GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 50,000 Max Cl/Cd: 38.63 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe335-il-50000.txt Download as CSV file: xf-goe335-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3300 0.10205 0.09549 -0.0220 1.0000 0.1302
-7.500 -0.3406 0.10160 0.09520 -0.0226 1.0000 0.1331
-7.250 -0.3495 0.10184 0.09559 -0.0267 1.0000 0.1342
-7.000 -0.3298 0.09458 0.08833 -0.0211 1.0000 0.1411
-6.750 -0.3325 0.09314 0.08700 -0.0229 1.0000 0.1466
-6.500 -0.3324 0.09068 0.08466 -0.0243 1.0000 0.1499
-6.250 -0.3256 0.08728 0.08129 -0.0222 1.0000 0.1588
-6.000 -0.3268 0.08574 0.07986 -0.0254 1.0000 0.1637
-5.750 -0.3213 0.08231 0.07649 -0.0225 1.0000 0.1736
-5.000 -0.3143 0.07462 0.06903 -0.0210 1.0000 0.1984
-4.750 -0.3114 0.07239 0.06684 -0.0219 1.0000 0.2086
-4.500 -0.3066 0.07027 0.06473 -0.0226 1.0000 0.2216
-4.250 -0.3014 0.06780 0.06229 -0.0222 1.0000 0.2358
-4.000 -0.2963 0.06510 0.05962 -0.0209 1.0000 0.2509
-3.750 -0.2911 0.06239 0.05695 -0.0190 1.0000 0.2680
-3.500 -0.2840 0.05993 0.05448 -0.0184 1.0000 0.2948
-3.250 -0.2800 0.05735 0.05196 -0.0156 1.0000 0.3260
-3.000 -0.2770 0.05486 0.04955 -0.0126 1.0000 0.3674
-2.750 -0.2779 0.05248 0.04726 -0.0082 1.0000 0.4218
-2.500 -0.2816 0.04985 0.04477 -0.0016 1.0000 0.4700
-2.250 -0.2835 0.04741 0.04243 0.0041 1.0000 0.5236
-2.000 -0.2841 0.04490 0.04003 0.0099 1.0000 0.5691
-1.750 -0.2799 0.04244 0.03764 0.0140 1.0000 0.6110
-1.500 -0.2716 0.04002 0.03526 0.0170 1.0000 0.6457
-1.250 -0.2565 0.03762 0.03288 0.0177 1.0000 0.6780
-1.000 0.0083 0.03514 0.02691 -0.0483 1.0000 0.2013
-0.750 0.0370 0.03385 0.02512 -0.0493 1.0000 0.1891
-0.500 0.0756 0.03266 0.02332 -0.0516 0.9958 0.1765
-0.250 0.1369 0.03117 0.02136 -0.0580 0.9806 0.1698
0.000 0.1946 0.03022 0.01995 -0.0635 0.9629 0.1699
0.250 0.2552 0.02952 0.01891 -0.0693 0.9447 0.1854
0.500 0.3157 0.02868 0.01783 -0.0746 0.9261 0.2011
0.750 0.3683 0.02775 0.01703 -0.0786 0.9053 0.2411
1.000 0.4332 0.02502 0.01560 -0.0837 0.8878 1.0000
1.250 0.4850 0.02506 0.01527 -0.0875 0.8636 1.0000
1.500 0.5483 0.02472 0.01467 -0.0926 0.8441 1.0000
1.750 0.5902 0.02470 0.01452 -0.0941 0.8192 1.0000
2.000 0.6313 0.02469 0.01439 -0.0953 0.7964 1.0000
2.250 0.6697 0.02471 0.01430 -0.0959 0.7748 1.0000
2.500 0.6982 0.02509 0.01461 -0.0953 0.7524 1.0000
2.750 0.7283 0.02540 0.01487 -0.0949 0.7330 1.0000
3.000 0.7584 0.02568 0.01509 -0.0944 0.7159 1.0000
3.250 0.7810 0.02638 0.01578 -0.0934 0.6979 1.0000
3.500 0.8049 0.02705 0.01644 -0.0925 0.6823 1.0000
3.750 0.8292 0.02773 0.01717 -0.0917 0.6679 1.0000
4.000 0.8537 0.02842 0.01789 -0.0910 0.6549 1.0000
4.250 0.8801 0.02901 0.01850 -0.0904 0.6432 1.0000
4.500 0.9031 0.02986 0.01941 -0.0897 0.6312 1.0000
4.750 0.9229 0.03097 0.02062 -0.0888 0.6189 1.0000
5.000 0.9426 0.03210 0.02192 -0.0879 0.6069 1.0000
5.250 0.9638 0.03309 0.02302 -0.0869 0.5952 1.0000
5.500 0.9876 0.03386 0.02390 -0.0860 0.5840 1.0000
5.750 1.0155 0.03432 0.02446 -0.0853 0.5736 1.0000
6.000 1.0294 0.03603 0.02642 -0.0841 0.5618 1.0000
6.250 1.0440 0.03777 0.02836 -0.0830 0.5508 1.0000
6.500 1.0638 0.03910 0.02988 -0.0821 0.5408 1.0000
6.750 1.0926 0.03964 0.03060 -0.0814 0.5310 1.0000
7.000 1.0970 0.04243 0.03364 -0.0800 0.5198 1.0000
7.250 1.1031 0.04516 0.03659 -0.0788 0.5091 1.0000
7.500 1.1193 0.04677 0.03849 -0.0774 0.4972 1.0000
7.750 1.1391 0.04780 0.03977 -0.0758 0.4834 1.0000
8.000 1.2138 0.03957 0.03157 -0.0714 0.4384 1.0000
8.250 1.2488 0.03480 0.02655 -0.0668 0.3851 1.0000
8.500 1.2554 0.03284 0.02464 -0.0613 0.3352 1.0000
8.750 1.2435 0.03219 0.02412 -0.0544 0.2637 1.0000
9.000 1.2236 0.03430 0.02526 -0.0483 0.1686 1.0000
9.250 1.2119 0.03761 0.02801 -0.0441 0.1336 1.0000
9.500 1.2064 0.04043 0.03064 -0.0407 0.1167 1.0000
9.750 1.2049 0.04313 0.03325 -0.0380 0.1052 1.0000
10.000 1.2079 0.04580 0.03589 -0.0357 0.0959 1.0000
10.250 1.2277 0.04842 0.03836 -0.0340 0.0877 1.0000
10.500 1.2676 0.05150 0.04172 -0.0337 0.0814 1.0000
10.750 1.3189 0.05687 0.04716 -0.0358 0.0760 1.0000
11.000 1.3204 0.06003 0.05083 -0.0334 0.0747 1.0000
11.250 1.3173 0.06342 0.05466 -0.0310 0.0736 1.0000
11.500 1.3099 0.06699 0.05859 -0.0286 0.0730 1.0000
11.750 1.2993 0.07082 0.06276 -0.0266 0.0728 1.0000
12.000 1.2849 0.07500 0.06725 -0.0253 0.0729 1.0000
12.250 1.2683 0.07956 0.07208 -0.0248 0.0734 1.0000
12.500 1.2486 0.08465 0.07742 -0.0253 0.0738 1.0000
12.750 1.2280 0.09028 0.08326 -0.0267 0.0743 1.0000
13.000 1.2073 0.09648 0.08965 -0.0290 0.0750 1.0000
13.250 1.1872 0.10327 0.09657 -0.0320 0.0756 1.0000
13.500 1.1706 0.11040 0.10381 -0.0352 0.0763 1.0000
13.750 1.0807 0.13240 0.12597 -0.0541 0.0876 1.0000
14.000 1.0736 0.14012 0.13367 -0.0574 0.0888 1.0000
14.250 1.0256 0.16062 0.15396 -0.0720 0.0991 1.0000
14.500 1.0325 0.16587 0.15923 -0.0730 0.1010 1.0000
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Polar data table (+)
Polar graphs
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