GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Reynolds number: 50,000 Max Cl/Cd: 37.86 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe115-il-50000-n5.txt Download as CSV file: xf-goe115-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3802 0.11404 0.10702 -0.0337 1.0000 0.0799
-9.750 -0.3801 0.10907 0.10209 -0.0359 1.0000 0.0668
-9.250 -0.3918 0.09948 0.09275 -0.0421 1.0000 0.0578
-9.000 -0.3860 0.09607 0.08934 -0.0421 1.0000 0.0561
-8.750 -0.3840 0.09258 0.08592 -0.0424 1.0000 0.0550
-8.500 -0.3854 0.08898 0.08241 -0.0431 1.0000 0.0540
-8.250 -0.3895 0.08548 0.07902 -0.0437 1.0000 0.0531
-8.000 -0.3973 0.08195 0.07564 -0.0442 1.0000 0.0522
-7.750 -0.4054 0.07811 0.07194 -0.0453 1.0000 0.0514
-7.500 -0.4135 0.07351 0.06747 -0.0477 1.0000 0.0504
-7.250 -0.4235 0.06752 0.06156 -0.0516 1.0000 0.0491
-7.000 -0.4361 0.06058 0.05452 -0.0564 1.0000 0.0476
-6.750 -0.4458 0.05443 0.04795 -0.0600 1.0000 0.0463
-6.500 -0.4444 0.05047 0.04366 -0.0605 1.0000 0.0461
-6.250 -0.4391 0.04728 0.04032 -0.0600 1.0000 0.0472
-6.000 -0.4310 0.04473 0.03764 -0.0594 1.0000 0.0490
-5.750 -0.3995 0.04045 0.03275 -0.0638 0.9918 0.0516
-5.500 -0.3643 0.03644 0.02798 -0.0675 0.9829 0.0531
-5.250 -0.3280 0.03353 0.02433 -0.0704 0.9742 0.0560
-5.000 -0.2936 0.03107 0.02154 -0.0727 0.9655 0.0605
-4.750 -0.2600 0.02920 0.01931 -0.0742 0.9560 0.0635
-4.500 -0.2247 0.02779 0.01749 -0.0759 0.9471 0.0692
-4.250 -0.1895 0.02632 0.01588 -0.0778 0.9385 0.0753
-4.000 -0.1558 0.02527 0.01458 -0.0791 0.9285 0.0799
-3.750 -0.1176 0.02425 0.01330 -0.0814 0.9206 0.0865
-3.500 -0.0815 0.02321 0.01226 -0.0835 0.9117 0.1024
-3.250 -0.0474 0.02242 0.01218 -0.0853 0.9025 0.2255
-3.000 -0.0096 0.02267 0.01205 -0.0870 0.8945 0.2998
-2.750 0.0194 0.02283 0.01203 -0.0873 0.8835 0.3387
-2.500 0.0508 0.02278 0.01177 -0.0880 0.8741 0.3614
-2.000 0.1149 0.02255 0.01111 -0.0896 0.8565 0.3946
-1.750 0.1448 0.02245 0.01098 -0.0900 0.8481 0.4244
-1.500 0.1744 0.02232 0.01083 -0.0903 0.8398 0.4534
-1.250 0.2016 0.02221 0.01074 -0.0903 0.8308 0.4760
-1.000 0.2341 0.02202 0.01048 -0.0911 0.8241 0.4932
-0.750 0.2602 0.02200 0.01045 -0.0910 0.8150 0.5096
-0.500 0.2922 0.02181 0.01026 -0.0917 0.8091 0.5304
-0.250 0.3166 0.02180 0.01036 -0.0914 0.8000 0.5567
0.000 0.3469 0.02149 0.01026 -0.0916 0.7944 0.6038
0.250 0.3691 0.02108 0.01046 -0.0904 0.7860 0.7325
0.500 0.4164 0.02093 0.01031 -0.0942 0.7809 1.0000
0.750 0.4406 0.02137 0.01059 -0.0939 0.7728 1.0000
1.000 0.4697 0.02163 0.01071 -0.0943 0.7668 1.0000
1.250 0.4933 0.02210 0.01108 -0.0939 0.7594 1.0000
1.500 0.5204 0.02245 0.01135 -0.0939 0.7534 1.0000
1.750 0.5452 0.02289 0.01176 -0.0937 0.7469 1.0000
2.000 0.5698 0.02334 0.01219 -0.0934 0.7402 1.0000
2.250 0.5983 0.02365 0.01248 -0.0935 0.7352 1.0000
2.500 0.6183 0.02430 0.01319 -0.0927 0.7271 1.0000
2.750 0.6477 0.02456 0.01347 -0.0928 0.7220 1.0000
3.000 0.6675 0.02515 0.01413 -0.0918 0.7126 1.0000
3.250 0.6957 0.02531 0.01437 -0.0915 0.7050 1.0000
3.500 0.7194 0.02566 0.01480 -0.0907 0.6954 1.0000
3.750 0.7421 0.02610 0.01535 -0.0898 0.6862 1.0000
4.000 0.7703 0.02632 0.01570 -0.0895 0.6794 1.0000
4.250 0.7900 0.02699 0.01657 -0.0885 0.6702 1.0000
4.500 0.8198 0.02716 0.01691 -0.0883 0.6641 1.0000
4.750 0.8377 0.02795 0.01790 -0.0871 0.6542 1.0000
5.000 0.8639 0.02831 0.01852 -0.0866 0.6466 1.0000
5.250 0.8863 0.02888 0.01936 -0.0857 0.6376 1.0000
5.500 0.9068 0.02955 0.02031 -0.0846 0.6279 1.0000
5.750 0.9410 0.02809 0.01906 -0.0825 0.6038 1.0000
6.000 0.9608 0.02638 0.01742 -0.0777 0.5562 1.0000
6.250 0.9693 0.02560 0.01671 -0.0724 0.4920 1.0000
6.500 0.9679 0.02579 0.01595 -0.0659 0.3221 1.0000
6.750 0.9469 0.02927 0.01782 -0.0604 0.1255 1.0000
7.000 0.9385 0.03208 0.02010 -0.0566 0.0841 1.0000
7.250 0.9368 0.03430 0.02225 -0.0535 0.0708 1.0000
7.500 0.9369 0.03648 0.02446 -0.0509 0.0628 1.0000
7.750 0.9386 0.03860 0.02672 -0.0486 0.0578 1.0000
8.000 0.9388 0.04098 0.02919 -0.0466 0.0546 1.0000
8.250 0.9428 0.04314 0.03147 -0.0447 0.0514 1.0000
8.500 0.9515 0.04501 0.03354 -0.0429 0.0472 1.0000
8.750 0.9629 0.04681 0.03541 -0.0412 0.0436 1.0000
9.000 1.0095 0.04790 0.03659 -0.0394 0.0402 1.0000
9.250 1.0564 0.04962 0.03866 -0.0394 0.0364 1.0000
9.500 1.0977 0.05239 0.04165 -0.0402 0.0335 1.0000
9.750 1.1318 0.05600 0.04555 -0.0408 0.0324 1.0000
10.000 1.1522 0.05974 0.04960 -0.0403 0.0318 1.0000
10.250 1.1657 0.06386 0.05401 -0.0394 0.0313 1.0000
10.500 1.1682 0.06756 0.05799 -0.0376 0.0309 1.0000
10.750 1.1608 0.07039 0.06119 -0.0347 0.0306 1.0000
11.000 1.1511 0.07342 0.06454 -0.0322 0.0304 1.0000
11.250 1.1390 0.07671 0.06814 -0.0303 0.0303 1.0000
11.500 1.1252 0.08032 0.07202 -0.0290 0.0301 1.0000
11.750 1.1103 0.08431 0.07628 -0.0285 0.0301 1.0000
12.000 1.0957 0.08863 0.08082 -0.0286 0.0302 1.0000
12.250 1.0787 0.09340 0.08581 -0.0294 0.0302 1.0000
12.500 1.0615 0.09857 0.09117 -0.0309 0.0302 1.0000
12.750 1.0460 0.10401 0.09677 -0.0329 0.0304 1.0000
13.000 1.0299 0.10990 0.10280 -0.0355 0.0306 1.0000
13.250 1.0148 0.11608 0.10910 -0.0385 0.0307 1.0000
13.500 1.0022 0.12240 0.11552 -0.0418 0.0309 1.0000
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Polar data table (+)
Polar graphs
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