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GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
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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