GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.56 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe177-il-1000000-n5.txt Download as CSV file: xf-goe177-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 177 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3103 0.09385 0.09236 -0.0207 0.9871 0.0031
-7.500 -0.2920 0.08650 0.08496 -0.0259 0.9392 0.0032
-7.250 -0.2883 0.08344 0.08178 -0.0269 0.8883 0.0032
-7.000 -0.2815 0.08026 0.07833 -0.0291 0.8184 0.0033
-6.750 -0.2685 0.07643 0.07433 -0.0333 0.7786 0.0033
-6.500 -0.2522 0.07204 0.06983 -0.0386 0.7517 0.0036
-6.250 -0.2328 0.06727 0.06496 -0.0447 0.7300 0.0037
-6.000 -0.2109 0.06264 0.06023 -0.0508 0.7118 0.0037
-5.500 -0.1234 0.01712 0.01317 -0.0932 0.7039 0.0029
-5.250 -0.0957 0.01458 0.01009 -0.0940 0.6867 0.0030
-5.000 -0.0679 0.01319 0.00834 -0.0943 0.6706 0.0032
-4.500 -0.0118 0.01138 0.00595 -0.0945 0.6376 0.0036
-4.250 0.0164 0.01084 0.00519 -0.0945 0.6218 0.0039
-4.000 0.0445 0.01043 0.00460 -0.0946 0.6073 0.0040
-3.750 0.0728 0.00978 0.00372 -0.0946 0.5900 0.0045
-3.500 0.1007 0.00954 0.00333 -0.0946 0.5668 0.0049
-3.250 0.1287 0.00940 0.00308 -0.0946 0.5470 0.0056
-3.000 0.1568 0.00921 0.00275 -0.0946 0.5284 0.0063
-2.750 0.1853 0.00894 0.00233 -0.0946 0.5167 0.0071
-2.500 0.2136 0.00873 0.00203 -0.0947 0.5042 0.0088
-2.250 0.2418 0.00863 0.00184 -0.0947 0.4910 0.0106
-2.000 0.2701 0.00851 0.00163 -0.0947 0.4780 0.0169
-1.500 0.3264 0.00829 0.00144 -0.0948 0.4531 0.0562
-1.250 0.3542 0.00839 0.00143 -0.0948 0.4287 0.0656
-1.000 0.3819 0.00850 0.00142 -0.0948 0.4041 0.0708
-0.750 0.4098 0.00856 0.00140 -0.0948 0.3858 0.0747
-0.500 0.4375 0.00866 0.00137 -0.0948 0.3649 0.0764
-0.250 0.4652 0.00876 0.00135 -0.0947 0.3442 0.0776
0.000 0.4929 0.00887 0.00135 -0.0947 0.3255 0.0789
0.250 0.5205 0.00899 0.00137 -0.0947 0.3082 0.0805
0.500 0.5481 0.00911 0.00139 -0.0947 0.2907 0.0812
0.750 0.5755 0.00923 0.00141 -0.0947 0.2697 0.0839
1.000 0.6027 0.00941 0.00147 -0.0946 0.2445 0.0880
1.250 0.6283 0.00989 0.00166 -0.0944 0.1821 0.0920
1.750 0.6809 0.01057 0.00208 -0.0942 0.1011 0.1195
2.000 0.7085 0.01058 0.00220 -0.0943 0.0946 0.1789
2.250 0.7351 0.01079 0.00241 -0.0942 0.0609 0.2457
2.500 0.7625 0.01083 0.00257 -0.0943 0.0573 0.3113
2.750 0.7899 0.01087 0.00272 -0.0943 0.0533 0.3676
3.250 0.8383 0.00986 0.00308 -0.0931 0.0491 1.0000
3.500 0.8655 0.01002 0.00323 -0.0931 0.0479 1.0000
3.750 0.8927 0.01020 0.00339 -0.0930 0.0459 1.0000
4.000 0.9195 0.01043 0.00359 -0.0929 0.0420 1.0000
4.250 0.9465 0.01061 0.00376 -0.0929 0.0387 1.0000
4.500 0.9724 0.01097 0.00397 -0.0927 0.0198 1.0000
4.750 0.9991 0.01118 0.00420 -0.0926 0.0126 1.0000
5.000 1.0255 0.01145 0.00453 -0.0924 0.0102 1.0000
5.250 1.0515 0.01178 0.00491 -0.0921 0.0077 1.0000
5.500 1.0776 0.01205 0.00521 -0.0919 0.0065 1.0000
5.750 1.1032 0.01242 0.00561 -0.0916 0.0052 1.0000
6.000 1.1288 0.01274 0.00598 -0.0914 0.0046 1.0000
6.250 1.1541 0.01311 0.00639 -0.0911 0.0041 1.0000
6.500 1.1790 0.01353 0.00683 -0.0907 0.0036 1.0000
6.750 1.2028 0.01408 0.00743 -0.0902 0.0032 1.0000
7.000 1.2271 0.01452 0.00792 -0.0897 0.0028 1.0000
7.250 1.2504 0.01507 0.00854 -0.0892 0.0026 1.0000
7.500 1.2735 0.01564 0.00919 -0.0885 0.0024 1.0000
7.750 1.2961 0.01622 0.00982 -0.0879 0.0022 1.0000
8.000 1.3163 0.01706 0.01074 -0.0869 0.0020 1.0000
8.250 1.3345 0.01808 0.01187 -0.0856 0.0019 1.0000
8.500 1.3520 0.01910 0.01302 -0.0842 0.0018 1.0000
8.750 1.3663 0.02037 0.01441 -0.0823 0.0017 1.0000
9.000 1.3771 0.02188 0.01604 -0.0799 0.0016 1.0000
9.250 1.3850 0.02354 0.01781 -0.0771 0.0015 1.0000
9.500 1.3927 0.02510 0.01948 -0.0744 0.0015 1.0000
9.750 1.3996 0.02640 0.02087 -0.0716 0.0014 1.0000
10.000 1.4062 0.02765 0.02221 -0.0689 0.0013 1.0000
10.250 1.4129 0.02895 0.02361 -0.0665 0.0012 1.0000
10.500 1.4179 0.03050 0.02525 -0.0642 0.0012 1.0000
10.750 1.4213 0.03234 0.02719 -0.0620 0.0011 1.0000
11.000 1.4243 0.03431 0.02928 -0.0601 0.0011 1.0000
11.250 1.4272 0.03641 0.03153 -0.0586 0.0011 1.0000
11.500 1.4291 0.03873 0.03398 -0.0574 0.0011 1.0000
11.750 1.4289 0.04144 0.03683 -0.0563 0.0010 1.0000
12.000 1.4253 0.04475 0.04029 -0.0551 0.0010 1.0000
12.250 1.4178 0.04877 0.04450 -0.0536 0.0010 1.0000
12.500 1.4150 0.05227 0.04818 -0.0528 0.0009 1.0000
12.750 1.4086 0.05632 0.05241 -0.0522 0.0009 1.0000
13.000 1.3992 0.06090 0.05719 -0.0520 0.0009 1.0000
13.250 1.3875 0.06590 0.06240 -0.0524 0.0008 1.0000
13.500 1.3749 0.07110 0.06777 -0.0534 0.0008 1.0000
13.750 1.3591 0.07702 0.07388 -0.0547 0.0008 1.0000
14.000 1.3435 0.08307 0.08011 -0.0566 0.0008 1.0000
14.250 1.3274 0.08950 0.08670 -0.0590 0.0008 1.0000
14.500 1.3121 0.09607 0.09342 -0.0618 0.0008 1.0000
14.750 1.2954 0.10316 0.10066 -0.0651 0.0008 1.0000
15.000 1.2798 0.11039 0.10802 -0.0686 0.0008 1.0000
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Polar data table (+)
Polar graphs
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