GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.72 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe115-il-1000000-n5.txt Download as CSV file: xf-goe115-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 115 (MVA MK.2) 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6003 0.07414 0.07262 -0.0454 1.0000 0.0039
-11.250 -0.7757 0.03595 0.03400 -0.0759 1.0000 0.0032
-11.000 -0.7717 0.02863 0.02616 -0.0830 0.9903 0.0033
-10.750 -0.7521 0.02522 0.02242 -0.0859 0.9828 0.0034
-10.500 -0.7256 0.02275 0.01966 -0.0887 0.9762 0.0035
-10.250 -0.6973 0.02067 0.01731 -0.0911 0.9670 0.0036
-10.000 -0.6676 0.01855 0.01491 -0.0937 0.9546 0.0038
-9.750 -0.6369 0.01728 0.01344 -0.0955 0.9388 0.0041
-9.500 -0.6102 0.01633 0.01229 -0.0961 0.9178 0.0042
-9.250 -0.5863 0.01564 0.01142 -0.0959 0.8972 0.0044
-9.000 -0.5635 0.01497 0.01055 -0.0953 0.8780 0.0046
-8.750 -0.5404 0.01434 0.00973 -0.0948 0.8623 0.0049
-8.500 -0.5168 0.01375 0.00899 -0.0943 0.8486 0.0051
-8.250 -0.4927 0.01323 0.00831 -0.0939 0.8363 0.0053
-8.000 -0.4683 0.01271 0.00764 -0.0935 0.8247 0.0056
-7.750 -0.4439 0.01214 0.00695 -0.0931 0.8135 0.0062
-7.500 -0.4188 0.01173 0.00645 -0.0927 0.8027 0.0067
-7.250 -0.3933 0.01140 0.00601 -0.0924 0.7914 0.0074
-6.750 -0.3420 0.01068 0.00507 -0.0918 0.7684 0.0088
-6.500 -0.3157 0.01044 0.00477 -0.0916 0.7570 0.0100
-6.250 -0.2893 0.01024 0.00450 -0.0914 0.7450 0.0113
-6.000 -0.2628 0.01007 0.00425 -0.0912 0.7322 0.0128
-5.750 -0.2354 0.01012 0.00430 -0.0911 0.7185 0.0147
-5.500 -0.2082 0.01012 0.00423 -0.0909 0.7043 0.0164
-5.250 -0.1814 0.01006 0.00408 -0.0908 0.6897 0.0175
-5.000 -0.1541 0.01011 0.00405 -0.0907 0.6757 0.0181
-4.750 -0.1282 0.00979 0.00363 -0.0904 0.6628 0.0193
-4.500 -0.1013 0.00967 0.00344 -0.0902 0.6513 0.0203
-4.250 -0.0742 0.00956 0.00328 -0.0901 0.6419 0.0214
-4.000 -0.0473 0.00940 0.00305 -0.0900 0.6335 0.0224
-3.750 -0.0202 0.00924 0.00282 -0.0899 0.6258 0.0233
-3.500 0.0068 0.00909 0.00260 -0.0897 0.6189 0.0241
-3.250 0.0340 0.00892 0.00236 -0.0896 0.6126 0.0247
-3.000 0.0612 0.00880 0.00218 -0.0895 0.6066 0.0253
-2.750 0.0886 0.00866 0.00200 -0.0894 0.6013 0.0258
-2.500 0.1160 0.00856 0.00186 -0.0893 0.5956 0.0263
-2.250 0.1434 0.00849 0.00175 -0.0892 0.5905 0.0266
-2.000 0.1709 0.00834 0.00155 -0.0892 0.5859 0.0275
-1.750 0.1983 0.00823 0.00139 -0.0891 0.5813 0.0285
-1.250 0.2534 0.00809 0.00119 -0.0889 0.5722 0.0299
-1.000 0.2809 0.00805 0.00113 -0.0889 0.5668 0.0304
-0.500 0.3360 0.00799 0.00102 -0.0887 0.5571 0.0313
-0.250 0.3637 0.00796 0.00099 -0.0887 0.5528 0.0323
0.000 0.3912 0.00794 0.00096 -0.0886 0.5489 0.0333
0.250 0.4188 0.00793 0.00095 -0.0886 0.5450 0.0340
0.500 0.4465 0.00792 0.00094 -0.0886 0.5404 0.0353
0.750 0.4738 0.00785 0.00094 -0.0885 0.5367 0.0717
1.000 0.4999 0.00752 0.00090 -0.0883 0.5335 0.1838
1.250 0.5267 0.00737 0.00098 -0.0882 0.5303 0.2567
1.500 0.5543 0.00736 0.00104 -0.0882 0.5262 0.2720
1.750 0.5818 0.00739 0.00109 -0.0881 0.5218 0.2807
2.000 0.6091 0.00743 0.00115 -0.0880 0.5175 0.2873
2.250 0.6368 0.00744 0.00121 -0.0880 0.5138 0.2931
2.500 0.6641 0.00747 0.00128 -0.0880 0.5077 0.3005
2.750 0.6911 0.00751 0.00136 -0.0878 0.4980 0.3116
3.000 0.7179 0.00757 0.00145 -0.0877 0.4892 0.3236
3.250 0.7450 0.00760 0.00153 -0.0876 0.4798 0.3350
3.500 0.7700 0.00780 0.00163 -0.0871 0.4439 0.3426
4.000 0.8116 0.00901 0.00227 -0.0849 0.2969 0.3633
4.250 0.8327 0.00959 0.00262 -0.0839 0.2347 0.3818
4.500 0.8413 0.01130 0.00355 -0.0810 0.0510 0.4066
4.750 0.8634 0.01139 0.00389 -0.0802 0.0327 0.5342
5.250 0.9244 0.01115 0.00460 -0.0820 0.0129 1.0000
5.500 0.9487 0.01142 0.00488 -0.0814 0.0113 1.0000
5.750 0.9723 0.01172 0.00520 -0.0808 0.0097 1.0000
6.000 0.9950 0.01211 0.00560 -0.0799 0.0081 1.0000
6.250 1.0181 0.01245 0.00597 -0.0791 0.0075 1.0000
6.500 1.0409 0.01281 0.00636 -0.0783 0.0069 1.0000
6.750 1.0632 0.01319 0.00677 -0.0774 0.0064 1.0000
7.000 1.0854 0.01356 0.00713 -0.0766 0.0057 1.0000
7.250 1.1049 0.01413 0.00777 -0.0752 0.0052 1.0000
7.500 1.1259 0.01455 0.00823 -0.0742 0.0049 1.0000
7.750 1.1457 0.01505 0.00878 -0.0729 0.0047 1.0000
8.000 1.1651 0.01555 0.00933 -0.0716 0.0044 1.0000
8.250 1.1832 0.01611 0.00994 -0.0701 0.0042 1.0000
8.500 1.2012 0.01664 0.01051 -0.0686 0.0039 1.0000
8.750 1.2176 0.01724 0.01116 -0.0668 0.0038 1.0000
9.000 1.2326 0.01784 0.01180 -0.0649 0.0036 1.0000
9.250 1.2443 0.01848 0.01251 -0.0623 0.0035 1.0000
9.500 1.2526 0.01930 0.01339 -0.0593 0.0033 1.0000
9.750 1.2582 0.02034 0.01452 -0.0560 0.0033 1.0000
10.000 1.2672 0.02125 0.01552 -0.0535 0.0031 1.0000
10.250 1.2780 0.02210 0.01644 -0.0514 0.0030 1.0000
10.500 1.2846 0.02330 0.01774 -0.0489 0.0030 1.0000
10.750 1.2968 0.02415 0.01866 -0.0473 0.0028 1.0000
11.000 1.3020 0.02560 0.02022 -0.0451 0.0028 1.0000
11.250 1.3121 0.02672 0.02141 -0.0435 0.0027 1.0000
11.500 1.3212 0.02796 0.02274 -0.0420 0.0026 1.0000
11.750 1.3286 0.02941 0.02429 -0.0405 0.0025 1.0000
12.000 1.3322 0.03132 0.02633 -0.0387 0.0025 1.0000
12.250 1.3418 0.03264 0.02772 -0.0377 0.0023 1.0000
12.500 1.3475 0.03441 0.02959 -0.0364 0.0023 1.0000
12.750 1.3504 0.03652 0.03184 -0.0351 0.0023 1.0000
13.000 1.3603 0.03789 0.03325 -0.0345 0.0022 1.0000
13.250 1.3618 0.04025 0.03575 -0.0335 0.0022 1.0000
13.500 1.3669 0.04223 0.03782 -0.0328 0.0021 1.0000
13.750 1.3667 0.04490 0.04063 -0.0321 0.0021 1.0000
14.000 1.3690 0.04731 0.04315 -0.0317 0.0020 1.0000
14.250 1.3693 0.05003 0.04599 -0.0313 0.0020 1.0000
14.500 1.3664 0.05322 0.04932 -0.0311 0.0020 1.0000
14.750 1.3607 0.05687 0.05312 -0.0311 0.0020 1.0000
15.000 1.3552 0.06064 0.05704 -0.0313 0.0020 1.0000
15.250 1.3460 0.06510 0.06166 -0.0320 0.0019 1.0000
15.500 1.3315 0.07048 0.06724 -0.0330 0.0019 1.0000
15.750 1.3221 0.07536 0.07227 -0.0343 0.0019 1.0000
16.000 1.3027 0.08211 0.07923 -0.0364 0.0019 1.0000
16.250 1.2819 0.08945 0.08678 -0.0391 0.0018 1.0000
16.500 1.2752 0.09460 0.09204 -0.0413 0.0019 1.0000
16.750 1.2449 0.10468 0.10235 -0.0460 0.0018 1.0000
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Polar data table (+)
Polar graphs
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