GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 50,000 Max Cl/Cd: 30.47 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe648-il-50000-n5.txt Download as CSV file: xf-goe648-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3456 0.10086 0.09353 -0.0452 1.0000 0.0852
-10.000 -0.3575 0.09680 0.08956 -0.0458 1.0000 0.0857
-9.750 -0.3736 0.09243 0.08530 -0.0465 1.0000 0.0860
-9.500 -0.3940 0.08779 0.08077 -0.0471 1.0000 0.0861
-9.250 -0.4205 0.08275 0.07584 -0.0479 1.0000 0.0858
-9.000 -0.4616 0.07694 0.07013 -0.0489 1.0000 0.0851
-8.750 -0.5071 0.07249 0.06573 -0.0475 1.0000 0.0843
-8.500 -0.5444 0.06781 0.06097 -0.0460 1.0000 0.0839
-8.250 -0.5714 0.06351 0.05652 -0.0444 1.0000 0.0840
-8.000 -0.5898 0.05949 0.05228 -0.0427 1.0000 0.0845
-7.750 -0.5919 0.05479 0.04715 -0.0437 0.9960 0.0859
-7.500 -0.5809 0.04926 0.04078 -0.0468 0.9869 0.0887
-7.250 -0.5527 0.04736 0.03883 -0.0487 0.9801 0.0913
-7.000 -0.5275 0.04515 0.03637 -0.0501 0.9722 0.0940
-6.750 -0.5031 0.04262 0.03337 -0.0515 0.9644 0.0978
-6.500 -0.4754 0.04045 0.03081 -0.0529 0.9569 0.1017
-6.250 -0.4482 0.03913 0.02941 -0.0536 0.9488 0.1053
-6.000 -0.4171 0.03754 0.02746 -0.0550 0.9416 0.1106
-5.750 -0.3907 0.03629 0.02605 -0.0553 0.9331 0.1152
-5.500 -0.3578 0.03527 0.02491 -0.0567 0.9258 0.1213
-5.250 -0.3308 0.03421 0.02362 -0.0568 0.9170 0.1277
-5.000 -0.2980 0.03342 0.02284 -0.0580 0.9096 0.1352
-4.750 -0.2700 0.03260 0.02187 -0.0582 0.9007 0.1430
-4.500 -0.2375 0.03192 0.02116 -0.0592 0.8930 0.1529
-4.250 -0.2090 0.03127 0.02052 -0.0594 0.8841 0.1627
-4.000 -0.1766 0.03063 0.01981 -0.0601 0.8759 0.1753
-3.750 -0.1464 0.03009 0.01923 -0.0605 0.8674 0.1899
-3.500 -0.1149 0.02951 0.01872 -0.0612 0.8585 0.2077
-3.250 -0.0830 0.02889 0.01823 -0.0619 0.8493 0.2308
-3.000 -0.0478 0.02813 0.01761 -0.0629 0.8393 0.2658
-2.750 -0.0185 0.02741 0.01706 -0.0628 0.8263 0.3090
-2.500 0.0262 0.02634 0.01628 -0.0649 0.8173 0.3776
-2.250 0.0511 0.02577 0.01598 -0.0636 0.8025 0.4404
-2.000 0.0758 0.02533 0.01578 -0.0621 0.7888 0.5111
-1.750 0.1108 0.02472 0.01543 -0.0618 0.7805 0.5970
-1.500 0.1286 0.02454 0.01547 -0.0588 0.7666 0.6619
-1.250 0.1523 0.02431 0.01541 -0.0566 0.7544 0.7272
-1.000 0.1891 0.02388 0.01501 -0.0564 0.7450 0.7921
-0.750 0.2279 0.02370 0.01487 -0.0571 0.7308 0.8515
-0.500 0.2947 0.02346 0.01454 -0.0631 0.7171 0.9088
-0.250 0.3664 0.02319 0.01406 -0.0705 0.7022 0.9536
0.000 0.4307 0.02293 0.01356 -0.0770 0.6854 0.9934
0.250 0.4545 0.02278 0.01320 -0.0764 0.6693 1.0000
0.500 0.4742 0.02268 0.01287 -0.0749 0.6532 1.0000
0.750 0.4950 0.02265 0.01262 -0.0734 0.6364 1.0000
1.000 0.5150 0.02270 0.01247 -0.0718 0.6188 1.0000
1.250 0.5358 0.02280 0.01236 -0.0703 0.6009 1.0000
1.500 0.5567 0.02296 0.01232 -0.0688 0.5831 1.0000
1.750 0.5776 0.02317 0.01235 -0.0674 0.5654 1.0000
2.000 0.5985 0.02343 0.01242 -0.0660 0.5479 1.0000
2.250 0.6194 0.02373 0.01255 -0.0646 0.5312 1.0000
2.500 0.6405 0.02407 0.01273 -0.0633 0.5154 1.0000
2.750 0.6626 0.02444 0.01293 -0.0622 0.5010 1.0000
3.000 0.6863 0.02479 0.01310 -0.0613 0.4880 1.0000
3.250 0.7076 0.02523 0.01342 -0.0602 0.4751 1.0000
3.500 0.7285 0.02570 0.01379 -0.0590 0.4630 1.0000
3.750 0.7532 0.02611 0.01403 -0.0584 0.4529 1.0000
4.000 0.7737 0.02665 0.01453 -0.0572 0.4423 1.0000
4.250 0.7971 0.02714 0.01490 -0.0565 0.4332 1.0000
4.500 0.8185 0.02768 0.01538 -0.0555 0.4239 1.0000
4.750 0.8417 0.02822 0.01584 -0.0548 0.4158 1.0000
5.000 0.8625 0.02883 0.01642 -0.0537 0.4075 1.0000
5.250 0.8874 0.02935 0.01682 -0.0533 0.4003 1.0000
5.500 0.9052 0.03008 0.01759 -0.0519 0.3923 1.0000
5.750 0.9313 0.03060 0.01800 -0.0516 0.3858 1.0000
6.000 0.9486 0.03141 0.01886 -0.0502 0.3787 1.0000
6.250 0.9692 0.03210 0.01955 -0.0492 0.3719 1.0000
6.500 0.9960 0.03269 0.02002 -0.0491 0.3661 1.0000
6.750 1.0084 0.03370 0.02117 -0.0472 0.3595 1.0000
7.000 1.0293 0.03444 0.02192 -0.0463 0.3535 1.0000
7.250 1.0553 0.03512 0.02250 -0.0461 0.3480 1.0000
7.500 1.0635 0.03631 0.02388 -0.0437 0.3419 1.0000
7.750 1.0815 0.03722 0.02483 -0.0426 0.3363 1.0000
8.000 1.1115 0.03782 0.02533 -0.0430 0.3314 1.0000
8.250 1.1132 0.03930 0.02701 -0.0399 0.3260 1.0000
8.500 1.1224 0.04055 0.02838 -0.0378 0.3206 1.0000
8.750 1.1443 0.04140 0.02923 -0.0372 0.3158 1.0000
9.000 1.1635 0.04244 0.03029 -0.0364 0.3114 1.0000
9.250 1.1503 0.04441 0.03250 -0.0318 0.3065 1.0000
9.500 1.1518 0.04602 0.03423 -0.0292 0.3018 1.0000
9.750 1.1728 0.04693 0.03515 -0.0286 0.2975 1.0000
10.000 1.1904 0.04810 0.03634 -0.0277 0.2937 1.0000
10.250 1.1490 0.05193 0.04048 -0.0221 0.2894 1.0000
10.500 1.1172 0.05605 0.04480 -0.0187 0.2848 1.0000
10.750 1.1204 0.05810 0.04693 -0.0175 0.2808 1.0000
11.000 1.1700 0.05705 0.04580 -0.0181 0.2774 1.0000
11.250 0.9302 0.08542 0.07465 -0.0206 0.2631 1.0000
11.500 0.9520 0.08574 0.07500 -0.0197 0.2609 1.0000
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Polar data table (+)
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