GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 50,000 Max Cl/Cd: 36.51 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe477-il-50000-n5.txt Download as CSV file: xf-goe477-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3515 0.11197 0.10598 -0.0262 1.0000 0.0942
-8.000 -0.3575 0.11009 0.10416 -0.0259 0.9987 0.0971
-7.750 -0.3650 0.10853 0.10267 -0.0309 0.9914 0.1009
-7.500 -0.3644 0.10566 0.09982 -0.0361 0.9846 0.1014
-7.000 -0.3457 0.09207 0.08613 -0.0442 0.9747 0.0608
-6.750 -0.3355 0.08827 0.08231 -0.0458 0.9699 0.0598
-6.500 -0.3254 0.08397 0.07799 -0.0498 0.9647 0.0596
-6.250 -0.3150 0.07958 0.07354 -0.0539 0.9592 0.0597
-6.000 -0.3017 0.07465 0.06851 -0.0591 0.9540 0.0603
-5.750 -0.2881 0.06961 0.06331 -0.0636 0.9486 0.0607
-5.500 -0.2667 0.06404 0.05750 -0.0688 0.9446 0.0609
-5.000 -0.2350 0.05774 0.05092 -0.0715 0.9353 0.0655
-4.750 -0.2081 0.05335 0.04617 -0.0753 0.9320 0.0684
-4.500 -0.1893 0.04904 0.04138 -0.0771 0.9270 0.0710
-4.250 -0.1641 0.04522 0.03700 -0.0792 0.9231 0.0756
-4.000 -0.1366 0.04306 0.03454 -0.0806 0.9198 0.0805
-3.750 -0.1073 0.03993 0.03054 -0.0821 0.9165 0.0876
-3.500 -0.0874 0.03885 0.02941 -0.0816 0.9118 0.0928
-3.250 -0.0585 0.03709 0.02700 -0.0823 0.9081 0.1010
-3.000 -0.0287 0.03595 0.02568 -0.0833 0.9049 0.1079
-2.750 -0.0006 0.03494 0.02422 -0.0837 0.9012 0.1158
-2.500 0.0230 0.03401 0.02296 -0.0832 0.8964 0.1194
-2.250 0.0518 0.03342 0.02223 -0.0836 0.8923 0.1256
-2.000 0.0847 0.03294 0.02147 -0.0848 0.8889 0.1351
-1.750 0.1091 0.03256 0.02096 -0.0843 0.8840 0.1398
-1.500 0.1363 0.03225 0.02039 -0.0842 0.8788 0.1454
-1.250 0.1720 0.03188 0.01991 -0.0856 0.8742 0.1530
-1.000 0.2010 0.03161 0.01951 -0.0858 0.8662 0.1633
-0.750 0.2399 0.03114 0.01902 -0.0875 0.8587 0.1809
-0.500 0.2684 0.03080 0.01877 -0.0876 0.8487 0.2131
-0.250 0.3097 0.02994 0.01836 -0.0900 0.8423 0.3047
0.250 0.3820 0.02829 0.01811 -0.0924 0.8277 1.0000
0.500 0.4045 0.02860 0.01819 -0.0915 0.8178 1.0000
0.750 0.4440 0.02861 0.01796 -0.0931 0.8111 1.0000
1.000 0.4647 0.02888 0.01809 -0.0918 0.7997 1.0000
1.250 0.4965 0.02890 0.01796 -0.0920 0.7903 1.0000
1.500 0.5322 0.02874 0.01767 -0.0927 0.7807 1.0000
1.750 0.5559 0.02875 0.01759 -0.0915 0.7675 1.0000
2.000 0.5809 0.02866 0.01743 -0.0904 0.7541 1.0000
2.250 0.6058 0.02852 0.01723 -0.0893 0.7402 1.0000
2.500 0.6296 0.02838 0.01704 -0.0880 0.7260 1.0000
2.750 0.6526 0.02821 0.01686 -0.0865 0.7110 1.0000
3.000 0.6751 0.02803 0.01666 -0.0850 0.6953 1.0000
3.250 0.6981 0.02779 0.01643 -0.0835 0.6792 1.0000
3.500 0.7217 0.02752 0.01617 -0.0820 0.6627 1.0000
4.000 0.7709 0.02692 0.01561 -0.0793 0.6261 1.0000
4.250 0.7952 0.02672 0.01540 -0.0780 0.6040 1.0000
4.500 0.8272 0.02622 0.01488 -0.0776 0.5823 1.0000
4.750 0.8543 0.02604 0.01466 -0.0766 0.5557 1.0000
5.000 0.8847 0.02583 0.01433 -0.0761 0.5287 1.0000
5.250 0.9150 0.02579 0.01413 -0.0757 0.5023 1.0000
5.500 0.9406 0.02609 0.01428 -0.0749 0.4786 1.0000
5.750 0.9656 0.02652 0.01454 -0.0741 0.4584 1.0000
6.000 0.9894 0.02710 0.01500 -0.0733 0.4405 1.0000
6.500 1.0361 0.02848 0.01629 -0.0720 0.4104 1.0000
6.750 1.0596 0.02923 0.01711 -0.0715 0.3977 1.0000
7.000 1.0855 0.02998 0.01792 -0.0713 0.3873 1.0000
7.250 1.1137 0.03072 0.01872 -0.0714 0.3783 1.0000
7.500 1.1385 0.03155 0.01976 -0.0712 0.3697 1.0000
7.750 1.1674 0.03232 0.02063 -0.0715 0.3622 1.0000
8.000 1.1907 0.03324 0.02178 -0.0711 0.3550 1.0000
8.250 1.2159 0.03413 0.02289 -0.0709 0.3485 1.0000
8.500 1.2442 0.03502 0.02397 -0.0711 0.3433 1.0000
8.750 1.2584 0.03602 0.02526 -0.0695 0.3349 1.0000
9.000 1.2674 0.03672 0.02608 -0.0669 0.3223 1.0000
9.250 1.2694 0.03735 0.02678 -0.0633 0.3078 1.0000
9.500 1.2698 0.03803 0.02755 -0.0596 0.2946 1.0000
9.750 1.2669 0.03888 0.02847 -0.0558 0.2809 1.0000
10.000 1.2633 0.04002 0.02976 -0.0524 0.2677 1.0000
10.250 1.2585 0.04140 0.03130 -0.0493 0.2536 1.0000
10.500 1.2534 0.04299 0.03303 -0.0465 0.2383 1.0000
10.750 1.2472 0.04490 0.03507 -0.0441 0.2198 1.0000
11.000 1.2408 0.04717 0.03754 -0.0421 0.1947 1.0000
11.250 1.2349 0.04984 0.04030 -0.0405 0.1269 1.0000
11.500 1.2125 0.05430 0.04400 -0.0391 0.0834 1.0000
11.750 1.1972 0.05893 0.04848 -0.0384 0.0723 1.0000
12.000 1.1830 0.06372 0.05331 -0.0382 0.0665 1.0000
12.250 1.1699 0.06862 0.05837 -0.0384 0.0630 1.0000
12.500 1.1556 0.07400 0.06390 -0.0393 0.0608 1.0000
12.750 1.1415 0.07964 0.06967 -0.0406 0.0591 1.0000
13.000 1.1303 0.08511 0.07534 -0.0421 0.0572 1.0000
13.250 1.1196 0.09067 0.08106 -0.0437 0.0554 1.0000
13.500 1.1100 0.09613 0.08664 -0.0454 0.0536 1.0000
13.750 1.1017 0.10134 0.09193 -0.0470 0.0518 1.0000
14.000 1.0946 0.10621 0.09687 -0.0485 0.0499 1.0000
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Polar data table (+)
Polar graphs
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