GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 100,000 Max Cl/Cd: 60.03 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe529-il-100000-n5.txt Download as CSV file: xf-goe529-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 529 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2493 0.11129 0.10666 -0.0400 1.0000 0.0468
-9.000 -0.2584 0.11026 0.10574 -0.0401 1.0000 0.0471
-8.750 -0.2706 0.10937 0.10499 -0.0391 1.0000 0.0472
-8.500 -0.2606 0.10597 0.10162 -0.0443 0.9906 0.0473
-8.250 -0.2359 0.09920 0.09484 -0.0420 0.9895 0.0487
-8.000 -0.2157 0.09513 0.09076 -0.0449 0.9809 0.0502
-7.750 -0.1975 0.09137 0.08698 -0.0490 0.9700 0.0519
-7.500 -0.1803 0.08787 0.08348 -0.0541 0.9575 0.0553
-7.250 -0.1606 0.08444 0.08001 -0.0709 0.9361 0.0586
-7.000 -0.1372 0.07988 0.07537 -0.0797 0.9217 0.0588
-6.750 -0.1225 0.07487 0.07038 -0.0794 0.9115 0.0595
-6.250 -0.0782 0.06372 0.05897 -0.0905 0.8863 0.0471
-5.750 -0.0345 0.05493 0.04987 -0.0987 0.8615 0.0470
-5.500 -0.0142 0.05121 0.04602 -0.1010 0.8490 0.0465
-5.250 0.0080 0.04719 0.04179 -0.1043 0.8369 0.0484
-5.000 0.0291 0.04595 0.04048 -0.1043 0.8262 0.0511
-4.750 0.0549 0.04149 0.03568 -0.1076 0.8160 0.0504
-4.500 0.0794 0.03736 0.03118 -0.1097 0.8046 0.0501
-4.250 0.1040 0.03518 0.02874 -0.1105 0.7939 0.0523
-4.000 0.1305 0.03216 0.02529 -0.1115 0.7845 0.0539
-3.750 0.1552 0.02925 0.02194 -0.1119 0.7737 0.0540
-3.500 0.1812 0.02679 0.01896 -0.1121 0.7645 0.0545
-3.250 0.2078 0.02480 0.01648 -0.1121 0.7560 0.0557
-3.000 0.2345 0.02334 0.01448 -0.1118 0.7473 0.0583
-2.750 0.2618 0.02202 0.01279 -0.1116 0.7400 0.0593
-2.500 0.2876 0.02102 0.01159 -0.1113 0.7315 0.0604
-2.250 0.3150 0.02022 0.01059 -0.1111 0.7247 0.0618
-2.000 0.3412 0.01958 0.00981 -0.1107 0.7166 0.0637
-1.750 0.3686 0.01896 0.00901 -0.1103 0.7099 0.0661
-1.500 0.3948 0.01850 0.00841 -0.1099 0.7023 0.0698
-1.250 0.4216 0.01808 0.00792 -0.1096 0.6956 0.0753
-1.000 0.4476 0.01774 0.00754 -0.1091 0.6884 0.0813
-0.750 0.4740 0.01735 0.00707 -0.1086 0.6817 0.0890
-0.500 0.5002 0.01708 0.00678 -0.1081 0.6749 0.1024
-0.250 0.5268 0.01688 0.00660 -0.1078 0.6678 0.1223
0.000 0.5535 0.01677 0.00651 -0.1075 0.6614 0.1542
0.250 0.5797 0.01664 0.00650 -0.1072 0.6541 0.2012
0.500 0.6069 0.01636 0.00638 -0.1071 0.6481 0.2728
1.000 0.6739 0.01498 0.00629 -0.1091 0.6339 1.0000
1.250 0.6986 0.01519 0.00638 -0.1084 0.6260 1.0000
1.500 0.7250 0.01537 0.00638 -0.1080 0.6193 1.0000
1.750 0.7497 0.01560 0.00652 -0.1074 0.6115 1.0000
2.000 0.7757 0.01579 0.00658 -0.1069 0.6045 1.0000
2.250 0.8002 0.01601 0.00674 -0.1063 0.5964 1.0000
2.500 0.8259 0.01620 0.00684 -0.1058 0.5891 1.0000
2.750 0.8501 0.01643 0.00704 -0.1051 0.5806 1.0000
3.000 0.8758 0.01662 0.00714 -0.1046 0.5731 1.0000
3.250 0.8994 0.01685 0.00739 -0.1038 0.5639 1.0000
3.500 0.9249 0.01702 0.00748 -0.1033 0.5565 1.0000
3.750 0.9481 0.01726 0.00775 -0.1025 0.5467 1.0000
4.000 0.9726 0.01746 0.00795 -0.1019 0.5385 1.0000
4.250 0.9966 0.01768 0.00817 -0.1012 0.5298 1.0000
4.500 1.0203 0.01792 0.00843 -0.1005 0.5212 1.0000
5.000 1.0677 0.01840 0.00897 -0.0990 0.5040 1.0000
5.250 1.0915 0.01861 0.00917 -0.0983 0.4954 1.0000
5.500 1.1145 0.01888 0.00948 -0.0974 0.4862 1.0000
5.750 1.1375 0.01917 0.00982 -0.0966 0.4772 1.0000
6.000 1.1609 0.01941 0.01006 -0.0958 0.4689 1.0000
6.250 1.1827 0.01976 0.01048 -0.0949 0.4590 1.0000
6.500 1.2055 0.02008 0.01084 -0.0941 0.4507 1.0000
6.750 1.2274 0.02045 0.01127 -0.0931 0.4420 1.0000
7.000 1.2493 0.02084 0.01173 -0.0922 0.4337 1.0000
7.250 1.2712 0.02122 0.01215 -0.0913 0.4252 1.0000
7.500 1.2916 0.02168 0.01274 -0.0902 0.4159 1.0000
7.750 1.3132 0.02209 0.01318 -0.0892 0.4079 1.0000
8.000 1.3326 0.02259 0.01385 -0.0880 0.3991 1.0000
8.250 1.3536 0.02306 0.01440 -0.0870 0.3917 1.0000
8.500 1.3708 0.02355 0.01499 -0.0854 0.3805 1.0000
8.750 1.3839 0.02403 0.01553 -0.0832 0.3642 1.0000
9.000 1.3936 0.02459 0.01617 -0.0805 0.3457 1.0000
9.250 1.4033 0.02521 0.01687 -0.0779 0.3291 1.0000
9.500 1.4108 0.02590 0.01762 -0.0750 0.3134 1.0000
9.750 1.4154 0.02672 0.01848 -0.0718 0.2958 1.0000
10.000 1.4172 0.02777 0.01949 -0.0686 0.2762 1.0000
10.250 1.4195 0.02897 0.02071 -0.0657 0.2566 1.0000
10.500 1.4183 0.03049 0.02224 -0.0628 0.2347 1.0000
10.750 1.4155 0.03230 0.02402 -0.0601 0.2113 1.0000
11.000 1.4081 0.03465 0.02627 -0.0576 0.1786 1.0000
11.250 1.3928 0.03790 0.02927 -0.0552 0.1421 1.0000
11.500 1.3780 0.04149 0.03268 -0.0535 0.1222 1.0000
11.750 1.3662 0.04511 0.03625 -0.0522 0.1037 1.0000
12.000 1.3543 0.04898 0.04007 -0.0514 0.0679 1.0000
12.250 1.3376 0.05358 0.04452 -0.0510 0.0538 1.0000
12.500 1.3259 0.05782 0.04878 -0.0508 0.0446 1.0000
12.750 1.3151 0.06214 0.05317 -0.0508 0.0374 1.0000
13.000 1.3059 0.06644 0.05756 -0.0510 0.0327 1.0000
13.250 1.2971 0.07085 0.06206 -0.0515 0.0301 1.0000
13.500 1.2894 0.07527 0.06662 -0.0521 0.0282 1.0000
13.750 1.2820 0.07982 0.07131 -0.0529 0.0270 1.0000
14.000 1.2734 0.08468 0.07629 -0.0540 0.0258 1.0000
14.250 1.2646 0.08971 0.08145 -0.0553 0.0250 1.0000
14.500 1.2563 0.09481 0.08665 -0.0567 0.0244 1.0000
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Polar data table (+)
Polar graphs
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