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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.87 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe286-il-1000000-n5.txt
Download as CSV file: xf-goe286-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 286 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4483   0.09149   0.08994  -0.0127   0.9787   0.0106
  -9.000  -0.4451   0.08789   0.08632  -0.0147   0.9626   0.0109
  -8.500  -0.4650   0.07295   0.07134  -0.0276   0.9369   0.0126
  -8.250  -0.4539   0.06966   0.06800  -0.0310   0.9158   0.0128
  -8.000  -0.4429   0.06651   0.06467  -0.0339   0.8655   0.0129
  -7.500  -0.4261   0.03954   0.03705  -0.0582   0.8375   0.0160
  -7.250  -0.4040   0.03747   0.03475  -0.0590   0.8091   0.0162
  -7.000  -0.3995   0.01992   0.01588  -0.0631   0.8089   0.0190
  -6.750  -0.3742   0.01865   0.01424  -0.0630   0.7824   0.0194
  -6.500  -0.3489   0.01734   0.01258  -0.0630   0.7485   0.0197
  -6.250  -0.3233   0.01635   0.01122  -0.0630   0.6841   0.0200
  -6.000  -0.2963   0.01592   0.01055  -0.0630   0.6452   0.0202
  -5.750  -0.2686   0.01563   0.01012  -0.0631   0.6270   0.0205
  -5.500  -0.2408   0.01529   0.00967  -0.0631   0.6146   0.0207
  -5.250  -0.2130   0.01479   0.00904  -0.0632   0.6059   0.0210
  -5.000  -0.1851   0.01421   0.00832  -0.0632   0.5979   0.0212
  -4.750  -0.1571   0.01367   0.00767  -0.0633   0.5910   0.0215
  -4.500  -0.1290   0.01313   0.00701  -0.0633   0.5831   0.0217
  -4.250  -0.1007   0.01266   0.00642  -0.0634   0.5756   0.0220
  -4.000  -0.0724   0.01220   0.00587  -0.0634   0.5679   0.0223
  -3.750  -0.0440   0.01184   0.00540  -0.0635   0.5548   0.0226
  -3.500  -0.0156   0.01157   0.00501  -0.0635   0.5364   0.0231
  -3.250   0.0128   0.01128   0.00459  -0.0636   0.5138   0.0233
  -3.000   0.0409   0.01112   0.00423  -0.0637   0.4729   0.0236
  -2.750   0.0690   0.01105   0.00396  -0.0637   0.4306   0.0238
  -2.500   0.0972   0.01097   0.00372  -0.0638   0.4019   0.0240
  -2.250   0.1256   0.01087   0.00352  -0.0639   0.3823   0.0242
  -2.000   0.1541   0.01077   0.00333  -0.0640   0.3652   0.0243
  -1.750   0.1824   0.01060   0.00306  -0.0640   0.3477   0.0245
  -1.500   0.2106   0.01037   0.00272  -0.0641   0.3298   0.0249
  -1.250   0.2390   0.01024   0.00251  -0.0642   0.3129   0.0252
  -1.000   0.2674   0.01016   0.00235  -0.0643   0.2977   0.0255
  -0.750   0.2958   0.01014   0.00224  -0.0644   0.2782   0.0259
  -0.500   0.3241   0.01017   0.00216  -0.0645   0.2560   0.0264
  -0.250   0.3522   0.01026   0.00213  -0.0646   0.2291   0.0270
   0.000   0.3786   0.01085   0.00231  -0.0647   0.1241   0.0275
   0.250   0.4070   0.01087   0.00229  -0.0647   0.1184   0.0281
   0.500   0.4354   0.01090   0.00229  -0.0648   0.1131   0.0287
   0.750   0.4638   0.01092   0.00229  -0.0649   0.1099   0.0293
   1.000   0.4922   0.01095   0.00230  -0.0649   0.1085   0.0299
   1.250   0.5206   0.01098   0.00232  -0.0650   0.1080   0.0303
   1.500   0.5490   0.01101   0.00235  -0.0651   0.1072   0.0311
   1.750   0.5773   0.01106   0.00238  -0.0652   0.1060   0.0326
   2.000   0.6055   0.01111   0.00245  -0.0652   0.1047   0.0352
   2.250   0.6337   0.01113   0.00253  -0.0653   0.1035   0.0675
   2.500   0.6618   0.01108   0.00264  -0.0655   0.1025   0.1402
   2.750   0.6895   0.01063   0.00282  -0.0658   0.1013   0.4256
   3.250   0.7415   0.00955   0.00310  -0.0652   0.0988   1.0000
   3.750   0.7971   0.00988   0.00337  -0.0653   0.0958   1.0000
   4.000   0.8249   0.01001   0.00348  -0.0653   0.0952   1.0000
   4.250   0.8527   0.01014   0.00359  -0.0653   0.0945   1.0000
   4.500   0.8805   0.01028   0.00372  -0.0654   0.0932   1.0000
   4.750   0.9081   0.01043   0.00385  -0.0654   0.0906   1.0000
   5.000   0.9354   0.01063   0.00400  -0.0654   0.0844   1.0000
   5.250   0.9614   0.01104   0.00425  -0.0653   0.0580   1.0000
   5.500   0.9882   0.01130   0.00449  -0.0652   0.0550   1.0000
   5.750   1.0150   0.01154   0.00472  -0.0651   0.0527   1.0000
   6.000   1.0419   0.01177   0.00495  -0.0650   0.0509   1.0000
   6.250   1.0686   0.01199   0.00519  -0.0650   0.0497   1.0000
   6.500   1.0952   0.01223   0.00544  -0.0649   0.0485   1.0000
   6.750   1.1216   0.01249   0.00571  -0.0648   0.0472   1.0000
   7.000   1.1477   0.01277   0.00599  -0.0646   0.0459   1.0000
   7.250   1.1734   0.01308   0.00632  -0.0644   0.0443   1.0000
   7.500   1.1989   0.01342   0.00667  -0.0642   0.0426   1.0000
   7.750   1.2247   0.01369   0.00696  -0.0640   0.0418   1.0000
   8.000   1.2505   0.01393   0.00722  -0.0639   0.0407   1.0000
   8.250   1.2759   0.01422   0.00751  -0.0637   0.0383   1.0000
   8.500   1.3005   0.01459   0.00787  -0.0634   0.0350   1.0000
   8.750   1.3241   0.01504   0.00824  -0.0630   0.0224   1.0000
   9.000   1.3456   0.01572   0.00887  -0.0623   0.0139   1.0000
   9.250   1.3682   0.01625   0.00942  -0.0617   0.0118   1.0000
   9.500   1.3911   0.01670   0.00992  -0.0611   0.0107   1.0000
   9.750   1.4136   0.01717   0.01042  -0.0605   0.0099   1.0000
  10.000   1.4352   0.01769   0.01098  -0.0598   0.0091   1.0000
  10.250   1.4556   0.01830   0.01162  -0.0590   0.0084   1.0000
  10.500   1.4762   0.01885   0.01222  -0.0581   0.0080   1.0000
  10.750   1.4962   0.01940   0.01282  -0.0573   0.0077   1.0000
  11.000   1.5153   0.02000   0.01346  -0.0562   0.0073   1.0000
  11.250   1.5332   0.02064   0.01415  -0.0551   0.0069   1.0000
  11.500   1.5495   0.02134   0.01489  -0.0537   0.0065   1.0000
  11.750   1.5627   0.02215   0.01576  -0.0519   0.0061   1.0000
  12.000   1.5716   0.02303   0.01671  -0.0494   0.0059   1.0000
  12.250   1.5820   0.02388   0.01763  -0.0474   0.0057   1.0000
  12.500   1.5916   0.02486   0.01868  -0.0455   0.0056   1.0000
  12.750   1.6006   0.02596   0.01985  -0.0437   0.0054   1.0000
  13.000   1.6085   0.02721   0.02118  -0.0421   0.0053   1.0000
  13.250   1.6155   0.02863   0.02268  -0.0406   0.0051   1.0000
  13.500   1.6217   0.03024   0.02437  -0.0394   0.0050   1.0000
  13.750   1.6267   0.03207   0.02628  -0.0384   0.0048   1.0000
  14.000   1.6305   0.03414   0.02844  -0.0377   0.0047   1.0000
  14.250   1.6329   0.03648   0.03087  -0.0372   0.0046   1.0000
  14.500   1.6337   0.03914   0.03363  -0.0369   0.0045   1.0000
  14.750   1.6326   0.04222   0.03680  -0.0370   0.0044   1.0000
  15.000   1.6289   0.04576   0.04045  -0.0375   0.0043   1.0000
  15.250   1.6228   0.04975   0.04456  -0.0382   0.0042   1.0000
  15.500   1.6131   0.05424   0.04917  -0.0390   0.0042   1.0000
  15.750   1.6009   0.05910   0.05416  -0.0400   0.0041   1.0000
  16.000   1.5911   0.06375   0.05892  -0.0411   0.0041   1.0000
  16.250   1.5799   0.06869   0.06398  -0.0424   0.0040   1.0000
  16.500   1.5686   0.07383   0.06924  -0.0438   0.0040   1.0000
  16.750   1.5563   0.07925   0.07477  -0.0455   0.0040   1.0000
  17.000   1.5422   0.08500   0.08064  -0.0473   0.0040   1.0000
  17.250   1.5291   0.09070   0.08644  -0.0492   0.0039   1.0000
  17.500   1.5152   0.09659   0.09245  -0.0512   0.0039   1.0000
  17.750   1.5004   0.10265   0.09862  -0.0533   0.0039   1.0000
  18.000   1.4863   0.10871   0.10478  -0.0556   0.0039   1.0000
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