.4614
0.500 0.4887 0.00646 0.00112 -0.0957 0.5816 0.5159
0.750 0.5145 0.00646 0.00117 -0.0953 0.5685 0.5495
1.000 0.5399 0.00651 0.00121 -0.0947 0.5482 0.5742
1.250 0.5644 0.00662 0.00127 -0.0940 0.5201 0.5993
1.500 0.5877 0.00679 0.00135 -0.0931 0.4812 0.6275
1.750 0.6113 0.00690 0.00145 -0.0922 0.4530 0.6671
2.000 0.6347 0.00693 0.00156 -0.0913 0.4327 0.7223
2.250 0.6560 0.00687 0.00168 -0.0898 0.4149 0.8139
2.500 0.6776 0.00682 0.00181 -0.0883 0.3945 0.9077
2.750 0.7310 0.00719 0.00203 -0.0943 0.3462 0.9991
3.000 0.7524 0.00760 0.00222 -0.0931 0.2993 1.0000
3.250 0.7729 0.00805 0.00244 -0.0918 0.2536 1.0000
3.500 0.7945 0.00843 0.00265 -0.0906 0.2204 1.0000
3.750 0.8170 0.00876 0.00285 -0.0896 0.1938 1.0000
4.000 0.8392 0.00912 0.00306 -0.0885 0.1640 1.0000
4.250 0.8559 0.00988 0.00347 -0.0866 0.0962 1.0000
4.500 0.8782 0.01023 0.00373 -0.0856 0.0767 1.0000
4.750 0.8984 0.01075 0.00406 -0.0842 0.0429 1.0000
5.000 0.9217 0.01102 0.00429 -0.0834 0.0361 1.0000
5.250 0.9457 0.01124 0.00451 -0.0826 0.0345 1.0000
5.500 0.9694 0.01147 0.00474 -0.0819 0.0334 1.0000
5.750 0.9929 0.01172 0.00499 -0.0811 0.0323 1.0000
6.000 1.0159 0.01199 0.00525 -0.0802 0.0313 1.0000
6.250 1.0388 0.01226 0.00553 -0.0793 0.0303 1.0000
6.500 1.0614 0.01255 0.00584 -0.0784 0.0296 1.0000
6.750 1.0834 0.01287 0.00618 -0.0774 0.0288 1.0000
7.000 1.1048 0.01321 0.00655 -0.0762 0.0280 1.0000
7.250 1.1268 0.01350 0.00685 -0.0752 0.0278 1.0000
7.500 1.1484 0.01379 0.00718 -0.0742 0.0276 1.0000
7.750 1.1698 0.01410 0.00751 -0.0731 0.0273 1.0000
8.000 1.1908 0.01439 0.00783 -0.0720 0.0268 1.0000
8.250 1.2111 0.01472 0.00817 -0.0707 0.0262 1.0000
8.500 1.2299 0.01503 0.00853 -0.0691 0.0254 1.0000
8.750 1.2479 0.01537 0.00889 -0.0674 0.0248 1.0000
9.000 1.2651 0.01575 0.00929 -0.0656 0.0242 1.0000
9.250 1.2822 0.01613 0.00969 -0.0639 0.0234 1.0000
9.500 1.2978 0.01661 0.01019 -0.0619 0.0227 1.0000
9.750 1.3111 0.01721 0.01084 -0.0596 0.0218 1.0000
10.000 1.3292 0.01756 0.01122 -0.0581 0.0215 1.0000
10.250 1.3468 0.01792 0.01162 -0.0566 0.0210 1.0000
10.500 1.3637 0.01834 0.01208 -0.0551 0.0205 1.0000
10.750 1.3801 0.01879 0.01256 -0.0535 0.0198 1.0000
11.000 1.3964 0.01926 0.01306 -0.0519 0.0190 1.0000
11.250 1.4121 0.01975 0.01357 -0.0504 0.0181 1.0000
11.500 1.4270 0.02032 0.01414 -0.0487 0.0171 1.0000
11.750 1.4412 0.02093 0.01479 -0.0471 0.0164 1.0000
12.000 1.4550 0.02158 0.01550 -0.0454 0.0156 1.0000
12.250 1.4686 0.02226 0.01620 -0.0439 0.0146 1.0000
12.500 1.4815 0.02301 0.01697 -0.0423 0.0137 1.0000
12.750 1.4932 0.02386 0.01785 -0.0406 0.0128 1.0000
13.000 1.5042 0.02478 0.01882 -0.0390 0.0120 1.0000
13.250 1.5145 0.02578 0.01986 -0.0374 0.0112 1.0000
13.500 1.5234 0.02691 0.02102 -0.0358 0.0102 1.0000
13.750 1.5321 0.02809 0.02226 -0.0342 0.0098 1.0000
14.000 1.5402 0.02935 0.02359 -0.0327 0.0092 1.0000
14.250 1.5477 0.03071 0.02502 -0.0313 0.0089 1.0000
14.500 1.5538 0.03222 0.02659 -0.0299 0.0084 1.0000
14.750 1.5588 0.03387 0.02831 -0.0286 0.0080 1.0000
15.000 1.5632 0.03564 0.03015 -0.0274 0.0077 1.0000
15.250 1.5672 0.03751 0.03210 -0.0264 0.0075 1.0000
15.500 1.5711 0.03945 0.03413 -0.0255 0.0072 1.0000
15.750 1.5745 0.04153 0.03629 -0.0247 0.0070 1.0000
16.000 1.5763 0.04384 0.03870 -0.0241 0.0069 1.0000
16.250 1.5774 0.04632 0.04126 -0.0236 0.0066 1.0000
16.500 1.5774 0.04902 0.04404 -0.0234 0.0064 1.0000
16.750 1.5768 0.05189 0.04701 -0.0233 0.0062 1.0000
17.000 1.5747 0.05502 0.05023 -0.0234 0.0060 1.0000
17.250 1.5707 0.05850 0.05381 -0.0237 0.0059 1.0000
17.500 1.5659 0.06221 0.05762 -0.0242 0.0058 1.0000
17.750 1.5604 0.06613 0.06165 -0.0249 0.0056 1.0000
18.000 1.5554 0.07007 0.06570 -0.0259 0.0055 1.0000
18.250 1.5505 0.07412 0.06985 -0.0270 0.0054 1.0000
18.500 1.5421 0.07884 0.07469 -0.0284 0.0054 1.0000
18.750 1.5343 0.08360 0.07957 -0.0301 0.0053 1.0000
19.000 1.5252 0.08866 0.08475 -0.0320 0.0052 1.0000
19.250 1.5141 0.09422 0.09043 -0.0343 0.0051 1.0000
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Polar data table (+)
Polar graphs
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