GOE 522 AIRFOIL (goe522-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 522 AIRFOIL (goe522-il) Reynolds number: 100,000 Max Cl/Cd: 32.13 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe522-il-100000.txt Download as CSV file: xf-goe522-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 522 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5402 0.08483 0.07954 -0.0770 0.9835 0.0885
-11.500 -0.6231 0.06999 0.06431 -0.0889 0.9780 0.0872
-11.250 -0.6801 0.06274 0.05675 -0.0928 0.9678 0.0866
-11.000 -0.7190 0.05887 0.05260 -0.0927 0.9584 0.0863
-10.750 -0.7374 0.05551 0.04891 -0.0922 0.9495 0.0865
-10.500 -0.7463 0.05273 0.04582 -0.0910 0.9407 0.0870
-10.250 -0.7447 0.04986 0.04251 -0.0908 0.9324 0.0881
-10.000 -0.7237 0.04835 0.04094 -0.0915 0.9255 0.0895
-9.750 -0.7062 0.04734 0.03996 -0.0910 0.9166 0.0913
-9.500 -0.6735 0.04568 0.03810 -0.0936 0.9111 0.0941
-9.250 -0.6723 0.04417 0.03633 -0.0907 0.9000 0.0959
-9.000 -0.6358 0.04306 0.03529 -0.0928 0.8938 0.0988
-8.750 -0.6192 0.04210 0.03428 -0.0918 0.8847 0.1019
-8.500 -0.5949 0.04076 0.03280 -0.0921 0.8765 0.1061
-8.250 -0.5533 0.03950 0.03143 -0.0950 0.8719 0.1140
-8.000 -0.5473 0.03901 0.03111 -0.0919 0.8589 0.1186
-7.750 -0.5097 0.03783 0.02985 -0.0940 0.8533 0.1331
-7.500 -0.4994 0.03737 0.02941 -0.0916 0.8412 0.1431
-7.250 -0.4650 0.03658 0.02851 -0.0931 0.8347 0.1580
-7.000 -0.4418 0.03616 0.02816 -0.0926 0.8253 0.1681
-6.750 -0.4138 0.03558 0.02754 -0.0927 0.8163 0.1784
-6.500 -0.3688 0.03478 0.02665 -0.0954 0.8123 0.1906
-6.250 -0.3586 0.03478 0.02673 -0.0927 0.7984 0.1960
-6.000 -0.3173 0.03393 0.02572 -0.0946 0.7937 0.2053
-5.750 -0.2977 0.03382 0.02570 -0.0932 0.7828 0.2110
-5.500 -0.2640 0.03316 0.02484 -0.0939 0.7757 0.2198
-5.250 -0.2171 0.03239 0.02421 -0.0964 0.7726 0.2297
-5.000 -0.2075 0.03242 0.02406 -0.0936 0.7591 0.2364
-4.750 -0.1661 0.03173 0.02349 -0.0951 0.7548 0.2461
-4.500 -0.1201 0.03080 0.02251 -0.0974 0.7523 0.2589
-4.250 -0.1123 0.03114 0.02285 -0.0942 0.7392 0.2666
-4.000 -0.0711 0.03037 0.02208 -0.0957 0.7350 0.2808
-3.750 -0.0223 0.02949 0.02120 -0.0984 0.7324 0.2993
-3.500 0.0328 0.02864 0.02038 -0.1022 0.7304 0.3218
-3.250 0.0224 0.02934 0.02103 -0.0961 0.7156 0.3313
-3.000 0.0705 0.02858 0.02025 -0.0988 0.7126 0.3553
-2.750 0.1277 0.02772 0.01940 -0.1030 0.7103 0.3806
-2.500 0.1134 0.02855 0.02036 -0.0961 0.6966 0.3873
-2.250 0.1618 0.02794 0.01974 -0.0988 0.6929 0.4090
-2.000 0.2184 0.02727 0.01902 -0.1028 0.6900 0.4308
-1.750 0.2028 0.02826 0.02007 -0.0958 0.6782 0.4375
-1.500 0.2409 0.02798 0.01973 -0.0971 0.6733 0.4542
-1.250 0.2944 0.02741 0.01900 -0.1009 0.6700 0.4728
-1.000 0.3150 0.02756 0.01925 -0.0995 0.6634 0.4825
-0.750 0.3120 0.02819 0.01987 -0.0945 0.6540 0.4909
-0.500 0.3623 0.02762 0.01925 -0.0978 0.6505 0.5050
-0.250 0.4161 0.02708 0.01852 -0.1019 0.6476 0.5212
0.000 0.3648 0.02898 0.02057 -0.0896 0.6357 0.5224
0.250 0.4086 0.02855 0.02018 -0.0917 0.6317 0.5370
0.500 0.4658 0.02787 0.01945 -0.0960 0.6287 0.5554
0.750 0.4248 0.02969 0.02137 -0.0856 0.6191 0.5596
1.000 0.4351 0.03026 0.02193 -0.0830 0.6130 0.5724
1.250 0.4875 0.02954 0.02116 -0.0864 0.6101 0.5923
1.500 0.5532 0.02864 0.02023 -0.0920 0.6076 0.6121
1.750 0.4423 0.03337 0.02520 -0.0727 0.5933 0.6075
2.000 0.4938 0.03226 0.02408 -0.0754 0.5910 0.6284
2.250 0.5610 0.03067 0.02248 -0.0804 0.5889 0.6562
2.500 0.5638 0.03151 0.02341 -0.0767 0.5825 0.6751
2.750 0.5166 0.03455 0.02656 -0.0672 0.5712 0.6868
3.000 0.6177 0.03088 0.02288 -0.0753 0.5697 0.7347
3.250 0.7299 0.02818 0.02013 -0.0867 0.5662 0.7925
3.750 0.7414 0.03000 0.02247 -0.0809 0.5511 0.9257
4.000 0.8727 0.02859 0.02069 -0.0984 0.5467 1.0000
4.250 0.8257 0.03057 0.02271 -0.0877 0.5398 1.0000
4.500 0.8092 0.03211 0.02422 -0.0818 0.5326 1.0000
4.750 0.8761 0.03118 0.02307 -0.0874 0.5286 1.0000
5.000 0.9700 0.03019 0.02176 -0.0976 0.5245 1.0000
5.250 0.8162 0.03586 0.02783 -0.0728 0.5130 1.0000
5.500 0.8851 0.03427 0.02605 -0.0776 0.5094 1.0000
5.750 0.9791 0.03245 0.02396 -0.0865 0.5057 1.0000
6.000 0.6912 0.04968 0.04182 -0.0558 0.4775 1.0000
6.250 0.7574 0.04639 0.03838 -0.0576 0.4774 1.0000
6.500 0.8352 0.04281 0.03464 -0.0608 0.4773 1.0000
6.750 0.8384 0.04431 0.03611 -0.0587 0.4691 1.0000
7.000 0.9208 0.04094 0.03257 -0.0629 0.4681 1.0000
7.250 1.0163 0.03779 0.02920 -0.0697 0.4659 1.0000
7.500 0.8700 0.04764 0.03937 -0.0543 0.4477 1.0000
7.750 0.9508 0.04397 0.03554 -0.0578 0.4471 1.0000
8.000 1.0494 0.04019 0.03153 -0.0640 0.4456 1.0000
8.250 0.9098 0.05041 0.04206 -0.0508 0.4271 1.0000
8.500 0.9934 0.04623 0.03771 -0.0540 0.4268 1.0000
8.750 1.0958 0.04190 0.03315 -0.0600 0.4254 1.0000
9.000 0.9038 0.05736 0.04900 -0.0458 0.4022 1.0000
9.250 0.9729 0.05346 0.04498 -0.0471 0.4022 1.0000
9.500 1.0663 0.04845 0.03980 -0.0506 0.4026 1.0000
9.750 0.9433 0.06090 0.05248 -0.0435 0.3852 1.0000
10.000 1.0106 0.05699 0.04847 -0.0445 0.3852 1.0000
10.250 1.0984 0.05208 0.04339 -0.0471 0.3855 1.0000
10.500 0.5010 0.13489 0.12735 -0.0549 0.4021 1.0000
10.750 0.4923 0.13712 0.12958 -0.0552 0.3965 1.0000
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Polar data table (+)
Polar graphs
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