GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 770 AIRFOIL (goe770-il) Reynolds number: 50,000 Max Cl/Cd: 11.34 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe770-il-50000-n5.txt Download as CSV file: xf-goe770-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 770 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5286 0.08357 0.07589 -0.0646 1.0000 0.0893
-12.750 -0.5767 0.07462 0.06675 -0.0701 1.0000 0.0891
-12.500 -0.6145 0.06842 0.06034 -0.0728 1.0000 0.0891
-12.250 -0.6457 0.06395 0.05568 -0.0735 1.0000 0.0893
-12.000 -0.6745 0.06088 0.05247 -0.0720 1.0000 0.0896
-11.750 -0.6565 0.05878 0.05044 -0.0736 0.9719 0.0913
-11.500 -0.6390 0.05599 0.04748 -0.0762 0.9347 0.0933
-11.250 -0.6310 0.05316 0.04433 -0.0772 0.9037 0.0952
-11.000 -0.6243 0.05053 0.04129 -0.0772 0.8793 0.0969
-10.750 -0.6196 0.04822 0.03849 -0.0762 0.8588 0.0988
-10.500 -0.5976 0.04666 0.03688 -0.0761 0.8419 0.1013
-10.250 -0.5797 0.04523 0.03527 -0.0753 0.8274 0.1041
-10.000 -0.5648 0.04374 0.03350 -0.0743 0.8135 0.1071
-9.750 -0.5487 0.04230 0.03175 -0.0732 0.8013 0.1101
-9.500 -0.5244 0.04118 0.03064 -0.0728 0.7903 0.1136
-9.250 -0.5038 0.04008 0.02939 -0.0721 0.7798 0.1178
-9.000 -0.4819 0.03899 0.02812 -0.0714 0.7704 0.1222
-8.750 -0.4586 0.03808 0.02723 -0.0709 0.7619 0.1272
-8.500 -0.4370 0.03720 0.02616 -0.0702 0.7530 0.1330
-8.250 -0.4153 0.03634 0.02536 -0.0693 0.7458 0.1390
-8.000 -0.3949 0.03559 0.02449 -0.0685 0.7377 0.1464
-7.750 -0.3770 0.03480 0.02381 -0.0674 0.7303 0.1538
-7.500 -0.3594 0.03402 0.02301 -0.0661 0.7244 0.1632
-7.250 -0.3432 0.03335 0.02237 -0.0650 0.7175 0.1744
-7.000 -0.3288 0.03266 0.02182 -0.0636 0.7106 0.1879
-6.750 -0.3141 0.03196 0.02124 -0.0620 0.7049 0.2066
-6.500 -0.3002 0.03130 0.02073 -0.0603 0.6996 0.2337
-6.250 -0.2868 0.03078 0.02036 -0.0587 0.6928 0.2702
-6.000 -0.2722 0.03023 0.01995 -0.0570 0.6870 0.3111
-5.750 -0.2559 0.02980 0.01976 -0.0551 0.6821 0.3523
-5.500 -0.2383 0.02980 0.02001 -0.0532 0.6768 0.3931
-5.250 -0.2208 0.03006 0.02040 -0.0514 0.6702 0.4314
-5.000 -0.2013 0.03027 0.02057 -0.0498 0.6646 0.4653
-4.750 -0.1803 0.03040 0.02057 -0.0482 0.6601 0.4959
-4.500 -0.1603 0.03076 0.02089 -0.0465 0.6549 0.5236
-4.250 -0.1428 0.03124 0.02139 -0.0447 0.6482 0.5497
-4.000 -0.1225 0.03158 0.02168 -0.0428 0.6427 0.5749
-3.750 -0.0993 0.03184 0.02184 -0.0411 0.6383 0.5983
-3.500 -0.0768 0.03219 0.02215 -0.0395 0.6334 0.6182
-3.250 -0.0586 0.03266 0.02263 -0.0380 0.6262 0.6349
-3.000 -0.0375 0.03279 0.02265 -0.0367 0.6208 0.6511
-2.750 -0.0105 0.03284 0.02257 -0.0359 0.6164 0.6638
-2.500 0.0116 0.03300 0.02263 -0.0349 0.6112 0.6760
-2.250 0.0284 0.03347 0.02310 -0.0337 0.6038 0.6880
-2.000 0.0517 0.03361 0.02315 -0.0328 0.5985 0.6995
-1.750 0.0785 0.03357 0.02296 -0.0322 0.5943 0.7116
-1.500 0.0981 0.03395 0.02332 -0.0312 0.5883 0.7223
-1.250 0.1131 0.03450 0.02387 -0.0298 0.5811 0.7336
-1.000 0.1369 0.03464 0.02393 -0.0290 0.5761 0.7447
-0.750 0.1643 0.03460 0.02377 -0.0283 0.5724 0.7578
-0.500 0.1765 0.03545 0.02469 -0.0266 0.5651 0.7705
-0.250 0.1905 0.03602 0.02526 -0.0249 0.5584 0.7856
0.000 0.2179 0.03617 0.02536 -0.0243 0.5540 0.7986
0.250 0.2488 0.03608 0.02517 -0.0241 0.5508 0.8126
0.500 0.2464 0.03759 0.02680 -0.0215 0.5413 0.8283
0.750 0.2712 0.03805 0.02726 -0.0213 0.5359 0.8408
1.000 0.3019 0.03805 0.02718 -0.0216 0.5322 0.8544
1.250 0.3406 0.03787 0.02688 -0.0228 0.5296 0.8669
1.500 0.3316 0.04036 0.02958 -0.0208 0.5177 0.8845
1.750 0.3670 0.04054 0.02970 -0.0223 0.5137 0.8985
2.000 0.4080 0.04044 0.02949 -0.0243 0.5109 0.9130
2.500 0.4482 0.04403 0.03319 -0.0281 0.4953 0.9509
2.750 0.4982 0.04395 0.03302 -0.0318 0.4925 0.9659
3.250 0.4887 0.04875 0.03782 -0.0310 0.4762 1.0000
3.500 0.5010 0.04892 0.03784 -0.0292 0.4736 1.0000
4.000 0.4560 0.05544 0.04423 -0.0239 0.4567 1.0000
4.250 0.4825 0.05555 0.04423 -0.0236 0.4547 1.0000
4.750 0.4567 0.06281 0.05143 -0.0219 0.4399 1.0000
5.000 0.4798 0.06346 0.05200 -0.0217 0.4376 1.0000
5.500 0.4668 0.07008 0.05859 -0.0210 0.4248 1.0000
5.750 0.4838 0.07145 0.05991 -0.0209 0.4220 1.0000
6.000 0.5047 0.07250 0.06091 -0.0208 0.4199 1.0000
6.250 0.4888 0.07692 0.06535 -0.0207 0.4135 1.0000
6.500 0.4919 0.07954 0.06796 -0.0207 0.4087 1.0000
6.750 0.5073 0.08111 0.06950 -0.0207 0.4055 1.0000
7.000 0.5266 0.08241 0.07078 -0.0206 0.4034 1.0000
7.250 0.5498 0.08339 0.07173 -0.0206 0.4017 1.0000
7.500 0.5201 0.08915 0.07755 -0.0210 0.3939 1.0000
7.750 0.5309 0.09120 0.07960 -0.0210 0.3902 1.0000
8.000 0.5480 0.09275 0.08114 -0.0211 0.3876 1.0000
8.250 0.5705 0.09381 0.08219 -0.0210 0.3855 1.0000
8.500 0.5541 0.09837 0.08680 -0.0215 0.3790 1.0000
8.750 0.5603 0.10085 0.08930 -0.0217 0.3745 1.0000
9.000 0.5769 0.10241 0.09086 -0.0217 0.3712 1.0000
9.250 0.6006 0.10333 0.09178 -0.0216 0.3688 1.0000
9.750 0.5954 0.10981 0.09834 -0.0223 0.3570 1.0000
10.000 0.6155 0.11098 0.09952 -0.0223 0.3535 1.0000
10.250 0.6422 0.11153 0.10008 -0.0221 0.3511 1.0000
10.500 0.6199 0.11656 0.10518 -0.0230 0.3423 1.0000
10.750 0.6354 0.11812 0.10677 -0.0231 0.3380 1.0000
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Polar data table (+)
Polar graphs
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