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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 500,000
Max Cl/Cd: 93.93 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe385-il-500000-n5.txt
Download as CSV file: xf-goe385-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3846   0.10022   0.09803  -0.0193   1.0000   0.0084
  -9.250  -0.3841   0.09548   0.09331  -0.0217   1.0000   0.0085
  -9.000  -0.3839   0.09087   0.08873  -0.0242   1.0000   0.0087
  -8.750  -0.3784   0.08790   0.08579  -0.0260   1.0000   0.0089
  -8.500  -0.3714   0.08524   0.08315  -0.0278   0.9971   0.0091
  -8.250  -0.3588   0.08178   0.07970  -0.0318   0.9770   0.0094
  -8.000  -0.3505   0.07792   0.07583  -0.0360   0.9578   0.0098
  -7.750  -0.3429   0.07317   0.07106  -0.0414   0.9376   0.0101
  -7.500  -0.3349   0.06757   0.06539  -0.0475   0.9122   0.0104
  -7.250  -0.3260   0.06081   0.05848  -0.0541   0.8814   0.0108
  -7.000  -0.3175   0.04908   0.04641  -0.0637   0.8582   0.0116
  -6.750  -0.2979   0.04663   0.04378  -0.0651   0.8411   0.0119
  -6.500  -0.2768   0.04429   0.04126  -0.0664   0.8274   0.0124
  -6.000  -0.2376   0.02951   0.02550  -0.0709   0.8072   0.0154
  -5.750  -0.2127   0.02859   0.02444  -0.0711   0.7964   0.0158
  -5.500  -0.1875   0.02756   0.02326  -0.0713   0.7857   0.0166
  -5.250  -0.1651   0.02019   0.01492  -0.0710   0.7767   0.0199
  -5.000  -0.1385   0.01985   0.01450  -0.0711   0.7647   0.0204
  -4.750  -0.1117   0.01960   0.01417  -0.0712   0.7514   0.0210
  -4.500  -0.0848   0.01913   0.01355  -0.0712   0.7366   0.0217
  -4.250  -0.0579   0.01804   0.01222  -0.0712   0.7203   0.0227
  -3.750  -0.0032   0.01626   0.00989  -0.0709   0.6855   0.0249
  -3.500   0.0243   0.01562   0.00899  -0.0708   0.6685   0.0255
  -3.250   0.0519   0.01520   0.00835  -0.0707   0.6519   0.0258
  -3.000   0.0787   0.01384   0.00674  -0.0706   0.6375   0.0269
  -2.750   0.1062   0.01329   0.00606  -0.0706   0.6256   0.0276
  -2.500   0.1340   0.01282   0.00550  -0.0707   0.6166   0.0281
  -2.250   0.1620   0.01242   0.00501  -0.0707   0.6099   0.0287
  -2.000   0.1900   0.01204   0.00457  -0.0707   0.6029   0.0291
  -1.750   0.2180   0.01171   0.00417  -0.0707   0.5966   0.0296
  -1.500   0.2462   0.01139   0.00381  -0.0708   0.5898   0.0300
  -1.000   0.3025   0.01092   0.00325  -0.0709   0.5766   0.0314
  -0.750   0.3306   0.01070   0.00299  -0.0710   0.5698   0.0319
  -0.500   0.3589   0.01049   0.00274  -0.0711   0.5634   0.0323
  -0.250   0.3872   0.01032   0.00254  -0.0712   0.5562   0.0328
   0.000   0.4156   0.01018   0.00237  -0.0713   0.5490   0.0334
   0.250   0.4439   0.01009   0.00224  -0.0714   0.5399   0.0341
   0.500   0.4723   0.01001   0.00213  -0.0715   0.5296   0.0347
   0.750   0.5005   0.00998   0.00206  -0.0716   0.5176   0.0351
   1.000   0.5287   0.00993   0.00194  -0.0717   0.5051   0.0364
   1.250   0.5568   0.00993   0.00188  -0.0718   0.4927   0.0382
   1.500   0.5848   0.00995   0.00186  -0.0718   0.4783   0.0416
   1.750   0.6127   0.01001   0.00187  -0.0719   0.4617   0.0454
   2.000   0.6385   0.00884   0.00202  -0.0725   0.4440   0.6029
   2.250   0.6634   0.00805   0.00210  -0.0715   0.4250   1.0000
   2.750   0.7175   0.00849   0.00229  -0.0714   0.3865   1.0000
   3.000   0.7446   0.00871   0.00241  -0.0714   0.3693   1.0000
   3.250   0.7717   0.00893   0.00254  -0.0714   0.3551   1.0000
   3.500   0.7988   0.00914   0.00268  -0.0714   0.3431   1.0000
   3.750   0.8255   0.00939   0.00284  -0.0713   0.3283   1.0000
   4.000   0.8522   0.00964   0.00301  -0.0713   0.3137   1.0000
   4.500   0.9061   0.01006   0.00336  -0.0712   0.2942   1.0000
   4.750   0.9328   0.01029   0.00355  -0.0712   0.2867   1.0000
   5.000   0.9599   0.01046   0.00373  -0.0712   0.2805   1.0000
   5.250   0.9866   0.01068   0.00394  -0.0711   0.2739   1.0000
   5.500   1.0134   0.01087   0.00414  -0.0711   0.2683   1.0000
   5.750   1.0400   0.01108   0.00435  -0.0711   0.2616   1.0000
   6.000   1.0661   0.01135   0.00459  -0.0710   0.2508   1.0000
   6.250   1.0913   0.01169   0.00487  -0.0708   0.2326   1.0000
   6.500   1.1163   0.01205   0.00516  -0.0705   0.2155   1.0000
   6.750   1.1408   0.01246   0.00548  -0.0702   0.1965   1.0000
   7.000   1.1635   0.01305   0.00591  -0.0697   0.1609   1.0000
   7.250   1.1831   0.01396   0.00657  -0.0689   0.1211   1.0000
   7.500   1.2054   0.01455   0.00709  -0.0683   0.1062   1.0000
   7.750   1.2275   0.01513   0.00761  -0.0677   0.0875   1.0000
   8.000   1.2453   0.01612   0.00840  -0.0665   0.0529   1.0000
   8.250   1.2660   0.01678   0.00904  -0.0657   0.0409   1.0000
   8.500   1.2820   0.01784   0.00996  -0.0642   0.0168   1.0000
   8.750   1.3025   0.01845   0.01061  -0.0633   0.0140   1.0000
   9.000   1.3215   0.01914   0.01137  -0.0622   0.0123   1.0000
   9.250   1.3398   0.01984   0.01217  -0.0611   0.0110   1.0000
   9.500   1.3584   0.02047   0.01287  -0.0599   0.0102   1.0000
   9.750   1.3752   0.02118   0.01366  -0.0586   0.0094   1.0000
  10.000   1.3899   0.02197   0.01453  -0.0570   0.0088   1.0000
  10.250   1.3995   0.02291   0.01555  -0.0545   0.0083   1.0000
  10.500   1.4063   0.02408   0.01682  -0.0519   0.0079   1.0000
  10.750   1.4165   0.02509   0.01792  -0.0500   0.0077   1.0000
  11.000   1.4253   0.02624   0.01919  -0.0482   0.0074   1.0000
  11.250   1.4331   0.02755   0.02060  -0.0464   0.0071   1.0000
  11.500   1.4400   0.02902   0.02216  -0.0449   0.0068   1.0000
  11.750   1.4462   0.03065   0.02388  -0.0436   0.0065   1.0000
  12.000   1.4516   0.03246   0.02578  -0.0425   0.0062   1.0000
  12.250   1.4553   0.03453   0.02795  -0.0416   0.0060   1.0000
  12.500   1.4556   0.03706   0.03058  -0.0409   0.0058   1.0000
  12.750   1.4518   0.04017   0.03381  -0.0403   0.0056   1.0000
  13.000   1.4475   0.04352   0.03728  -0.0401   0.0055   1.0000
  13.250   1.4463   0.04665   0.04056  -0.0401   0.0054   1.0000
  13.500   1.4437   0.05005   0.04408  -0.0404   0.0054   1.0000
  13.750   1.4393   0.05372   0.04787  -0.0407   0.0053   1.0000
  14.000   1.4337   0.05760   0.05188  -0.0411   0.0052   1.0000
  14.250   1.4266   0.06171   0.05611  -0.0417   0.0051   1.0000
  14.500   1.4190   0.06602   0.06054  -0.0424   0.0050   1.0000
  14.750   1.4114   0.07048   0.06513  -0.0433   0.0050   1.0000
  15.000   1.4033   0.07510   0.06986  -0.0444   0.0049   1.0000
  15.250   1.3949   0.07986   0.07474  -0.0456   0.0048   1.0000
  15.500   1.3867   0.08473   0.07973  -0.0469   0.0047   1.0000
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