GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 50,000 Max Cl/Cd: 32.49 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe534-il-50000-n5.txt Download as CSV file: xf-goe534-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 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 -0.2415 0.10281 0.09552 -0.0323 1.0000 0.0961
-9.000 -0.2424 0.09982 0.09261 -0.0327 1.0000 0.0956
-8.750 -0.2452 0.09678 0.08968 -0.0331 1.0000 0.0950
-8.500 -0.2500 0.09384 0.08685 -0.0332 1.0000 0.0945
-8.250 -0.2571 0.09115 0.08429 -0.0330 1.0000 0.0944
-8.000 -0.2673 0.08889 0.08218 -0.0321 1.0000 0.0949
-7.750 -0.2842 0.08714 0.08061 -0.0301 1.0000 0.0954
-7.500 -0.3082 0.08592 0.07956 -0.0271 1.0000 0.0953
-7.250 -0.2981 0.08079 0.07444 -0.0340 0.9858 0.0971
-7.000 -0.2827 0.07289 0.06647 -0.0460 0.9677 0.0987
-6.750 -0.2704 0.06271 0.05613 -0.0602 0.9491 0.1010
-6.500 -0.2363 0.06105 0.05445 -0.0632 0.9369 0.1048
-6.250 -0.2208 0.04633 0.03890 -0.0834 0.9200 0.1123
-6.000 -0.1875 0.04579 0.03844 -0.0842 0.9066 0.1167
-5.750 -0.1565 0.04040 0.03242 -0.0914 0.8933 0.1252
-5.500 -0.1184 0.03915 0.03109 -0.0938 0.8821 0.1330
-5.250 -0.0884 0.03725 0.02893 -0.0958 0.8671 0.1404
-5.000 -0.0561 0.03564 0.02707 -0.0976 0.8533 0.1476
-4.750 -0.0204 0.03355 0.02459 -0.0999 0.8414 0.1534
-4.500 0.0087 0.03256 0.02349 -0.1002 0.8259 0.1577
-4.250 0.0385 0.03117 0.02177 -0.1009 0.8112 0.1620
-4.000 0.0706 0.02979 0.01998 -0.1017 0.7979 0.1670
-3.750 0.0996 0.02910 0.01924 -0.1015 0.7832 0.1707
-3.500 0.1267 0.02840 0.01839 -0.1010 0.7678 0.1744
-3.250 0.1554 0.02766 0.01739 -0.1008 0.7536 0.1796
-3.000 0.1848 0.02705 0.01662 -0.1006 0.7402 0.1853
-2.750 0.2105 0.02670 0.01624 -0.0999 0.7247 0.1909
-2.500 0.2387 0.02623 0.01556 -0.0995 0.7107 0.1982
-2.250 0.2673 0.02583 0.01511 -0.0990 0.6984 0.2057
-2.000 0.2930 0.02559 0.01475 -0.0983 0.6834 0.2174
-1.750 0.3201 0.02541 0.01460 -0.0977 0.6700 0.2315
-1.500 0.3494 0.02518 0.01431 -0.0973 0.6582 0.2519
-1.250 0.3752 0.02513 0.01429 -0.0966 0.6441 0.2759
-1.000 0.4017 0.02514 0.01433 -0.0958 0.6316 0.3021
-0.750 0.4293 0.02517 0.01427 -0.0951 0.6201 0.3320
-0.500 0.4542 0.02534 0.01444 -0.0941 0.6069 0.3576
-0.250 0.4806 0.02544 0.01449 -0.0932 0.5956 0.3829
0.000 0.5058 0.02566 0.01464 -0.0922 0.5838 0.4152
0.250 0.5293 0.02589 0.01495 -0.0909 0.5719 0.4453
0.500 0.5563 0.02594 0.01488 -0.0899 0.5618 0.4753
0.750 0.5805 0.02609 0.01504 -0.0890 0.5494 0.4967
1.000 0.6082 0.02609 0.01493 -0.0884 0.5391 0.5164
1.250 0.6341 0.02619 0.01499 -0.0878 0.5276 0.5351
1.500 0.6608 0.02628 0.01503 -0.0872 0.5172 0.5549
1.750 0.6875 0.02636 0.01508 -0.0866 0.5066 0.5757
2.000 0.7132 0.02649 0.01524 -0.0860 0.4961 0.5992
2.250 0.7394 0.02654 0.01532 -0.0854 0.4861 0.6262
3.000 0.8203 0.02670 0.01600 -0.0843 0.4556 1.0000
3.250 0.8470 0.02716 0.01624 -0.0840 0.4463 1.0000
3.500 0.8710 0.02778 0.01675 -0.0834 0.4366 1.0000
3.750 0.8961 0.02827 0.01709 -0.0828 0.4274 1.0000
4.000 0.9195 0.02889 0.01761 -0.0820 0.4183 1.0000
4.250 0.9429 0.02947 0.01811 -0.0812 0.4093 1.0000
4.500 0.9668 0.03005 0.01858 -0.0805 0.4012 1.0000
4.750 0.9878 0.03077 0.01928 -0.0795 0.3920 1.0000
5.000 1.0136 0.03120 0.01954 -0.0788 0.3850 1.0000
5.250 1.0310 0.03217 0.02059 -0.0776 0.3757 1.0000
5.500 1.0562 0.03262 0.02090 -0.0769 0.3690 1.0000
5.750 1.0732 0.03364 0.02199 -0.0756 0.3606 1.0000
6.000 1.0948 0.03430 0.02260 -0.0746 0.3534 1.0000
6.250 1.1163 0.03501 0.02326 -0.0736 0.3469 1.0000
6.500 1.1313 0.03615 0.02449 -0.0722 0.3392 1.0000
6.750 1.1554 0.03662 0.02486 -0.0714 0.3333 1.0000
7.000 1.1682 0.03791 0.02625 -0.0698 0.3262 1.0000
7.250 1.1843 0.03893 0.02731 -0.0685 0.3197 1.0000
7.500 1.2105 0.03928 0.02753 -0.0679 0.3147 1.0000
7.750 1.2136 0.04116 0.02962 -0.0657 0.3078 1.0000
8.000 1.2280 0.04222 0.03071 -0.0642 0.3018 1.0000
8.250 1.2555 0.04250 0.03087 -0.0637 0.2972 1.0000
8.500 1.2480 0.04500 0.03363 -0.0608 0.2911 1.0000
8.750 1.2542 0.04652 0.03522 -0.0589 0.2855 1.0000
9.000 1.2808 0.04678 0.03537 -0.0583 0.2809 1.0000
9.250 1.2673 0.04951 0.03828 -0.0552 0.2761 1.0000
9.500 1.2426 0.05328 0.04228 -0.0523 0.2710 1.0000
9.750 1.2528 0.05466 0.04366 -0.0511 0.2664 1.0000
10.000 1.2925 0.05385 0.04270 -0.0507 0.2624 1.0000
10.250 1.1018 0.07790 0.06747 -0.0552 0.2514 1.0000
10.500 1.1280 0.07735 0.06689 -0.0537 0.2485 1.0000
10.750 1.1795 0.07339 0.06284 -0.0507 0.2467 1.0000
11.000 1.0378 0.09979 0.08955 -0.0623 0.2311 1.0000
11.250 1.0663 0.09840 0.08815 -0.0603 0.2293 1.0000
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Polar data table (+)
Polar graphs
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