GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 50,000 Max Cl/Cd: 37.94 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe377-il-50000.txt Download as CSV file: xf-goe377-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3833 0.10730 0.10040 -0.0210 1.0000 0.1272
-8.250 -0.3917 0.10633 0.09957 -0.0224 1.0000 0.1314
-8.000 -0.4046 0.10593 0.09932 -0.0236 1.0000 0.1323
-7.750 -0.3838 0.09959 0.09297 -0.0212 1.0000 0.1429
-7.500 -0.3950 0.09866 0.09218 -0.0221 1.0000 0.1456
-7.250 -0.3876 0.09444 0.08798 -0.0205 1.0000 0.1520
-7.000 -0.3907 0.09254 0.08618 -0.0214 1.0000 0.1589
-6.750 -0.3901 0.08937 0.08310 -0.0213 1.0000 0.1643
-6.500 -0.3887 0.08695 0.08075 -0.0213 1.0000 0.1728
-6.000 -0.3884 0.08221 0.07613 -0.0228 1.0000 0.1887
-5.750 -0.3820 0.07822 0.07221 -0.0197 1.0000 0.1971
-5.500 -0.3805 0.07555 0.06960 -0.0198 1.0000 0.2072
-5.250 -0.3777 0.07284 0.06693 -0.0195 1.0000 0.2204
-5.000 -0.3738 0.06995 0.06408 -0.0181 1.0000 0.2355
-4.750 -0.3696 0.06716 0.06132 -0.0164 1.0000 0.2541
-4.500 0.0083 0.03956 0.03261 -0.0296 1.0000 1.0000
-4.250 -0.0002 0.03896 0.03213 -0.0256 1.0000 0.9923
-3.250 -0.3769 0.05130 0.04604 0.0140 1.0000 0.5084
-3.000 -0.3816 0.04894 0.04378 0.0209 1.0000 0.5593
-2.750 -0.3835 0.04636 0.04132 0.0289 1.0000 0.6052
-2.500 -0.3827 0.04400 0.03903 0.0335 1.0000 0.6421
-2.250 -0.3772 0.04136 0.03644 0.0368 1.0000 0.6703
-2.000 -0.1570 0.03619 0.02835 -0.0288 1.0000 0.2578
-1.750 -0.1142 0.03348 0.02466 -0.0309 1.0000 0.1870
-1.500 -0.0857 0.03162 0.02218 -0.0307 1.0000 0.1738
-1.250 -0.0611 0.03005 0.02027 -0.0301 1.0000 0.1728
-1.000 -0.0360 0.02857 0.01843 -0.0295 1.0000 0.1675
-0.750 -0.0103 0.02743 0.01689 -0.0290 1.0000 0.1653
-0.500 0.0122 0.02662 0.01583 -0.0282 1.0000 0.1707
-0.250 0.0344 0.02597 0.01496 -0.0274 1.0000 0.1788
0.000 0.0621 0.02544 0.01415 -0.0275 1.0000 0.1845
0.250 0.0881 0.02503 0.01358 -0.0274 1.0000 0.1930
0.500 0.1114 0.02474 0.01327 -0.0271 1.0000 0.2080
0.750 0.1334 0.02451 0.01316 -0.0269 1.0000 0.2421
1.000 0.1743 0.02214 0.01264 -0.0295 1.0000 1.0000
1.250 0.1913 0.02287 0.01285 -0.0286 1.0000 1.0000
1.500 0.2120 0.02374 0.01345 -0.0291 0.9978 1.0000
1.750 0.2754 0.02516 0.01456 -0.0374 0.9753 1.0000
2.000 0.3346 0.02629 0.01552 -0.0445 0.9535 1.0000
2.250 0.3903 0.02713 0.01627 -0.0506 0.9306 1.0000
2.500 0.4399 0.02774 0.01686 -0.0551 0.9072 1.0000
2.750 0.4966 0.02813 0.01730 -0.0604 0.8850 1.0000
3.000 0.5444 0.02833 0.01756 -0.0638 0.8607 1.0000
3.250 0.5920 0.02832 0.01767 -0.0667 0.8363 1.0000
3.500 0.6493 0.02786 0.01741 -0.0706 0.8134 1.0000
3.750 0.6996 0.02723 0.01695 -0.0727 0.7893 1.0000
4.000 0.7402 0.02674 0.01662 -0.0731 0.7630 1.0000
4.250 0.7797 0.02618 0.01627 -0.0730 0.7358 1.0000
4.500 0.8162 0.02575 0.01596 -0.0723 0.7077 1.0000
4.750 0.8496 0.02549 0.01580 -0.0713 0.6788 1.0000
5.000 0.8796 0.02551 0.01594 -0.0699 0.6500 1.0000
5.250 0.9069 0.02575 0.01623 -0.0684 0.6215 1.0000
5.500 0.9320 0.02618 0.01672 -0.0668 0.5938 1.0000
5.750 0.9555 0.02677 0.01739 -0.0651 0.5670 1.0000
6.000 0.9782 0.02750 0.01824 -0.0634 0.5420 1.0000
6.250 1.0029 0.02825 0.01914 -0.0620 0.5193 1.0000
6.500 1.0240 0.02926 0.02035 -0.0604 0.4968 1.0000
6.750 1.0450 0.03013 0.02141 -0.0586 0.4730 1.0000
7.000 1.0655 0.03033 0.02170 -0.0560 0.4417 1.0000
7.250 1.0787 0.02914 0.02026 -0.0514 0.3914 1.0000
7.500 1.0832 0.02855 0.01952 -0.0463 0.3385 1.0000
7.750 1.0798 0.02902 0.01996 -0.0408 0.2746 1.0000
8.250 1.0682 0.03392 0.02346 -0.0306 0.1286 1.0000
8.500 1.0867 0.03671 0.02607 -0.0287 0.1087 1.0000
8.750 1.1096 0.03945 0.02882 -0.0275 0.0957 1.0000
9.000 1.1328 0.04243 0.03201 -0.0265 0.0870 1.0000
9.250 1.1580 0.04584 0.03559 -0.0258 0.0825 1.0000
9.500 1.1799 0.05019 0.04023 -0.0250 0.0805 1.0000
9.750 1.1892 0.05419 0.04479 -0.0228 0.0799 1.0000
10.000 1.1925 0.05825 0.04935 -0.0204 0.0796 1.0000
10.250 1.1898 0.06229 0.05386 -0.0178 0.0794 1.0000
10.500 1.1809 0.06631 0.05829 -0.0151 0.0792 1.0000
10.750 1.1692 0.07044 0.06273 -0.0126 0.0793 1.0000
11.000 1.1532 0.07436 0.06690 -0.0101 0.0796 1.0000
11.250 1.1382 0.07867 0.07137 -0.0084 0.0801 1.0000
11.500 1.1205 0.08321 0.07607 -0.0075 0.0805 1.0000
11.750 1.0369 0.09229 0.08553 -0.0132 0.0872 1.0000
12.000 1.0054 0.10115 0.09443 -0.0189 0.0892 1.0000
12.250 0.9849 0.10988 0.10314 -0.0240 0.0911 1.0000
12.500 0.9780 0.11686 0.11011 -0.0266 0.0926 1.0000
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Polar data table (+)
Polar graphs
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