GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 575 AIRFOIL (goe575-il) Reynolds number: 100,000 Max Cl/Cd: 44.6 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe575-il-100000-n5.txt Download as CSV file: xf-goe575-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 575 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5042 0.09653 0.09123 -0.0345 1.0000 0.0585
-9.500 -0.5179 0.09180 0.08654 -0.0356 1.0000 0.0583
-9.250 -0.5391 0.08634 0.08113 -0.0373 1.0000 0.0580
-9.000 -0.5694 0.08065 0.07545 -0.0378 1.0000 0.0577
-8.750 -0.6101 0.07528 0.07005 -0.0348 1.0000 0.0575
-8.500 -0.6476 0.07095 0.06565 -0.0297 1.0000 0.0572
-8.250 -0.6893 0.06451 0.05900 -0.0242 1.0000 0.0570
-8.000 -0.7264 0.05849 0.05268 -0.0178 1.0000 0.0569
-7.750 -0.7588 0.05316 0.04691 -0.0105 1.0000 0.0575
-7.500 -0.7790 0.04809 0.04116 -0.0046 0.9972 0.0584
-7.250 -0.7758 0.04434 0.03674 -0.0018 0.9906 0.0591
-7.000 -0.7561 0.04256 0.03475 -0.0012 0.9859 0.0597
-6.750 -0.7386 0.04082 0.03279 0.0001 0.9799 0.0604
-6.500 -0.7183 0.03929 0.03102 0.0011 0.9745 0.0613
-6.250 -0.6975 0.03780 0.02928 0.0021 0.9689 0.0623
-6.000 -0.6773 0.03640 0.02760 0.0033 0.9629 0.0635
-5.750 -0.6521 0.03493 0.02575 0.0037 0.9579 0.0651
-5.500 -0.6303 0.03349 0.02396 0.0049 0.9512 0.0660
-5.250 -0.5987 0.03228 0.02247 0.0041 0.9472 0.0669
-5.000 -0.5738 0.03126 0.02142 0.0046 0.9400 0.0678
-4.750 -0.5394 0.03056 0.02069 0.0032 0.9358 0.0698
-4.500 -0.5144 0.02974 0.01977 0.0038 0.9278 0.0715
-4.250 -0.4771 0.02889 0.01878 0.0019 0.9238 0.0731
-4.000 -0.4498 0.02806 0.01783 0.0021 0.9157 0.0745
-3.750 -0.4125 0.02731 0.01704 0.0003 0.9109 0.0760
-3.500 -0.3862 0.02672 0.01648 0.0006 0.9022 0.0784
-3.250 -0.3500 0.02611 0.01584 -0.0009 0.8964 0.0819
-3.000 -0.3205 0.02551 0.01520 -0.0011 0.8878 0.0846
-2.750 -0.2864 0.02493 0.01466 -0.0022 0.8806 0.0879
-2.500 -0.2548 0.02438 0.01409 -0.0027 0.8721 0.0927
-2.250 -0.2217 0.02382 0.01359 -0.0036 0.8635 0.1002
-2.000 -0.1901 0.02328 0.01310 -0.0041 0.8536 0.1109
-1.750 -0.1545 0.02267 0.01258 -0.0052 0.8444 0.1282
-1.500 -0.1250 0.02224 0.01219 -0.0053 0.8317 0.1454
-1.250 -0.0864 0.02172 0.01168 -0.0070 0.8245 0.1671
-1.000 -0.0590 0.02143 0.01141 -0.0067 0.8108 0.1858
-0.750 -0.0256 0.02103 0.01103 -0.0075 0.7986 0.2009
-0.500 0.0167 0.02047 0.01051 -0.0101 0.7902 0.2178
-0.250 0.0605 0.02004 0.01013 -0.0133 0.7773 0.2389
0.000 0.1240 0.01937 0.00964 -0.0207 0.7657 0.2759
0.500 0.4819 0.01865 0.01079 -0.0836 0.7344 1.0000
0.750 0.5348 0.01827 0.01015 -0.0886 0.7095 1.0000
1.000 0.5845 0.01808 0.00970 -0.0930 0.6839 1.0000
1.250 0.6239 0.01808 0.00950 -0.0953 0.6596 1.0000
1.500 0.6575 0.01816 0.00941 -0.0965 0.6350 1.0000
1.750 0.6883 0.01829 0.00937 -0.0970 0.6122 1.0000
2.000 0.7163 0.01845 0.00937 -0.0970 0.5906 1.0000
2.250 0.7405 0.01865 0.00942 -0.0962 0.5685 1.0000
2.500 0.7622 0.01887 0.00950 -0.0949 0.5467 1.0000
2.750 0.7822 0.01912 0.00960 -0.0932 0.5242 1.0000
3.000 0.8017 0.01938 0.00971 -0.0914 0.5039 1.0000
3.250 0.8210 0.01964 0.00985 -0.0896 0.4858 1.0000
3.500 0.8409 0.01991 0.01004 -0.0880 0.4705 1.0000
3.750 0.8604 0.02018 0.01022 -0.0863 0.4559 1.0000
4.000 0.8805 0.02048 0.01042 -0.0847 0.4433 1.0000
4.250 0.8994 0.02076 0.01066 -0.0828 0.4304 1.0000
4.500 0.9184 0.02106 0.01092 -0.0811 0.4184 1.0000
4.750 0.9372 0.02138 0.01116 -0.0793 0.4078 1.0000
5.000 0.9556 0.02168 0.01146 -0.0774 0.3967 1.0000
5.250 0.9743 0.02202 0.01176 -0.0756 0.3871 1.0000
5.500 0.9925 0.02235 0.01208 -0.0737 0.3773 1.0000
5.750 1.0108 0.02270 0.01242 -0.0719 0.3680 1.0000
6.000 1.0278 0.02306 0.01278 -0.0698 0.3585 1.0000
6.250 1.0450 0.02343 0.01315 -0.0677 0.3493 1.0000
6.500 1.0611 0.02381 0.01353 -0.0655 0.3400 1.0000
6.750 1.0777 0.02421 0.01394 -0.0634 0.3312 1.0000
7.000 1.0926 0.02463 0.01436 -0.0609 0.3218 1.0000
7.250 1.1081 0.02505 0.01481 -0.0587 0.3129 1.0000
7.500 1.1220 0.02549 0.01526 -0.0561 0.3038 1.0000
7.750 1.1352 0.02593 0.01576 -0.0534 0.2937 1.0000
8.000 1.1466 0.02641 0.01620 -0.0504 0.2844 1.0000
8.250 1.1576 0.02687 0.01673 -0.0474 0.2731 1.0000
8.500 1.1685 0.02738 0.01724 -0.0445 0.2637 1.0000
8.750 1.1782 0.02791 0.01780 -0.0413 0.2532 1.0000
9.000 1.1888 0.02846 0.01840 -0.0384 0.2436 1.0000
9.250 1.1978 0.02908 0.01900 -0.0353 0.2350 1.0000
9.500 1.2094 0.02967 0.01969 -0.0327 0.2269 1.0000
9.750 1.2188 0.03035 0.02038 -0.0298 0.2200 1.0000
10.000 1.2292 0.03103 0.02114 -0.0271 0.2130 1.0000
10.250 1.2375 0.03178 0.02194 -0.0242 0.2061 1.0000
10.500 1.2459 0.03257 0.02277 -0.0214 0.1998 1.0000
10.750 1.2537 0.03341 0.02368 -0.0186 0.1929 1.0000
11.000 1.2587 0.03437 0.02463 -0.0155 0.1873 1.0000
11.250 1.2662 0.03531 0.02572 -0.0128 0.1801 1.0000
11.500 1.2706 0.03640 0.02684 -0.0099 0.1744 1.0000
11.750 1.2753 0.03754 0.02805 -0.0072 0.1686 1.0000
12.000 1.2796 0.03875 0.02937 -0.0045 0.1625 1.0000
12.250 1.2812 0.04013 0.03077 -0.0017 0.1577 1.0000
12.500 1.2843 0.04153 0.03231 0.0008 0.1516 1.0000
12.750 1.2847 0.04312 0.03401 0.0032 0.1456 1.0000
13.000 1.2838 0.04489 0.03577 0.0057 0.1414 1.0000
13.250 1.2853 0.04664 0.03771 0.0077 0.1356 1.0000
13.500 1.2836 0.04866 0.03983 0.0096 0.1307 1.0000
13.750 1.2807 0.05085 0.04201 0.0114 0.1272 1.0000
14.000 1.2800 0.05308 0.04445 0.0128 0.1224 1.0000
14.250 1.2775 0.05549 0.04697 0.0141 0.1187 1.0000
14.500 1.2734 0.05813 0.04966 0.0151 0.1155 1.0000
14.750 1.2702 0.06083 0.05242 0.0160 0.1126 1.0000
15.000 1.2679 0.06356 0.05530 0.0167 0.1098 1.0000
15.250 1.2644 0.06648 0.05834 0.0172 0.1072 1.0000
15.500 1.2614 0.06939 0.06135 0.0176 0.1053 1.0000
15.750 1.2582 0.07234 0.06437 0.0178 0.1034 1.0000
16.000 1.2580 0.07496 0.06701 0.0182 0.1020 1.0000
16.250 1.2528 0.07839 0.07060 0.0181 0.1002 1.0000
16.500 1.2487 0.08174 0.07411 0.0180 0.0989 1.0000
16.750 1.2415 0.08561 0.07814 0.0175 0.0972 1.0000
17.000 1.2348 0.08949 0.08215 0.0169 0.0958 1.0000
17.250 1.2276 0.09348 0.08627 0.0161 0.0945 1.0000
17.500 1.2215 0.09733 0.09023 0.0153 0.0933 1.0000
17.750 1.2185 0.10070 0.09366 0.0147 0.0920 1.0000
18.000 1.2181 0.10368 0.09671 0.0142 0.0910 1.0000
18.250 1.2073 0.10850 0.10166 0.0127 0.0898 1.0000
18.500 1.1756 0.11725 0.11067 0.0089 0.0890 1.0000
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