GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 500,000 Max Cl/Cd: 117.88 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe06k-il-500000.txt Download as CSV file: xf-goe06k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 6K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4693 0.11067 0.10843 -0.0240 1.0000 0.0143
-9.250 -0.4731 0.10815 0.10594 -0.0237 1.0000 0.0145
-9.000 -0.4784 0.10566 0.10349 -0.0235 1.0000 0.0146
-8.750 -0.4702 0.10172 0.09955 -0.0276 0.9986 0.0148
-8.500 -0.4593 0.09745 0.09529 -0.0321 0.9966 0.0149
-8.250 -0.4482 0.09301 0.09084 -0.0371 0.9947 0.0149
-8.000 -0.4419 0.08884 0.08669 -0.0414 0.9910 0.0150
-7.750 -0.4334 0.08437 0.08221 -0.0471 0.9871 0.0150
-7.500 -0.4126 0.07818 0.07598 -0.0559 0.9846 0.0150
-7.250 -0.4023 0.07345 0.07121 -0.0600 0.9793 0.0151
-7.000 -0.3855 0.06779 0.06547 -0.0655 0.9756 0.0151
-6.750 -0.3766 0.05867 0.05623 -0.0723 0.9729 0.0156
-6.500 -0.3688 0.05500 0.05249 -0.0729 0.9681 0.0160
-6.250 -0.3537 0.05170 0.04911 -0.0742 0.9643 0.0166
-6.000 -0.3322 0.04787 0.04514 -0.0767 0.9621 0.0171
-5.750 -0.3079 0.04400 0.04110 -0.0792 0.9605 0.0180
-5.500 -0.2948 0.04079 0.03772 -0.0782 0.9555 0.0191
-5.250 -0.2643 0.03885 0.03543 -0.0777 0.9521 0.0227
-5.000 -0.2406 0.03543 0.03169 -0.0781 0.9498 0.0228
-4.750 -0.2265 0.02815 0.02389 -0.0779 0.9478 0.0239
-4.000 -0.1688 0.01989 0.01469 -0.0729 0.9378 0.0199
-3.750 -0.1420 0.01692 0.01124 -0.0721 0.9366 0.0193
-3.500 -0.1114 0.01542 0.00949 -0.0724 0.9357 0.0207
-3.250 -0.0786 0.01483 0.00875 -0.0734 0.9349 0.0225
-3.000 -0.0495 0.01310 0.00684 -0.0737 0.9343 0.0249
-2.750 -0.0358 0.01276 0.00647 -0.0706 0.9282 0.0269
-2.500 -0.0078 0.01228 0.00595 -0.0706 0.9261 0.0298
-2.250 0.0238 0.01201 0.00565 -0.0715 0.9247 0.0335
-2.000 0.0539 0.01132 0.00493 -0.0721 0.9235 0.0415
-1.750 0.0861 0.01086 0.00445 -0.0731 0.9226 0.0508
-1.500 0.1192 0.01050 0.00408 -0.0743 0.9219 0.0628
-1.250 0.1529 0.01015 0.00377 -0.0757 0.9213 0.0786
-1.000 0.1654 0.00998 0.00376 -0.0725 0.9148 0.1262
-0.750 0.1783 0.00838 0.00373 -0.0700 0.9118 0.6113
-0.500 0.3715 0.00800 0.00433 -0.1079 0.9346 1.0000
-0.250 0.3883 0.00800 0.00430 -0.1056 0.9286 1.0000
0.000 0.4199 0.00791 0.00418 -0.1066 0.9263 1.0000
0.250 0.4570 0.00778 0.00404 -0.1088 0.9248 1.0000
0.500 0.5010 0.00753 0.00379 -0.1124 0.9233 1.0000
0.750 0.5553 0.00709 0.00334 -0.1182 0.9209 1.0000
1.000 0.5786 0.00695 0.00321 -0.1170 0.9122 1.0000
1.250 0.6217 0.00674 0.00302 -0.1204 0.9082 1.0000
1.500 0.6511 0.00657 0.00285 -0.1206 0.8965 1.0000
1.750 0.6833 0.00639 0.00266 -0.1213 0.8813 1.0000
2.000 0.7078 0.00633 0.00258 -0.1203 0.8649 1.0000
2.250 0.7256 0.00628 0.00247 -0.1177 0.8354 1.0000
2.500 0.7438 0.00631 0.00241 -0.1152 0.7947 1.0000
2.750 0.7594 0.00651 0.00240 -0.1122 0.7402 1.0000
3.000 0.7610 0.00705 0.00249 -0.1062 0.6424 1.0000
3.250 0.7440 0.00822 0.00285 -0.0963 0.4772 1.0000
3.500 0.7391 0.00940 0.00330 -0.0896 0.3174 1.0000
3.750 0.7396 0.01061 0.00378 -0.0843 0.1602 1.0000
4.000 0.7494 0.01144 0.00420 -0.0808 0.0767 1.0000
4.250 0.7655 0.01193 0.00462 -0.0784 0.0522 1.0000
4.500 0.7817 0.01243 0.00504 -0.0760 0.0352 1.0000
4.750 0.7983 0.01293 0.00559 -0.0736 0.0291 1.0000
5.000 0.8145 0.01347 0.00613 -0.0712 0.0245 1.0000
5.250 0.8272 0.01428 0.00703 -0.0681 0.0217 1.0000
5.500 0.8441 0.01478 0.00758 -0.0658 0.0199 1.0000
5.750 0.8597 0.01548 0.00838 -0.0633 0.0185 1.0000
6.000 0.8766 0.01625 0.00920 -0.0611 0.0171 1.0000
6.250 0.8956 0.01730 0.01032 -0.0595 0.0159 1.0000
6.500 0.9291 0.02065 0.01388 -0.0610 0.0142 1.0000
6.750 0.9502 0.02120 0.01454 -0.0596 0.0137 1.0000
7.000 0.9761 0.02291 0.01646 -0.0592 0.0132 1.0000
7.250 1.0002 0.02509 0.01895 -0.0583 0.0126 1.0000
7.500 1.0194 0.02864 0.02292 -0.0563 0.0127 1.0000
7.750 1.0333 0.03325 0.02785 -0.0535 0.0150 1.0000
8.000 1.0226 0.04247 0.03804 -0.0443 0.0205 1.0000
8.250 1.0287 0.04487 0.04071 -0.0403 0.0191 1.0000
8.500 1.0304 0.04754 0.04361 -0.0361 0.0179 1.0000
8.750 1.0313 0.04989 0.04614 -0.0323 0.0171 1.0000
9.000 1.0321 0.05170 0.04807 -0.0289 0.0163 1.0000
9.250 1.0317 0.05338 0.04982 -0.0256 0.0158 1.0000
9.500 1.0274 0.05561 0.05215 -0.0219 0.0154 1.0000
9.750 1.0148 0.05857 0.05529 -0.0167 0.0154 1.0000
10.000 0.9982 0.06103 0.05786 -0.0116 0.0151 1.0000
10.250 0.9800 0.06399 0.06095 -0.0071 0.0150 1.0000
10.500 0.9565 0.06767 0.06477 -0.0032 0.0148 1.0000
10.750 0.9321 0.07180 0.06903 -0.0005 0.0147 1.0000
11.000 0.9157 0.07542 0.07278 0.0009 0.0148 1.0000
11.250 0.8983 0.07961 0.07708 0.0011 0.0148 1.0000
11.500 0.8746 0.08547 0.08305 -0.0005 0.0147 1.0000
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Polar data table (+)
Polar graphs
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