GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 50,000 Max Cl/Cd: 39.02 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe492-il-50000-n5.txt Download as CSV file: xf-goe492-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 492 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4111 0.10993 0.10302 -0.0308 1.0000 0.0889
-8.500 -0.4206 0.10879 0.10202 -0.0327 1.0000 0.0898
-8.250 -0.4274 0.10698 0.10034 -0.0336 1.0000 0.0901
-8.000 -0.4040 0.10016 0.09347 -0.0305 1.0000 0.0942
-7.750 -0.4040 0.09748 0.09087 -0.0301 1.0000 0.0957
-7.500 -0.4069 0.09499 0.08847 -0.0297 1.0000 0.0975
-7.250 -0.4099 0.09243 0.08602 -0.0297 1.0000 0.0988
-6.750 -0.4082 0.08271 0.07640 -0.0394 1.0000 0.0492
-6.500 -0.4051 0.07945 0.07318 -0.0368 1.0000 0.0469
-6.250 -0.4018 0.07587 0.06965 -0.0378 1.0000 0.0452
-6.000 -0.3967 0.07197 0.06577 -0.0397 1.0000 0.0435
-5.500 -0.3685 0.05999 0.05345 -0.0509 1.0000 0.0383
-5.250 -0.3557 0.05571 0.04905 -0.0524 1.0000 0.0381
-5.000 -0.3379 0.05091 0.04395 -0.0551 1.0000 0.0381
-4.750 -0.3252 0.04829 0.04136 -0.0550 1.0000 0.0413
-4.500 -0.3035 0.04422 0.03695 -0.0572 1.0000 0.0436
-4.250 -0.2777 0.03968 0.03182 -0.0596 1.0000 0.0446
-4.000 -0.2502 0.03549 0.02696 -0.0614 1.0000 0.0458
-3.750 -0.2205 0.03196 0.02248 -0.0626 1.0000 0.0494
-3.500 -0.1967 0.02963 0.01993 -0.0629 1.0000 0.0567
-3.250 -0.1679 0.02713 0.01662 -0.0629 1.0000 0.0624
-3.000 -0.1429 0.02554 0.01473 -0.0628 1.0000 0.0771
-2.750 -0.1172 0.02402 0.01291 -0.0624 1.0000 0.0885
-2.500 -0.0930 0.02299 0.01163 -0.0619 1.0000 0.1055
-2.250 -0.0668 0.02212 0.01050 -0.0616 1.0000 0.1158
-2.000 -0.0412 0.02144 0.00966 -0.0613 1.0000 0.1300
-1.750 -0.0159 0.02084 0.00925 -0.0614 1.0000 0.1658
-1.500 0.0091 0.02045 0.00906 -0.0613 1.0000 0.2629
-1.250 0.0374 0.02005 0.00879 -0.0620 0.9978 0.3597
-1.000 0.0667 0.01879 0.00886 -0.0625 0.9927 0.6301
-0.750 0.1045 0.01836 0.00852 -0.0646 0.9829 1.0000
-0.500 0.1422 0.01873 0.00849 -0.0671 0.9750 1.0000
-0.250 0.1804 0.01910 0.00854 -0.0696 0.9673 1.0000
0.000 0.2152 0.01941 0.00861 -0.0715 0.9578 1.0000
0.250 0.2501 0.01973 0.00871 -0.0734 0.9486 1.0000
0.500 0.2892 0.02007 0.00890 -0.0760 0.9408 1.0000
0.750 0.3218 0.02036 0.00908 -0.0774 0.9302 1.0000
1.000 0.3552 0.02064 0.00931 -0.0789 0.9201 1.0000
1.250 0.3910 0.02092 0.00955 -0.0807 0.9107 1.0000
1.500 0.4268 0.02117 0.00982 -0.0825 0.9013 1.0000
1.750 0.4582 0.02144 0.01015 -0.0835 0.8901 1.0000
2.000 0.4909 0.02169 0.01047 -0.0846 0.8795 1.0000
2.250 0.5271 0.02190 0.01080 -0.0863 0.8704 1.0000
2.500 0.5603 0.02212 0.01121 -0.0874 0.8602 1.0000
3.000 0.6190 0.02266 0.01213 -0.0881 0.8370 1.0000
3.250 0.6492 0.02292 0.01270 -0.0885 0.8259 1.0000
3.500 0.6816 0.02312 0.01321 -0.0892 0.8156 1.0000
3.750 0.7127 0.02335 0.01379 -0.0896 0.8047 1.0000
4.000 0.7410 0.02360 0.01444 -0.0894 0.7915 1.0000
4.250 0.7762 0.02251 0.01391 -0.0876 0.7583 1.0000
4.500 0.7941 0.02035 0.01013 -0.0760 0.4103 1.0000
4.750 0.7879 0.02471 0.01206 -0.0717 0.0795 1.0000
5.000 0.8033 0.02666 0.01388 -0.0697 0.0589 1.0000
5.250 0.8194 0.02832 0.01570 -0.0678 0.0479 1.0000
5.500 0.8353 0.03016 0.01775 -0.0657 0.0438 1.0000
5.750 0.8565 0.03189 0.01981 -0.0641 0.0397 1.0000
6.000 0.8834 0.03411 0.02209 -0.0634 0.0348 1.0000
6.250 0.9191 0.03656 0.02485 -0.0632 0.0327 1.0000
6.500 0.9525 0.03953 0.02816 -0.0629 0.0317 1.0000
6.750 0.9796 0.04264 0.03169 -0.0620 0.0306 1.0000
7.000 1.0010 0.04571 0.03513 -0.0608 0.0289 1.0000
7.250 1.0189 0.04935 0.03897 -0.0599 0.0273 1.0000
7.500 1.0333 0.05335 0.04333 -0.0583 0.0268 1.0000
8.000 1.0548 0.06041 0.05155 -0.0539 0.0274 1.0000
8.250 1.0576 0.06411 0.05587 -0.0509 0.0282 1.0000
8.500 1.0570 0.06817 0.06040 -0.0483 0.0290 1.0000
8.750 1.0519 0.07231 0.06493 -0.0460 0.0297 1.0000
9.000 1.0438 0.07638 0.06930 -0.0439 0.0304 1.0000
9.250 1.0317 0.08030 0.07345 -0.0419 0.0309 1.0000
9.500 1.0162 0.08414 0.07746 -0.0402 0.0313 1.0000
9.750 0.9998 0.08828 0.08175 -0.0396 0.0317 1.0000
10.000 0.9830 0.09294 0.08652 -0.0403 0.0320 1.0000
10.250 0.9667 0.09818 0.09185 -0.0423 0.0323 1.0000
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Polar data table (+)
Polar graphs
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