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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)
Reynolds number: 500,000
Max Cl/Cd: 99.1 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe207-il-500000.txt
Download as CSV file: xf-goe207-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 207 (AVIATIK V8) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2290   0.09368   0.09129  -0.0207   0.8299   0.0203
  -7.250  -0.2198   0.09015   0.08766  -0.0195   0.8044   0.0204
  -7.000  -0.2089   0.08715   0.08455  -0.0203   0.7795   0.0206
  -6.750  -0.1964   0.08435   0.08164  -0.0220   0.7563   0.0208
  -6.500  -0.1818   0.08159   0.07879  -0.0245   0.7346   0.0210
  -6.250  -0.1654   0.07878   0.07588  -0.0275   0.7137   0.0214
  -6.000  -0.1473   0.07587   0.07287  -0.0309   0.6936   0.0218
  -5.750  -0.1273   0.07289   0.06978  -0.0345   0.6737   0.0223
  -5.500  -0.1052   0.06985   0.06663  -0.0385   0.6546   0.0229
  -5.250  -0.0728   0.06676   0.06339  -0.0454   0.6361   0.0236
  -5.000  -0.0348   0.06370   0.06013  -0.0537   0.6184   0.0237
  -4.750  -0.0026   0.06034   0.05660  -0.0591   0.6021   0.0238
  -4.250   0.0310   0.05431   0.05044  -0.0599   0.5733   0.0241
  -4.000   0.0553   0.05179   0.04783  -0.0620   0.5614   0.0244
  -3.750   0.0823   0.04939   0.04531  -0.0645   0.5508   0.0248
  -3.500   0.1113   0.04701   0.04282  -0.0672   0.5408   0.0253
  -3.250   0.1420   0.04463   0.04033  -0.0700   0.5316   0.0261
  -3.000   0.1785   0.04240   0.03791  -0.0732   0.5223   0.0274
  -2.750   0.2252   0.04049   0.03570  -0.0773   0.5137   0.0277
  -2.500   0.2510   0.03747   0.03258  -0.0790   0.5052   0.0280
  -2.250   0.2759   0.03538   0.03044  -0.0801   0.4970   0.0283
  -2.000   0.3040   0.03362   0.02857  -0.0814   0.4887   0.0286
  -1.750   0.3342   0.03195   0.02680  -0.0828   0.4805   0.0292
  -1.500   0.3653   0.03037   0.02508  -0.0841   0.4720   0.0300
  -1.250   0.3993   0.02885   0.02340  -0.0853   0.4638   0.0317
  -1.000   0.4379   0.02696   0.02117  -0.0866   0.4555   0.0327
  -0.750   0.4654   0.02544   0.01960  -0.0876   0.4465   0.0332
  -0.500   0.4943   0.02431   0.01835  -0.0884   0.4372   0.0340
  -0.250   0.5249   0.02322   0.01714  -0.0892   0.4273   0.0353
   0.000   0.5616   0.02228   0.01583  -0.0892   0.4182   0.0382
   0.250   0.5898   0.02089   0.01437  -0.0903   0.4077   0.0389
   0.500   0.6188   0.02005   0.01344  -0.0909   0.3978   0.0399
   0.750   0.6486   0.01934   0.01257  -0.0913   0.3882   0.0417
   1.000   0.6813   0.01842   0.01137  -0.0914   0.3793   0.0453
   1.250   0.7098   0.01773   0.01061  -0.0919   0.3705   0.0466
   1.500   0.7392   0.01730   0.01006  -0.0922   0.3619   0.0504
   1.750   0.7692   0.01660   0.00917  -0.0924   0.3544   0.0543
   2.000   0.7979   0.01621   0.00871  -0.0927   0.3468   0.0576
   2.250   0.8273   0.01582   0.00813  -0.0927   0.3396   0.0635
   2.500   0.8558   0.01549   0.00777  -0.0930   0.3325   0.0681
   2.750   0.8845   0.01521   0.00731  -0.0930   0.3256   0.0742
   3.000   0.9133   0.01482   0.00692  -0.0931   0.3198   0.0774
   3.250   0.9419   0.01454   0.00654  -0.0931   0.3143   0.0784
   3.500   0.9723   0.01334   0.00503  -0.0925   0.3096   0.0435
   3.750   1.0009   0.01324   0.00494  -0.0926   0.3054   0.0448
   4.000   1.0292   0.01317   0.00489  -0.0928   0.3009   0.0472
   4.250   1.0570   0.01326   0.00495  -0.0929   0.2966   0.0492
   4.500   1.0849   0.01337   0.00504  -0.0930   0.2927   0.0523
   4.750   1.1131   0.01340   0.00513  -0.0931   0.2889   0.0605
   5.000   1.1413   0.01342   0.00527  -0.0933   0.2851   0.1335
   5.250   1.1620   0.01228   0.00551  -0.0921   0.2807   1.0000
   5.500   1.1895   0.01246   0.00566  -0.0921   0.2761   1.0000
   5.750   1.2169   0.01263   0.00580  -0.0922   0.2716   1.0000
   6.000   1.2439   0.01286   0.00599  -0.0921   0.2671   1.0000
   6.250   1.2705   0.01313   0.00622  -0.0921   0.2626   1.0000
   6.500   1.2979   0.01327   0.00638  -0.0921   0.2583   1.0000
   6.750   1.3246   0.01349   0.00657  -0.0921   0.2527   1.0000
   7.000   1.3508   0.01376   0.00681  -0.0921   0.2474   1.0000
   7.250   1.3778   0.01392   0.00700  -0.0921   0.2420   1.0000
   7.500   1.4036   0.01422   0.00726  -0.0920   0.2352   1.0000
   7.750   1.4300   0.01443   0.00747  -0.0919   0.2268   1.0000
   8.000   1.4553   0.01477   0.00775  -0.0918   0.2140   1.0000
   8.250   1.4785   0.01536   0.00816  -0.0915   0.1861   1.0000
   8.500   1.4852   0.01798   0.01013  -0.0894   0.0927   1.0000
   9.000   1.5140   0.02084   0.01279  -0.0865   0.0303   1.0000
   9.250   1.5318   0.02175   0.01379  -0.0854   0.0278   1.0000
   9.500   1.5500   0.02253   0.01466  -0.0843   0.0267   1.0000
   9.750   1.5665   0.02340   0.01563  -0.0830   0.0256   1.0000
  10.000   1.5800   0.02442   0.01675  -0.0814   0.0246   1.0000
  10.250   1.5885   0.02568   0.01811  -0.0793   0.0237   1.0000
  10.500   1.5871   0.02733   0.01987  -0.0759   0.0229   1.0000
  10.750   1.5800   0.02969   0.02239  -0.0729   0.0224   1.0000
  11.000   1.5847   0.03149   0.02429  -0.0717   0.0220   1.0000
  11.250   1.5858   0.03391   0.02684  -0.0709   0.0216   1.0000
  11.500   1.5842   0.03692   0.02999  -0.0706   0.0213   1.0000
  11.750   1.5801   0.04056   0.03376  -0.0709   0.0209   1.0000
  12.000   1.5731   0.04478   0.03812  -0.0716   0.0206   1.0000
  12.250   1.5634   0.04959   0.04307  -0.0726   0.0204   1.0000
  12.500   1.5508   0.05486   0.04848  -0.0737   0.0202   1.0000
  12.750   1.5360   0.06048   0.05424  -0.0749   0.0201   1.0000
  13.000   1.5195   0.06628   0.06017  -0.0761   0.0200   1.0000
  13.250   1.5020   0.07221   0.06623  -0.0772   0.0199   1.0000
  13.500   1.4843   0.07819   0.07233  -0.0783   0.0198   1.0000
  13.750   1.4683   0.08412   0.07837  -0.0796   0.0197   1.0000
  14.000   1.4538   0.08989   0.08424  -0.0809   0.0196   1.0000
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