GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 50,000 Max Cl/Cd: 16.1 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe614-il-50000-n5.txt Download as CSV file: xf-goe614-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 614 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1330 0.11095 0.10400 -0.0795 0.9367 0.0772
-9.750 -0.1294 0.10630 0.09935 -0.0827 0.9285 0.0766
-9.500 -0.1264 0.10104 0.09409 -0.0868 0.9217 0.0760
-9.250 -0.1304 0.09597 0.08904 -0.0897 0.9121 0.0755
-9.000 -0.1381 0.08964 0.08272 -0.0940 0.9043 0.0749
-8.750 -0.2111 0.07454 0.06756 -0.1030 0.8919 0.0731
-8.500 -0.2547 0.06747 0.06038 -0.1064 0.8769 0.0725
-8.250 -0.2892 0.06116 0.05379 -0.1085 0.8626 0.0722
-8.000 -0.2960 0.05514 0.04731 -0.1119 0.8548 0.0725
-7.750 -0.3063 0.05222 0.04406 -0.1101 0.8414 0.0728
-7.500 -0.2840 0.04907 0.04059 -0.1122 0.8363 0.0738
-7.250 -0.2813 0.04795 0.03939 -0.1096 0.8235 0.0747
-7.000 -0.2525 0.04589 0.03712 -0.1113 0.8186 0.0770
-6.750 -0.2483 0.04466 0.03569 -0.1088 0.8062 0.0788
-6.500 -0.2196 0.04242 0.03305 -0.1101 0.8010 0.0817
-6.250 -0.2098 0.04178 0.03239 -0.1079 0.7896 0.0837
-6.000 -0.1811 0.04033 0.03076 -0.1085 0.7836 0.0871
-5.750 -0.1641 0.03924 0.02941 -0.1072 0.7745 0.0905
-5.500 -0.1410 0.03821 0.02833 -0.1068 0.7666 0.0948
-5.250 -0.1055 0.03669 0.02660 -0.1082 0.7624 0.1031
-5.000 -0.1001 0.03637 0.02629 -0.1050 0.7501 0.1095
-4.750 -0.0668 0.03509 0.02493 -0.1061 0.7451 0.1279
-4.500 -0.0559 0.03491 0.02485 -0.1038 0.7343 0.1424
-4.250 -0.0253 0.03449 0.02446 -0.1042 0.7281 0.1665
-4.000 -0.0004 0.03443 0.02430 -0.1038 0.7208 0.1906
-3.750 0.0179 0.03455 0.02434 -0.1024 0.7116 0.2095
-3.500 0.0554 0.03416 0.02382 -0.1037 0.7073 0.2316
-3.250 0.0624 0.03453 0.02407 -0.1007 0.6960 0.2443
-3.000 0.0947 0.03430 0.02375 -0.1012 0.6908 0.2650
-2.750 0.1153 0.03438 0.02373 -0.1001 0.6831 0.2819
-2.500 0.1342 0.03451 0.02389 -0.0987 0.6750 0.2963
-2.250 0.1721 0.03400 0.02325 -0.0999 0.6710 0.3138
-2.000 0.1784 0.03450 0.02365 -0.0969 0.6609 0.3238
-1.750 0.2078 0.03424 0.02329 -0.0969 0.6553 0.3374
-1.500 0.2482 0.03369 0.02261 -0.0984 0.6518 0.3532
-1.250 0.2477 0.03460 0.02345 -0.0946 0.6409 0.3628
-1.000 0.2804 0.03436 0.02310 -0.0951 0.6362 0.3806
-0.750 0.3205 0.03390 0.02259 -0.0966 0.6331 0.4042
-0.500 0.3125 0.03524 0.02400 -0.0919 0.6220 0.4150
-0.250 0.3452 0.03500 0.02369 -0.0923 0.6176 0.4392
0.000 0.3864 0.03446 0.02307 -0.0939 0.6147 0.4642
0.250 0.3741 0.03619 0.02489 -0.0890 0.6035 0.4738
0.500 0.4058 0.03600 0.02467 -0.0894 0.5994 0.4979
0.750 0.4458 0.03545 0.02408 -0.0907 0.5966 0.5270
1.250 0.4592 0.03741 0.02621 -0.0857 0.5813 0.5746
1.750 0.4767 0.03935 0.02846 -0.0816 0.5678 0.6469
2.000 0.5029 0.03916 0.02857 -0.0809 0.5634 0.7331
2.250 0.5662 0.03830 0.02781 -0.0864 0.5608 1.0000
2.500 0.6100 0.03789 0.02708 -0.0883 0.5586 1.0000
2.750 0.5648 0.04213 0.03140 -0.0814 0.5450 1.0000
3.000 0.6000 0.04196 0.03100 -0.0821 0.5422 1.0000
3.250 0.6408 0.04151 0.03031 -0.0832 0.5403 1.0000
3.750 0.6290 0.04621 0.03492 -0.0777 0.5234 1.0000
4.250 0.6236 0.05114 0.03977 -0.0738 0.5066 1.0000
4.500 0.6068 0.05510 0.04373 -0.0716 0.4958 1.0000
4.750 0.6238 0.05608 0.04462 -0.0709 0.4902 1.0000
5.000 0.6547 0.05581 0.04422 -0.0706 0.4874 1.0000
5.250 0.6898 0.05518 0.04344 -0.0705 0.4855 1.0000
6.250 0.6865 0.06577 0.05396 -0.0655 0.4515 1.0000
6.500 0.7177 0.06538 0.05348 -0.0651 0.4493 1.0000
7.000 0.7143 0.07118 0.05928 -0.0633 0.4326 1.0000
7.250 0.7437 0.07098 0.05900 -0.0628 0.4304 1.0000
7.750 0.7368 0.07747 0.06553 -0.0614 0.4141 1.0000
8.250 0.7293 0.08426 0.07235 -0.0603 0.3984 1.0000
8.500 0.7553 0.08446 0.07251 -0.0599 0.3961 1.0000
9.000 0.7440 0.09201 0.08012 -0.0594 0.3810 1.0000
9.250 0.7661 0.09275 0.08083 -0.0590 0.3788 1.0000
9.500 0.7362 0.09973 0.08790 -0.0595 0.3693 1.0000
9.750 0.7469 0.10187 0.09005 -0.0594 0.3655 1.0000
10.000 0.7649 0.10311 0.09128 -0.0591 0.3630 1.0000
10.250 0.7852 0.10408 0.09223 -0.0588 0.3608 1.0000
10.500 0.7540 0.11126 0.09951 -0.0598 0.3517 1.0000
10.750 0.7662 0.11324 0.10151 -0.0598 0.3485 1.0000
11.000 0.7853 0.11437 0.10264 -0.0595 0.3462 1.0000
11.250 0.7837 0.11815 0.10646 -0.0600 0.3423 1.0000
11.500 0.7727 0.12301 0.11139 -0.0609 0.3372 1.0000
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Polar data table (+)
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