GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 50,000 Max Cl/Cd: 39.44 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe393-il-50000-n5.txt Download as CSV file: xf-goe393-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4466 0.11107 0.10438 0.0084 1.0000 0.0902
-8.000 -0.4451 0.10917 0.10255 0.0048 1.0000 0.0912
-7.750 -0.4401 0.10701 0.10046 -0.0006 1.0000 0.0918
-7.500 -0.4307 0.10310 0.09661 -0.0038 1.0000 0.0925
-7.250 -0.4177 0.09724 0.09076 0.0014 1.0000 0.0964
-7.000 -0.4073 0.09392 0.08747 -0.0007 1.0000 0.1000
-6.750 -0.3960 0.09090 0.08447 -0.0051 1.0000 0.1034
-6.500 -0.3802 0.08840 0.08195 -0.0131 1.0000 0.1054
-6.250 -0.3607 0.08550 0.07896 -0.0204 1.0000 0.1060
-6.000 -0.3521 0.08010 0.07367 -0.0168 1.0000 0.1077
-5.750 -0.3390 0.07652 0.07012 -0.0162 1.0000 0.1128
-5.500 -0.3099 0.07443 0.06782 -0.0266 1.0000 0.1199
-5.250 -0.2962 0.06990 0.06338 -0.0264 1.0000 0.1213
-5.000 -0.2804 0.06620 0.05970 -0.0267 1.0000 0.1234
-4.750 -0.2604 0.06288 0.05636 -0.0287 1.0000 0.1257
-4.500 -0.2378 0.05963 0.05302 -0.0314 1.0000 0.1272
-4.000 -0.1745 0.05099 0.04382 -0.0408 1.0000 0.0905
-3.750 -0.1544 0.04793 0.04075 -0.0415 1.0000 0.0874
-3.500 -0.1318 0.04498 0.03767 -0.0430 1.0000 0.0845
-3.250 -0.1022 0.04183 0.03428 -0.0459 0.9932 0.0820
-3.000 -0.0524 0.03800 0.02995 -0.0521 0.9671 0.0804
-2.750 -0.0100 0.03575 0.02746 -0.0562 0.9391 0.0842
-2.500 0.0323 0.03336 0.02466 -0.0598 0.9113 0.0877
-2.250 0.0723 0.03100 0.02182 -0.0624 0.8851 0.0881
-2.000 0.1092 0.02896 0.01927 -0.0640 0.8606 0.0892
-1.750 0.1429 0.02721 0.01696 -0.0647 0.8375 0.0910
-1.500 0.1731 0.02586 0.01523 -0.0646 0.8165 0.0936
-1.250 0.2011 0.02495 0.01407 -0.0642 0.7965 0.0979
-1.000 0.2292 0.02418 0.01290 -0.0637 0.7779 0.1075
-0.750 0.2558 0.02356 0.01203 -0.0630 0.7606 0.1180
-0.500 0.2836 0.02285 0.01106 -0.0623 0.7447 0.1283
-0.250 0.3115 0.02248 0.01042 -0.0618 0.7296 0.1480
0.000 0.3385 0.02210 0.01000 -0.0614 0.7151 0.1679
0.250 0.3656 0.02177 0.00954 -0.0608 0.7016 0.1830
0.500 0.3924 0.02153 0.00915 -0.0601 0.6889 0.1941
0.750 0.4187 0.02133 0.00889 -0.0594 0.6769 0.2032
1.000 0.4448 0.02122 0.00877 -0.0589 0.6645 0.2173
1.250 0.4711 0.02115 0.00872 -0.0584 0.6523 0.2313
1.500 0.4976 0.02110 0.00871 -0.0580 0.6409 0.2473
1.750 0.5239 0.02100 0.00875 -0.0575 0.6303 0.2783
2.000 0.5536 0.01960 0.00877 -0.0576 0.6192 1.0000
2.250 0.5802 0.01998 0.00894 -0.0572 0.6081 1.0000
2.500 0.6068 0.02036 0.00916 -0.0567 0.5980 1.0000
2.750 0.6332 0.02073 0.00942 -0.0562 0.5883 1.0000
3.000 0.6595 0.02118 0.00983 -0.0559 0.5777 1.0000
3.250 0.6857 0.02160 0.01020 -0.0554 0.5686 1.0000
3.500 0.7118 0.02205 0.01065 -0.0550 0.5592 1.0000
3.750 0.7378 0.02257 0.01121 -0.0548 0.5497 1.0000
4.000 0.7639 0.02300 0.01163 -0.0542 0.5420 1.0000
4.250 0.7895 0.02361 0.01237 -0.0540 0.5322 1.0000
4.500 0.8153 0.02410 0.01288 -0.0535 0.5248 1.0000
4.750 0.8407 0.02475 0.01368 -0.0533 0.5156 1.0000
5.000 0.8661 0.02534 0.01440 -0.0529 0.5077 1.0000
5.250 0.8912 0.02584 0.01502 -0.0523 0.4981 1.0000
5.500 0.9154 0.02620 0.01549 -0.0515 0.4846 1.0000
5.750 0.9393 0.02617 0.01549 -0.0501 0.4678 1.0000
6.000 0.9628 0.02615 0.01557 -0.0488 0.4491 1.0000
6.250 0.9861 0.02634 0.01592 -0.0478 0.4313 1.0000
6.500 1.0097 0.02661 0.01635 -0.0469 0.4154 1.0000
6.750 1.0332 0.02693 0.01685 -0.0459 0.3993 1.0000
7.000 1.0562 0.02720 0.01733 -0.0449 0.3813 1.0000
7.250 1.0786 0.02746 0.01773 -0.0437 0.3604 1.0000
7.500 1.1000 0.02789 0.01835 -0.0426 0.3355 1.0000
7.750 1.1203 0.02845 0.01907 -0.0414 0.3065 1.0000
8.000 1.1387 0.02922 0.01995 -0.0402 0.2700 1.0000
8.250 1.1547 0.03029 0.02094 -0.0390 0.2300 1.0000
8.500 1.1674 0.03181 0.02224 -0.0378 0.1934 1.0000
8.750 1.1773 0.03379 0.02401 -0.0366 0.1667 1.0000
9.000 1.1847 0.03605 0.02611 -0.0354 0.1467 1.0000
9.250 1.1917 0.03836 0.02848 -0.0342 0.1267 1.0000
9.500 1.1961 0.04082 0.03097 -0.0331 0.1101 1.0000
9.750 1.1985 0.04339 0.03359 -0.0319 0.0966 1.0000
10.000 1.1991 0.04602 0.03632 -0.0305 0.0865 1.0000
10.250 1.1978 0.04877 0.03904 -0.0295 0.0786 1.0000
10.500 1.2004 0.05160 0.04211 -0.0286 0.0708 1.0000
10.750 1.2016 0.05446 0.04496 -0.0280 0.0657 1.0000
11.000 1.2049 0.05751 0.04828 -0.0274 0.0604 1.0000
11.250 1.2057 0.06068 0.05161 -0.0275 0.0563 1.0000
11.500 1.2069 0.06368 0.05459 -0.0274 0.0534 1.0000
11.750 1.2094 0.06732 0.05856 -0.0269 0.0510 1.0000
12.000 1.2072 0.07147 0.06302 -0.0272 0.0490 1.0000
12.250 1.2019 0.07596 0.06775 -0.0282 0.0474 1.0000
12.500 1.1949 0.08068 0.07267 -0.0297 0.0461 1.0000
12.750 1.1869 0.08557 0.07771 -0.0314 0.0450 1.0000
13.000 1.1794 0.09043 0.08268 -0.0332 0.0439 1.0000
13.250 1.1731 0.09519 0.08748 -0.0346 0.0429 1.0000
13.500 1.1561 0.10234 0.09486 -0.0382 0.0428 1.0000
13.750 1.1379 0.11008 0.10280 -0.0424 0.0429 1.0000
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Polar data table (+)
Polar graphs
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