GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 50,000 Max Cl/Cd: 22.23 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe648-il-50000.txt Download as CSV file: xf-goe648-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 648 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3018 0.11084 0.10426 -0.0192 1.0000 0.3166
-8.500 -0.2698 0.10589 0.09928 -0.0176 1.0000 0.3263
-8.250 -0.3169 0.10763 0.10124 -0.0145 1.0000 0.3343
-8.000 -0.2794 0.10224 0.09581 -0.0131 1.0000 0.3456
-7.750 -0.3311 0.10407 0.09787 -0.0092 1.0000 0.3531
-7.500 -0.2936 0.09894 0.09270 -0.0079 1.0000 0.3656
-7.250 -0.3255 0.09866 0.09260 -0.0044 1.0000 0.3739
-7.000 -0.3102 0.09567 0.08963 -0.0024 1.0000 0.3838
-6.750 -0.3404 0.09517 0.08929 0.0014 1.0000 0.3931
-6.500 -0.3350 0.09301 0.08717 0.0039 1.0000 0.4051
-6.250 -0.3433 0.09116 0.08543 0.0069 1.0000 0.4153
-6.000 -0.5419 0.06429 0.05780 -0.0242 1.0000 0.1887
-5.750 -0.5369 0.06069 0.05410 -0.0237 1.0000 0.1874
-5.500 -0.5311 0.05687 0.05008 -0.0236 1.0000 0.1855
-5.250 -0.5234 0.05295 0.04583 -0.0239 1.0000 0.1840
-5.000 -0.5135 0.04950 0.04196 -0.0240 1.0000 0.1851
-4.750 -0.5012 0.04642 0.03836 -0.0239 1.0000 0.1870
-4.500 -0.4868 0.04384 0.03516 -0.0236 1.0000 0.1893
-4.250 -0.4723 0.04248 0.03397 -0.0224 1.0000 0.1943
-4.000 -0.4568 0.04111 0.03237 -0.0216 1.0000 0.2002
-3.750 -0.4398 0.03955 0.03024 -0.0210 1.0000 0.2062
-3.500 -0.4244 0.03859 0.02941 -0.0200 1.0000 0.2135
-3.250 -0.4072 0.03768 0.02817 -0.0192 1.0000 0.2226
-3.000 -0.3660 0.03731 0.02775 -0.0226 0.9898 0.2371
-2.750 -0.3076 0.03717 0.02731 -0.0285 0.9701 0.2601
-2.500 -0.2556 0.03683 0.02712 -0.0330 0.9505 0.2860
-2.250 -0.2088 0.03634 0.02669 -0.0364 0.9318 0.3205
-2.000 -0.1664 0.03584 0.02638 -0.0388 0.9152 0.3720
-1.750 -0.1263 0.03528 0.02644 -0.0404 0.8995 0.4627
-1.500 -0.0934 0.03485 0.02676 -0.0397 0.8846 0.5942
-1.250 -0.0619 0.03453 0.02712 -0.0374 0.8703 0.7369
-1.000 0.1614 0.03506 0.02766 -0.0665 0.8530 1.0000
-0.750 0.1663 0.03451 0.02687 -0.0652 0.8348 1.0000
-0.500 0.1960 0.03430 0.02636 -0.0663 0.8167 1.0000
-0.250 0.2334 0.03412 0.02591 -0.0679 0.7985 1.0000
0.000 0.2737 0.03387 0.02543 -0.0694 0.7804 1.0000
0.250 0.3168 0.03349 0.02483 -0.0711 0.7625 1.0000
0.500 0.3624 0.03298 0.02413 -0.0729 0.7448 1.0000
0.750 0.4066 0.03244 0.02341 -0.0743 0.7271 1.0000
1.000 0.4470 0.03195 0.02276 -0.0751 0.7093 1.0000
1.250 0.4853 0.03153 0.02218 -0.0755 0.6917 1.0000
1.500 0.5210 0.03124 0.02173 -0.0756 0.6743 1.0000
1.750 0.5520 0.03119 0.02153 -0.0753 0.6573 1.0000
2.000 0.5788 0.03138 0.02159 -0.0744 0.6409 1.0000
2.250 0.6036 0.03173 0.02182 -0.0734 0.6254 1.0000
2.500 0.6310 0.03205 0.02201 -0.0728 0.6115 1.0000
2.750 0.6807 0.03151 0.02126 -0.0749 0.6003 1.0000
3.000 0.6847 0.03289 0.02261 -0.0716 0.5860 1.0000
3.250 0.6962 0.03407 0.02375 -0.0694 0.5737 1.0000
3.500 0.7462 0.03356 0.02304 -0.0714 0.5640 1.0000
3.750 0.7354 0.03582 0.02536 -0.0668 0.5519 1.0000
4.000 0.7619 0.03645 0.02591 -0.0664 0.5424 1.0000
4.250 0.7711 0.03788 0.02732 -0.0641 0.5321 1.0000
4.500 0.7802 0.03945 0.02888 -0.0619 0.5231 1.0000
4.750 0.7901 0.04098 0.03040 -0.0599 0.5139 1.0000
5.000 0.7962 0.04285 0.03227 -0.0577 0.5056 1.0000
5.250 0.7745 0.04631 0.03578 -0.0533 0.4967 1.0000
5.500 0.8178 0.04615 0.03555 -0.0542 0.4896 1.0000
5.750 0.6369 0.06277 0.05229 -0.0450 0.4802 1.0000
6.000 0.8397 0.04956 0.03896 -0.0510 0.4742 1.0000
6.250 0.6168 0.07130 0.06079 -0.0441 0.4687 1.0000
6.500 0.5969 0.07650 0.06600 -0.0441 0.4650 1.0000
6.750 0.4697 0.09360 0.08332 -0.0505 0.5528 1.0000
7.000 0.4973 0.09502 0.08470 -0.0500 0.5319 1.0000
7.250 0.5248 0.09641 0.08605 -0.0494 0.5123 1.0000
7.500 0.5676 0.09469 0.08424 -0.0466 0.4705 1.0000
7.750 0.5851 0.09841 0.08797 -0.0476 0.4734 1.0000
8.000 0.4884 0.10991 0.09965 -0.0530 0.5667 1.0000
8.250 0.4973 0.11302 0.10274 -0.0532 0.5615 1.0000
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Polar data table (+)
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