GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 100,000 Max Cl/Cd: 59.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe547-il-100000-n5.txt Download as CSV file: xf-goe547-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3878 0.09959 0.09466 -0.0419 1.0000 0.0464
-9.000 -0.4036 0.09588 0.09105 -0.0415 1.0000 0.0450
-8.500 -0.4557 0.08603 0.08140 -0.0440 0.9982 0.0428
-8.250 -0.4249 0.08743 0.08277 -0.0413 0.9964 0.0462
-8.000 -0.4186 0.08255 0.07790 -0.0469 0.9895 0.0471
-7.750 -0.4127 0.07582 0.07116 -0.0553 0.9808 0.0468
-7.500 -0.4070 0.06552 0.06076 -0.0680 0.9707 0.0460
-7.250 -0.4053 0.05314 0.04795 -0.0802 0.9607 0.0453
-7.000 -0.3899 0.04817 0.04264 -0.0842 0.9538 0.0464
-6.750 -0.3733 0.04385 0.03792 -0.0869 0.9472 0.0481
-6.500 -0.3544 0.03956 0.03309 -0.0891 0.9410 0.0491
-6.250 -0.3277 0.03567 0.02858 -0.0916 0.9374 0.0499
-6.000 -0.3104 0.03319 0.02563 -0.0910 0.9300 0.0504
-5.750 -0.2823 0.03094 0.02279 -0.0922 0.9257 0.0522
-5.500 -0.2503 0.02902 0.02040 -0.0937 0.9229 0.0537
-5.250 -0.2298 0.02766 0.01886 -0.0928 0.9160 0.0545
-5.000 -0.2000 0.02633 0.01732 -0.0936 0.9119 0.0555
-4.750 -0.1667 0.02512 0.01592 -0.0949 0.9091 0.0566
-4.500 -0.1407 0.02421 0.01485 -0.0948 0.9037 0.0579
-4.250 -0.1129 0.02335 0.01385 -0.0949 0.8986 0.0594
-4.000 -0.0796 0.02251 0.01285 -0.0959 0.8953 0.0618
-3.750 -0.0440 0.02175 0.01195 -0.0975 0.8930 0.0654
-3.500 -0.0240 0.02123 0.01146 -0.0962 0.8852 0.0679
-3.250 0.0078 0.02056 0.01074 -0.0970 0.8814 0.0714
-3.000 0.0432 0.01995 0.01002 -0.0984 0.8787 0.0761
-2.750 0.0647 0.01947 0.00954 -0.0973 0.8713 0.0818
-2.500 0.0957 0.01891 0.00894 -0.0980 0.8669 0.0934
-2.250 0.1299 0.01825 0.00840 -0.0994 0.8639 0.1177
-2.000 0.1520 0.01780 0.00831 -0.0986 0.8568 0.1960
-1.750 0.1818 0.01729 0.00816 -0.0992 0.8520 0.2945
-1.500 0.2155 0.01676 0.00807 -0.1004 0.8489 0.4106
-1.250 0.2367 0.01664 0.00816 -0.0991 0.8413 0.4875
-1.000 0.2670 0.01638 0.00805 -0.0994 0.8366 0.5544
-0.750 0.3009 0.01603 0.00787 -0.1003 0.8334 0.6262
-0.500 0.3204 0.01588 0.00795 -0.0984 0.8254 0.7011
-0.250 0.3960 0.01531 0.00781 -0.1077 0.8248 1.0000
0.000 0.4285 0.01529 0.00764 -0.1086 0.8202 1.0000
0.250 0.4529 0.01542 0.00766 -0.1079 0.8133 1.0000
0.500 0.4805 0.01549 0.00763 -0.1079 0.8071 1.0000
0.750 0.5150 0.01546 0.00750 -0.1090 0.8033 1.0000
1.000 0.5332 0.01571 0.00770 -0.1072 0.7944 1.0000
1.250 0.5652 0.01572 0.00763 -0.1080 0.7897 1.0000
1.500 0.5871 0.01592 0.00781 -0.1068 0.7821 1.0000
1.750 0.6158 0.01599 0.00784 -0.1069 0.7763 1.0000
2.000 0.6431 0.01610 0.00792 -0.1067 0.7703 1.0000
2.250 0.6674 0.01624 0.00806 -0.1060 0.7626 1.0000
2.500 0.6946 0.01623 0.00803 -0.1056 0.7537 1.0000
2.750 0.7271 0.01599 0.00776 -0.1059 0.7430 1.0000
3.000 0.7512 0.01595 0.00770 -0.1047 0.7297 1.0000
3.250 0.7734 0.01603 0.00780 -0.1034 0.7180 1.0000
3.500 0.7988 0.01612 0.00791 -0.1027 0.7087 1.0000
3.750 0.8275 0.01613 0.00794 -0.1026 0.6997 1.0000
4.000 0.8497 0.01626 0.00811 -0.1013 0.6877 1.0000
4.250 0.8736 0.01636 0.00826 -0.1003 0.6758 1.0000
4.500 0.8988 0.01644 0.00838 -0.0995 0.6639 1.0000
4.750 0.9244 0.01653 0.00850 -0.0988 0.6516 1.0000
5.000 0.9488 0.01664 0.00865 -0.0979 0.6379 1.0000
5.250 0.9711 0.01679 0.00886 -0.0966 0.6220 1.0000
5.500 0.9927 0.01697 0.00910 -0.0952 0.6056 1.0000
5.750 1.0139 0.01718 0.00939 -0.0937 0.5894 1.0000
6.000 1.0332 0.01740 0.00966 -0.0918 0.5684 1.0000
6.250 1.0497 0.01763 0.00992 -0.0894 0.5400 1.0000
6.500 1.0651 0.01792 0.01015 -0.0868 0.5047 1.0000
6.750 1.0784 0.01832 0.01041 -0.0839 0.4606 1.0000
7.000 1.0893 0.01890 0.01077 -0.0806 0.4146 1.0000
7.250 1.0982 0.01959 0.01128 -0.0772 0.3753 1.0000
7.750 1.1115 0.02132 0.01268 -0.0700 0.3044 1.0000
8.000 1.1164 0.02236 0.01352 -0.0665 0.2679 1.0000
8.250 1.1218 0.02343 0.01441 -0.0632 0.2312 1.0000
8.500 1.1282 0.02452 0.01535 -0.0602 0.1936 1.0000
8.750 1.1349 0.02567 0.01634 -0.0575 0.1555 1.0000
9.000 1.1384 0.02712 0.01751 -0.0545 0.1254 1.0000
9.250 1.1438 0.02854 0.01883 -0.0519 0.1053 1.0000
9.500 1.1539 0.02971 0.02005 -0.0498 0.0824 1.0000
9.750 1.1597 0.03123 0.02142 -0.0475 0.0615 1.0000
10.000 1.1636 0.03294 0.02307 -0.0450 0.0492 1.0000
10.250 1.1662 0.03479 0.02493 -0.0425 0.0422 1.0000
10.500 1.1711 0.03648 0.02675 -0.0403 0.0373 1.0000
10.750 1.1741 0.03837 0.02867 -0.0382 0.0339 1.0000
11.000 1.1795 0.04010 0.03054 -0.0364 0.0308 1.0000
11.250 1.1839 0.04194 0.03251 -0.0347 0.0288 1.0000
11.500 1.1854 0.04411 0.03475 -0.0330 0.0276 1.0000
11.750 1.1886 0.04622 0.03701 -0.0314 0.0266 1.0000
12.000 1.1920 0.04842 0.03937 -0.0298 0.0255 1.0000
12.250 1.1961 0.05061 0.04171 -0.0285 0.0246 1.0000
12.500 1.1999 0.05288 0.04410 -0.0274 0.0236 1.0000
12.750 1.2034 0.05521 0.04654 -0.0264 0.0227 1.0000
13.000 1.2047 0.05779 0.04919 -0.0256 0.0217 1.0000
13.250 1.2074 0.06047 0.05196 -0.0247 0.0210 1.0000
13.500 1.2119 0.06309 0.05480 -0.0239 0.0205 1.0000
13.750 1.2155 0.06593 0.05786 -0.0231 0.0201 1.0000
14.000 1.2174 0.06903 0.06122 -0.0225 0.0197 1.0000
14.250 1.2168 0.07250 0.06493 -0.0222 0.0194 1.0000
14.500 1.2136 0.07629 0.06897 -0.0221 0.0192 1.0000
14.750 1.2077 0.08050 0.07344 -0.0224 0.0190 1.0000
15.000 1.1991 0.08520 0.07838 -0.0232 0.0188 1.0000
15.250 1.1884 0.09030 0.08374 -0.0244 0.0187 1.0000
15.500 1.1750 0.09601 0.08970 -0.0263 0.0186 1.0000
15.750 1.1599 0.10231 0.09624 -0.0289 0.0186 1.0000
16.000 1.1427 0.10932 0.10350 -0.0323 0.0186 1.0000
16.250 1.1232 0.11730 0.11171 -0.0367 0.0187 1.0000
16.500 1.1011 0.12652 0.12115 -0.0423 0.0189 1.0000
16.750 1.0766 0.13719 0.13203 -0.0491 0.0192 1.0000
17.000 1.0470 0.15050 0.14546 -0.0577 0.0196 1.0000
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