GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il) Reynolds number: 50,000 Max Cl/Cd: 29.32 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe320-il-50000.txt Download as CSV file: xf-goe320-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 320 (HANSA-BRANDENBURG II.1) 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3437 0.12667 0.12105 -0.0099 1.0000 0.1333
-7.250 -0.3670 0.12705 0.12151 -0.0086 1.0000 0.1338
-7.000 -0.3859 0.12726 0.12178 -0.0102 1.0000 0.1343
-6.750 -0.3755 0.12193 0.11652 -0.0064 1.0000 0.1359
-6.500 -0.3697 0.11853 0.11316 -0.0037 1.0000 0.1383
-6.250 -0.3726 0.11644 0.11111 -0.0024 1.0000 0.1410
-6.000 -0.3780 0.11463 0.10936 -0.0020 1.0000 0.1439
-5.750 -0.3851 0.11320 0.10795 -0.0033 1.0000 0.1473
-5.500 -0.3919 0.11372 0.10838 -0.0125 1.0000 0.1500
-5.250 -0.3886 0.10855 0.10336 -0.0064 1.0000 0.1519
-5.000 -0.3856 0.10560 0.10046 -0.0036 1.0000 0.1553
-4.750 -0.3826 0.10331 0.09819 -0.0040 1.0000 0.1602
-4.500 -0.3719 0.10223 0.09699 -0.0137 1.0000 0.1665
-4.250 -0.3708 0.09821 0.09308 -0.0091 1.0000 0.1689
-4.000 -0.3655 0.09557 0.09049 -0.0077 1.0000 0.1735
-3.750 -0.3446 0.09419 0.08894 -0.0167 1.0000 0.1835
-3.500 -0.3430 0.09051 0.08538 -0.0129 1.0000 0.1865
-3.250 -0.2808 0.08653 0.08129 -0.0249 0.9820 0.2039
-3.000 -0.2345 0.08307 0.07774 -0.0327 0.9637 0.2222
-2.750 -0.1971 0.07999 0.07464 -0.0378 0.9488 0.2421
-2.500 -0.1575 0.07763 0.07218 -0.0443 0.9346 0.2756
-2.250 -0.1250 0.07467 0.06926 -0.0466 0.9216 0.3139
-2.000 -0.1088 0.07217 0.06687 -0.0451 0.9085 0.3541
-1.500 -0.0811 0.06763 0.06259 -0.0379 0.8818 0.4726
-1.250 -0.0617 0.06520 0.06029 -0.0338 0.8689 0.5344
-1.000 -0.0496 0.06329 0.05847 -0.0303 0.8533 0.5792
-0.750 -0.0301 0.06126 0.05650 -0.0282 0.8374 0.6192
-0.500 0.0009 0.05909 0.05435 -0.0291 0.8208 0.6502
-0.250 0.0594 0.05710 0.05224 -0.0380 0.8019 0.6640
0.000 0.1632 0.05479 0.04955 -0.0591 0.7802 0.6207
0.250 0.3648 0.05471 0.04703 -0.0994 0.7566 0.2862
0.500 0.4163 0.05403 0.04570 -0.1019 0.7386 0.2328
0.750 0.4582 0.05310 0.04439 -0.1029 0.7210 0.2136
1.000 0.4983 0.05249 0.04334 -0.1033 0.7038 0.1991
1.250 0.5342 0.05146 0.04213 -0.1036 0.6875 0.1914
1.500 0.6031 0.04877 0.03902 -0.1061 0.6808 0.1872
1.750 0.6291 0.04846 0.03855 -0.1049 0.6641 0.1901
2.000 0.6544 0.04839 0.03829 -0.1036 0.6479 0.1921
2.250 0.6786 0.04843 0.03817 -0.1023 0.6327 0.1965
2.500 0.7402 0.04498 0.03458 -0.1027 0.6271 0.2144
2.750 0.7620 0.04464 0.03425 -0.1009 0.6112 0.2308
3.000 0.7876 0.04392 0.03361 -0.0994 0.5961 0.2620
3.250 0.8183 0.04117 0.03237 -0.0974 0.5839 1.0000
3.500 0.8716 0.03880 0.02914 -0.0966 0.5749 1.0000
3.750 0.8909 0.03927 0.02939 -0.0949 0.5601 1.0000
4.000 0.9134 0.03958 0.02950 -0.0935 0.5469 1.0000
4.250 0.9685 0.03713 0.02667 -0.0940 0.5389 1.0000
4.500 0.9835 0.03810 0.02757 -0.0923 0.5245 1.0000
4.750 1.0025 0.03878 0.02815 -0.0909 0.5112 1.0000
5.000 1.0329 0.03854 0.02774 -0.0901 0.4993 1.0000
5.250 1.0804 0.03701 0.02590 -0.0906 0.4886 1.0000
5.500 1.0947 0.03823 0.02709 -0.0890 0.4750 1.0000
5.750 1.1133 0.03930 0.02811 -0.0877 0.4626 1.0000
6.000 1.1480 0.03928 0.02786 -0.0877 0.4517 1.0000
6.250 1.1733 0.04002 0.02849 -0.0871 0.4400 1.0000
6.500 1.1817 0.04211 0.03064 -0.0852 0.4286 1.0000
6.750 1.2206 0.04220 0.03046 -0.0858 0.4189 1.0000
7.000 1.2174 0.04513 0.03361 -0.0831 0.4090 1.0000
7.250 1.2510 0.04585 0.03413 -0.0834 0.4011 1.0000
7.500 1.2181 0.05108 0.03976 -0.0789 0.3939 1.0000
7.750 1.2491 0.05201 0.04059 -0.0791 0.3878 1.0000
8.000 1.2376 0.05621 0.04492 -0.0766 0.3830 1.0000
8.250 0.7800 0.12232 0.11232 -0.0908 0.4351 1.0000
8.500 0.8178 0.12248 0.11234 -0.0893 0.4197 1.0000
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Polar data table (+)
Polar graphs
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