GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 50,000 Max Cl/Cd: 37.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe488-il-50000-n5.txt Download as CSV file: xf-goe488-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4116 0.10899 0.10174 -0.0221 1.0000 0.1094
-8.750 -0.4200 0.10757 0.10044 -0.0241 1.0000 0.1135
-8.500 -0.4346 0.10664 0.09966 -0.0261 1.0000 0.1145
-8.250 -0.4095 0.10051 0.09346 -0.0231 1.0000 0.1216
-8.000 -0.4146 0.09845 0.09149 -0.0234 1.0000 0.1263
-7.750 -0.4319 0.09747 0.09069 -0.0254 1.0000 0.1288
-7.250 -0.4238 0.09018 0.08350 -0.0239 1.0000 0.1329
-7.000 -0.4207 0.08720 0.08057 -0.0233 1.0000 0.1360
-6.750 -0.4215 0.08452 0.07794 -0.0239 1.0000 0.1398
-6.500 -0.4314 0.08327 0.07666 -0.0299 1.0000 0.1444
-6.250 -0.4216 0.07869 0.07219 -0.0253 1.0000 0.1474
-6.000 -0.4184 0.07633 0.06983 -0.0252 1.0000 0.1570
-5.500 -0.3941 0.06302 0.05586 -0.0360 1.0000 0.0858
-5.250 -0.3849 0.06002 0.05287 -0.0341 1.0000 0.0836
-5.000 -0.3737 0.05672 0.04946 -0.0338 1.0000 0.0816
-4.750 -0.3601 0.05326 0.04582 -0.0340 1.0000 0.0798
-4.500 -0.3444 0.04975 0.04203 -0.0344 1.0000 0.0782
-4.250 -0.3273 0.04670 0.03870 -0.0346 1.0000 0.0792
-4.000 -0.3085 0.04382 0.03548 -0.0348 1.0000 0.0818
-3.750 -0.2888 0.04100 0.03230 -0.0348 1.0000 0.0819
-3.500 -0.2682 0.03835 0.02930 -0.0346 1.0000 0.0810
-3.250 -0.2465 0.03588 0.02643 -0.0343 1.0000 0.0802
-3.000 -0.2240 0.03370 0.02385 -0.0339 1.0000 0.0798
-2.750 -0.2010 0.03175 0.02148 -0.0334 1.0000 0.0796
-2.500 -0.1774 0.03006 0.01939 -0.0329 1.0000 0.0799
-2.250 -0.1535 0.02860 0.01757 -0.0323 1.0000 0.0805
-2.000 -0.1293 0.02735 0.01598 -0.0317 1.0000 0.0815
-1.750 -0.1050 0.02631 0.01461 -0.0310 1.0000 0.0829
-1.500 -0.0806 0.02549 0.01350 -0.0304 1.0000 0.0859
-1.250 -0.0589 0.02493 0.01298 -0.0297 1.0000 0.0917
-1.000 -0.0352 0.02444 0.01230 -0.0290 1.0000 0.0973
-0.750 -0.0100 0.02393 0.01158 -0.0284 1.0000 0.1009
-0.500 0.0205 0.02351 0.01114 -0.0293 0.9968 0.1060
-0.250 0.0628 0.02318 0.01072 -0.0322 0.9880 0.1163
0.000 0.1079 0.02283 0.01046 -0.0358 0.9774 0.1394
0.250 0.1531 0.02208 0.01034 -0.0396 0.9640 0.2601
0.500 0.2124 0.01999 0.01000 -0.0454 0.9512 1.0000
0.750 0.2582 0.02013 0.00985 -0.0487 0.9359 1.0000
1.000 0.2986 0.02025 0.00979 -0.0510 0.9224 1.0000
1.250 0.3355 0.02036 0.00978 -0.0527 0.9093 1.0000
1.500 0.3720 0.02042 0.00977 -0.0542 0.8956 1.0000
1.750 0.4094 0.02042 0.00974 -0.0557 0.8812 1.0000
2.000 0.4467 0.02037 0.00969 -0.0570 0.8664 1.0000
2.250 0.4836 0.02026 0.00960 -0.0581 0.8503 1.0000
2.500 0.5159 0.02015 0.00954 -0.0583 0.8313 1.0000
2.750 0.5464 0.02002 0.00948 -0.0580 0.8098 1.0000
3.000 0.5765 0.01987 0.00941 -0.0576 0.7853 1.0000
3.250 0.6048 0.01973 0.00935 -0.0568 0.7563 1.0000
3.500 0.6332 0.01959 0.00927 -0.0559 0.7210 1.0000
3.750 0.6644 0.01941 0.00912 -0.0553 0.6800 1.0000
4.000 0.6981 0.01931 0.00888 -0.0549 0.6333 1.0000
4.250 0.7276 0.01952 0.00886 -0.0541 0.5842 1.0000
4.500 0.7519 0.01998 0.00915 -0.0529 0.5387 1.0000
4.750 0.7747 0.02054 0.00955 -0.0516 0.5004 1.0000
5.000 0.7974 0.02114 0.01003 -0.0504 0.4697 1.0000
5.250 0.8203 0.02179 0.01061 -0.0493 0.4439 1.0000
5.500 0.8438 0.02247 0.01127 -0.0484 0.4220 1.0000
5.750 0.8675 0.02317 0.01202 -0.0476 0.4014 1.0000
6.000 0.8917 0.02390 0.01283 -0.0469 0.3822 1.0000
6.250 0.9158 0.02467 0.01365 -0.0461 0.3632 1.0000
6.500 0.9383 0.02544 0.01455 -0.0452 0.3430 1.0000
6.750 0.9597 0.02621 0.01551 -0.0440 0.3221 1.0000
7.000 0.9769 0.02688 0.01628 -0.0422 0.2970 1.0000
7.250 0.9891 0.02738 0.01688 -0.0398 0.2652 1.0000
7.500 1.0017 0.02790 0.01750 -0.0374 0.2317 1.0000
7.750 1.0153 0.02858 0.01821 -0.0353 0.1973 1.0000
8.000 1.0270 0.02963 0.01913 -0.0333 0.1541 1.0000
8.250 1.0374 0.03142 0.02067 -0.0313 0.0996 1.0000
8.500 1.0468 0.03366 0.02264 -0.0293 0.0675 1.0000
8.750 1.0539 0.03595 0.02488 -0.0269 0.0575 1.0000
9.000 1.0609 0.03812 0.02718 -0.0245 0.0514 1.0000
9.250 1.0647 0.04047 0.02955 -0.0219 0.0477 1.0000
9.500 1.0734 0.04240 0.03181 -0.0196 0.0436 1.0000
9.750 1.0789 0.04449 0.03407 -0.0173 0.0403 1.0000
10.000 1.0828 0.04673 0.03642 -0.0152 0.0383 1.0000
10.250 1.0887 0.04924 0.03908 -0.0132 0.0370 1.0000
10.500 1.0961 0.05189 0.04205 -0.0114 0.0359 1.0000
10.750 1.1009 0.05477 0.04525 -0.0097 0.0350 1.0000
11.000 1.1019 0.05792 0.04879 -0.0081 0.0342 1.0000
11.250 1.0991 0.06125 0.05242 -0.0069 0.0336 1.0000
11.500 1.0927 0.06491 0.05635 -0.0061 0.0330 1.0000
11.750 1.0833 0.06895 0.06065 -0.0059 0.0326 1.0000
12.000 1.0712 0.07347 0.06542 -0.0065 0.0323 1.0000
12.250 1.0560 0.07885 0.07103 -0.0082 0.0322 1.0000
12.500 1.0378 0.08516 0.07758 -0.0112 0.0324 1.0000
12.750 1.0155 0.09313 0.08578 -0.0158 0.0332 1.0000
13.000 0.9930 0.10214 0.09499 -0.0215 0.0339 1.0000
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Polar data table (+)
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