GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 50,000 Max Cl/Cd: 29.45 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe533-il-50000-n5.txt Download as CSV file: xf-goe533-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 533 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2585 0.11203 0.10520 -0.0386 1.0000 0.1485
-9.250 -0.2801 0.11118 0.10454 -0.0401 1.0000 0.1501
-9.000 -0.2933 0.10939 0.10294 -0.0403 1.0000 0.1504
-8.500 -0.3049 0.09641 0.09002 -0.0429 1.0000 0.0884
-8.250 -0.3057 0.09466 0.08838 -0.0401 1.0000 0.0873
-8.000 -0.3114 0.09254 0.08638 -0.0395 0.9965 0.0866
-7.750 -0.2929 0.08762 0.08146 -0.0458 0.9814 0.0853
-7.250 -0.2786 0.06940 0.06292 -0.0736 0.9403 0.0770
-7.000 -0.2573 0.06483 0.05822 -0.0786 0.9269 0.0762
-6.750 -0.2369 0.05987 0.05305 -0.0844 0.9136 0.0753
-6.500 -0.2142 0.05478 0.04763 -0.0903 0.9019 0.0746
-6.250 -0.1928 0.05036 0.04280 -0.0946 0.8887 0.0749
-6.000 -0.1711 0.04661 0.03855 -0.0977 0.8754 0.0757
-5.750 -0.1441 0.04320 0.03456 -0.1005 0.8648 0.0764
-5.500 -0.1158 0.04045 0.03134 -0.1024 0.8542 0.0767
-5.250 -0.0890 0.03817 0.02861 -0.1034 0.8430 0.0770
-5.000 -0.0570 0.03603 0.02613 -0.1048 0.8344 0.0777
-4.750 -0.0314 0.03456 0.02447 -0.1049 0.8230 0.0788
-4.500 0.0016 0.03315 0.02286 -0.1059 0.8152 0.0814
-4.250 0.0264 0.03210 0.02158 -0.1056 0.8036 0.0839
-4.000 0.0570 0.03089 0.02006 -0.1058 0.7950 0.0863
-3.750 0.0843 0.02992 0.01883 -0.1054 0.7849 0.0880
-3.500 0.1121 0.02900 0.01781 -0.1050 0.7760 0.0901
-3.250 0.1391 0.02827 0.01702 -0.1046 0.7666 0.0935
-3.000 0.1657 0.02771 0.01632 -0.1040 0.7574 0.0990
-2.750 0.1935 0.02706 0.01558 -0.1037 0.7486 0.1049
-2.500 0.2190 0.02656 0.01502 -0.1032 0.7393 0.1116
-2.250 0.2472 0.02597 0.01435 -0.1031 0.7308 0.1220
-2.000 0.2729 0.02545 0.01387 -0.1029 0.7215 0.1420
-1.750 0.3017 0.02436 0.01324 -0.1035 0.7133 0.2208
-1.500 0.3214 0.02357 0.01358 -0.1020 0.7043 0.4980
-1.250 0.3404 0.02357 0.01390 -0.0990 0.6961 0.6201
-1.000 0.3543 0.02369 0.01420 -0.0950 0.6876 0.7157
-0.750 0.3667 0.02353 0.01421 -0.0903 0.6794 0.7873
-0.500 0.3856 0.02329 0.01401 -0.0872 0.6719 0.8466
-0.250 0.4201 0.02317 0.01385 -0.0878 0.6625 0.9041
0.000 0.4722 0.02309 0.01352 -0.0925 0.6542 1.0000
0.250 0.4972 0.02345 0.01365 -0.0929 0.6448 1.0000
0.500 0.5286 0.02363 0.01353 -0.0938 0.6379 1.0000
0.750 0.5520 0.02413 0.01388 -0.0938 0.6279 1.0000
1.000 0.5836 0.02431 0.01380 -0.0944 0.6213 1.0000
1.250 0.6055 0.02491 0.01430 -0.0941 0.6115 1.0000
1.500 0.6351 0.02517 0.01435 -0.0944 0.6046 1.0000
1.750 0.6580 0.02575 0.01484 -0.0940 0.5957 1.0000
2.000 0.6848 0.02613 0.01508 -0.0939 0.5883 1.0000
2.250 0.7103 0.02660 0.01544 -0.0937 0.5809 1.0000
2.500 0.7332 0.02718 0.01595 -0.0933 0.5725 1.0000
2.750 0.7638 0.02738 0.01599 -0.0934 0.5671 1.0000
3.000 0.7805 0.02830 0.01695 -0.0924 0.5575 1.0000
3.250 0.8085 0.02862 0.01716 -0.0923 0.5515 1.0000
3.500 0.8280 0.02942 0.01796 -0.0915 0.5435 1.0000
3.750 0.8518 0.02997 0.01848 -0.0911 0.5366 1.0000
4.000 0.8803 0.03027 0.01869 -0.0910 0.5314 1.0000
4.250 0.8938 0.03144 0.01994 -0.0897 0.5225 1.0000
4.500 0.9218 0.03174 0.02019 -0.0895 0.5173 1.0000
4.750 0.9370 0.03283 0.02134 -0.0884 0.5096 1.0000
5.000 0.9586 0.03351 0.02203 -0.0877 0.5031 1.0000
5.250 0.9900 0.03362 0.02209 -0.0878 0.4989 1.0000
5.500 0.9947 0.03533 0.02393 -0.0858 0.4896 1.0000
5.750 1.0243 0.03540 0.02397 -0.0856 0.4841 1.0000
6.000 1.0334 0.03674 0.02541 -0.0838 0.4753 1.0000
6.250 1.0606 0.03680 0.02545 -0.0833 0.4685 1.0000
6.500 1.0725 0.03780 0.02651 -0.0816 0.4595 1.0000
6.750 1.0986 0.03784 0.02656 -0.0809 0.4522 1.0000
7.000 1.1096 0.03891 0.02771 -0.0792 0.4438 1.0000
7.250 1.1294 0.03945 0.02829 -0.0782 0.4366 1.0000
7.500 1.1535 0.03984 0.02870 -0.0775 0.4309 1.0000
7.750 1.1489 0.04201 0.03103 -0.0748 0.4223 1.0000
8.000 1.1845 0.04163 0.03065 -0.0750 0.4175 1.0000
8.250 1.1603 0.04495 0.03412 -0.0708 0.4081 1.0000
8.500 1.1874 0.04503 0.03425 -0.0703 0.4025 1.0000
8.750 1.1709 0.04823 0.03756 -0.0675 0.3940 1.0000
9.000 1.1797 0.04970 0.03912 -0.0662 0.3871 1.0000
9.250 1.2256 0.04839 0.03786 -0.0664 0.3836 1.0000
9.500 1.1634 0.05613 0.04574 -0.0636 0.3705 1.0000
9.750 1.2047 0.05470 0.04437 -0.0629 0.3675 1.0000
10.000 1.1471 0.06364 0.05343 -0.0627 0.3531 1.0000
10.250 1.1867 0.06193 0.05179 -0.0614 0.3506 1.0000
10.750 1.1716 0.06975 0.05978 -0.0611 0.3335 1.0000
11.250 1.1518 0.07909 0.06930 -0.0620 0.3166 1.0000
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Polar data table (+)
Polar graphs
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