GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 50,000 Max Cl/Cd: 30.12 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe553-il-50000-n5.txt Download as CSV file: xf-goe553-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2580 0.10894 0.10219 -0.0376 1.0000 0.1509
-9.000 -0.2828 0.10820 0.10164 -0.0391 1.0000 0.1529
-8.500 -0.3077 0.09594 0.08954 -0.0430 1.0000 0.0915
-8.250 -0.3003 0.09390 0.08758 -0.0400 1.0000 0.0899
-8.000 -0.3122 0.09252 0.08637 -0.0370 1.0000 0.0884
-7.750 -0.3184 0.08303 0.07688 -0.0520 0.9777 0.0803
-7.500 -0.2945 0.07836 0.07214 -0.0574 0.9635 0.0789
-7.250 -0.2753 0.07234 0.06604 -0.0657 0.9477 0.0779
-7.000 -0.2590 0.06599 0.05951 -0.0744 0.9317 0.0775
-6.750 -0.2416 0.06005 0.05330 -0.0820 0.9167 0.0774
-6.500 -0.2206 0.05477 0.04766 -0.0882 0.9033 0.0773
-6.250 -0.1937 0.04995 0.04241 -0.0937 0.8929 0.0767
-6.000 -0.1714 0.04623 0.03826 -0.0966 0.8790 0.0764
-5.750 -0.1462 0.04298 0.03454 -0.0989 0.8667 0.0765
-5.500 -0.1138 0.03997 0.03099 -0.1017 0.8579 0.0778
-5.250 -0.0887 0.03779 0.02829 -0.1026 0.8450 0.0793
-5.000 -0.0598 0.03583 0.02594 -0.1035 0.8345 0.0806
-4.750 -0.0291 0.03414 0.02401 -0.1043 0.8249 0.0817
-4.500 -0.0024 0.03282 0.02247 -0.1043 0.8136 0.0829
-4.250 0.0303 0.03145 0.02085 -0.1050 0.8055 0.0846
-4.000 0.0553 0.03056 0.01977 -0.1045 0.7939 0.0874
-3.750 0.0856 0.02960 0.01852 -0.1045 0.7850 0.0910
-3.500 0.1117 0.02877 0.01763 -0.1039 0.7748 0.0939
-3.250 0.1387 0.02804 0.01682 -0.1034 0.7655 0.0971
-3.000 0.1663 0.02738 0.01603 -0.1029 0.7562 0.1013
-2.750 0.1926 0.02685 0.01538 -0.1024 0.7466 0.1074
-2.500 0.2205 0.02626 0.01472 -0.1022 0.7378 0.1167
-2.250 0.2457 0.02578 0.01422 -0.1018 0.7281 0.1278
-2.000 0.2750 0.02507 0.01352 -0.1019 0.7198 0.1531
-1.750 0.3000 0.02401 0.01314 -0.1023 0.7100 0.2577
-1.500 0.3220 0.02339 0.01347 -0.1005 0.7021 0.5236
-1.250 0.3391 0.02357 0.01385 -0.0976 0.6925 0.6266
-1.000 0.3551 0.02353 0.01400 -0.0935 0.6848 0.7137
-0.750 0.3673 0.02349 0.01412 -0.0892 0.6757 0.7784
-0.500 0.3864 0.02326 0.01392 -0.0861 0.6678 0.8324
-0.250 0.4149 0.02316 0.01379 -0.0856 0.6590 0.8806
0.000 0.4619 0.02307 0.01353 -0.0890 0.6500 0.9352
0.250 0.4977 0.02329 0.01353 -0.0913 0.6407 1.0000
0.500 0.5263 0.02357 0.01356 -0.0920 0.6323 1.0000
0.750 0.5537 0.02394 0.01370 -0.0925 0.6238 1.0000
1.000 0.5808 0.02430 0.01388 -0.0927 0.6151 1.0000
1.250 0.6093 0.02464 0.01401 -0.0930 0.6076 1.0000
1.500 0.6334 0.02514 0.01439 -0.0928 0.5984 1.0000
1.750 0.6647 0.02534 0.01436 -0.0932 0.5923 1.0000
2.000 0.6845 0.02605 0.01505 -0.0925 0.5822 1.0000
2.250 0.7138 0.02632 0.01515 -0.0926 0.5758 1.0000
2.500 0.7344 0.02703 0.01583 -0.0920 0.5668 1.0000
2.750 0.7613 0.02741 0.01609 -0.0918 0.5598 1.0000
3.000 0.7842 0.02802 0.01665 -0.0913 0.5522 1.0000
3.250 0.8073 0.02860 0.01719 -0.0908 0.5446 1.0000
3.500 0.8374 0.02881 0.01727 -0.0909 0.5394 1.0000
3.750 0.8523 0.02986 0.01840 -0.0896 0.5300 1.0000
4.000 0.8802 0.03018 0.01863 -0.0895 0.5244 1.0000
4.250 0.8975 0.03114 0.01964 -0.0885 0.5166 1.0000
4.500 0.9205 0.03174 0.02022 -0.0879 0.5100 1.0000
4.750 0.9487 0.03203 0.02045 -0.0878 0.5050 1.0000
5.000 0.9599 0.03336 0.02190 -0.0863 0.4963 1.0000
5.250 0.9877 0.03366 0.02215 -0.0860 0.4912 1.0000
5.500 1.0005 0.03486 0.02343 -0.0846 0.4831 1.0000
5.750 1.0243 0.03525 0.02384 -0.0839 0.4763 1.0000
6.000 1.0431 0.03592 0.02452 -0.0828 0.4686 1.0000
6.250 1.0636 0.03636 0.02499 -0.0818 0.4603 1.0000
6.500 1.0826 0.03689 0.02555 -0.0806 0.4521 1.0000
6.750 1.1025 0.03732 0.02601 -0.0794 0.4438 1.0000
7.000 1.1209 0.03796 0.02668 -0.0783 0.4364 1.0000
7.250 1.1331 0.03904 0.02784 -0.0767 0.4287 1.0000
7.500 1.1679 0.03877 0.02756 -0.0769 0.4240 1.0000
7.750 1.1562 0.04140 0.03038 -0.0736 0.4148 1.0000
8.000 1.1854 0.04142 0.03041 -0.0733 0.4093 1.0000
8.250 1.1767 0.04375 0.03286 -0.0702 0.4012 1.0000
8.500 1.1913 0.04463 0.03382 -0.0688 0.3946 1.0000
8.750 1.2116 0.04518 0.03442 -0.0678 0.3886 1.0000
9.000 1.1874 0.04886 0.03824 -0.0646 0.3793 1.0000
9.250 1.2310 0.04771 0.03711 -0.0648 0.3751 1.0000
9.500 1.1721 0.05493 0.04449 -0.0618 0.3631 1.0000
9.750 1.2093 0.05393 0.04356 -0.0611 0.3593 1.0000
10.000 1.1507 0.06286 0.05260 -0.0608 0.3455 1.0000
10.250 1.1861 0.06167 0.05149 -0.0596 0.3425 1.0000
10.750 1.1665 0.07013 0.06012 -0.0596 0.3254 1.0000
11.250 1.1325 0.08164 0.07176 -0.0613 0.3069 1.0000
11.750 1.1058 0.09346 0.08372 -0.0638 0.2913 1.0000
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Polar data table (+)
Polar graphs
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