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GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 269 AIRFOIL (goe269-il)
Reynolds number: 200,000
Max Cl/Cd: 80.2 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe269-il-200000.txt
Download as CSV file: xf-goe269-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 269 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3719   0.11219   0.10858  -0.0100   1.0000   0.0378
  -8.750  -0.3721   0.11092   0.10736  -0.0142   1.0000   0.0382
  -8.500  -0.3733   0.10929   0.10579  -0.0182   1.0000   0.0383
  -8.250  -0.3564   0.10231   0.09880  -0.0151   1.0000   0.0389
  -8.000  -0.3458   0.09872   0.09522  -0.0145   1.0000   0.0398
  -7.750  -0.3384   0.09587   0.09240  -0.0152   1.0000   0.0407
  -7.500  -0.3323   0.09316   0.08973  -0.0161   1.0000   0.0417
  -7.250  -0.3259   0.09044   0.08704  -0.0176   1.0000   0.0428
  -7.000  -0.3167   0.08759   0.08422  -0.0205   1.0000   0.0444
  -6.750  -0.3004   0.08587   0.08253  -0.0315   1.0000   0.0460
  -6.500  -0.2817   0.08345   0.08007  -0.0408   1.0000   0.0464
  -6.250  -0.2866   0.07875   0.07548  -0.0348   1.0000   0.0469
  -6.000  -0.2877   0.07615   0.07294  -0.0305   1.0000   0.0474
  -5.750  -0.2892   0.07423   0.07107  -0.0280   1.0000   0.0481
  -5.500  -0.2839   0.07205   0.06893  -0.0279   0.9991   0.0489
  -5.250  -0.2446   0.06773   0.06454  -0.0358   0.9943   0.0513
  -5.000  -0.1071   0.04348   0.04028  -0.0619   0.9692   0.0572
  -4.750  -0.0803   0.03953   0.03631  -0.0645   0.9609   0.0587
  -4.500  -0.0456   0.03547   0.03217  -0.0697   0.9533   0.0611
  -4.250   0.0196   0.03223   0.02840  -0.0834   0.9431   0.0669
  -4.000   0.0393   0.02701   0.02320  -0.0851   0.9320   0.0679
  -3.750   0.0599   0.02408   0.02028  -0.0854   0.9195   0.0691
  -3.500   0.0835   0.02171   0.01784  -0.0862   0.9068   0.0709
  -3.250   0.1097   0.01953   0.01551  -0.0874   0.8945   0.0739
  -3.000   0.1527   0.01788   0.01322  -0.0911   0.8812   0.0797
  -2.750   0.1712   0.01514   0.01056  -0.0914   0.8693   0.0812
  -2.500   0.1931   0.01369   0.00909  -0.0914   0.8570   0.0838
  -2.250   0.2291   0.01365   0.00848  -0.0919   0.8436   0.0926
  -2.000   0.2521   0.01094   0.00575  -0.0930   0.8350   0.0946
  -1.750   0.2767   0.00981   0.00459  -0.0933   0.8232   0.0975
  -1.500   0.3077   0.00908   0.00347  -0.0937   0.8119   0.1084
  -1.250   0.3326   0.00800   0.00238  -0.0939   0.8023   0.1118
  -1.000   0.3606   0.00736   0.00154  -0.0942   0.7907   0.1252
  -0.750   0.3877   0.00678   0.00083  -0.0944   0.7794   0.1402
  -0.500   0.4407   0.01810   0.01114  -0.0996   0.7903   0.0949
  -0.250   0.4708   0.01653   0.00929  -0.0994   0.7782   0.0845
   0.000   0.4994   0.01574   0.00828  -0.0990   0.7664   0.0861
   0.250   0.5276   0.01522   0.00754  -0.0986   0.7548   0.0903
   0.500   0.5559   0.01484   0.00692  -0.0981   0.7428   0.0927
   0.750   0.5837   0.01398   0.00605  -0.0979   0.7299   0.0979
   1.000   0.6113   0.01383   0.00581  -0.0976   0.7170   0.1060
   1.250   0.6388   0.01337   0.00535  -0.0973   0.7042   0.1122
   1.500   0.6662   0.01328   0.00519  -0.0969   0.6909   0.1207
   1.750   0.6935   0.01302   0.00495  -0.0966   0.6772   0.1270
   2.000   0.7209   0.01297   0.00486  -0.0962   0.6631   0.1355
   2.250   0.7482   0.01283   0.00475  -0.0959   0.6481   0.1425
   2.500   0.7756   0.01281   0.00471  -0.0956   0.6322   0.1510
   2.750   0.8029   0.01277   0.00469  -0.0953   0.6150   0.1658
   3.000   0.8300   0.01266   0.00468  -0.0950   0.5957   0.2018
   3.250   0.8512   0.01126   0.00459  -0.0932   0.5769   1.0000
   3.500   0.8778   0.01144   0.00459  -0.0927   0.5568   1.0000
   3.750   0.9045   0.01160   0.00466  -0.0924   0.5357   1.0000
   4.000   0.9312   0.01181   0.00477  -0.0920   0.5171   1.0000
   4.250   0.9579   0.01205   0.00493  -0.0916   0.5003   1.0000
   4.500   0.9843   0.01232   0.00511  -0.0913   0.4840   1.0000
   4.750   1.0107   0.01261   0.00533  -0.0910   0.4687   1.0000
   5.000   1.0370   0.01293   0.00559  -0.0906   0.4546   1.0000
   5.250   1.0632   0.01326   0.00591  -0.0903   0.4411   1.0000
   5.500   1.0893   0.01360   0.00623  -0.0900   0.4277   1.0000
   5.750   1.1151   0.01396   0.00656  -0.0896   0.4137   1.0000
   6.000   1.1407   0.01431   0.00692  -0.0892   0.3993   1.0000
   6.250   1.1662   0.01466   0.00727  -0.0888   0.3843   1.0000
   6.500   1.1913   0.01498   0.00762  -0.0883   0.3669   1.0000
   6.750   1.2158   0.01532   0.00796  -0.0878   0.3473   1.0000
   7.000   1.2401   0.01568   0.00834  -0.0872   0.3250   1.0000
   7.250   1.2634   0.01611   0.00874  -0.0865   0.2965   1.0000
   7.500   1.2856   0.01668   0.00921  -0.0857   0.2598   1.0000
   7.750   1.3062   0.01748   0.00982  -0.0848   0.2252   1.0000
   8.000   1.3265   0.01833   0.01054  -0.0839   0.1982   1.0000
   8.250   1.3468   0.01917   0.01130  -0.0830   0.1788   1.0000
   8.500   1.3670   0.02000   0.01210  -0.0820   0.1633   1.0000
   8.750   1.3868   0.02082   0.01291  -0.0810   0.1498   1.0000
   9.000   1.4061   0.02165   0.01376  -0.0800   0.1376   1.0000
   9.250   1.4251   0.02246   0.01459  -0.0789   0.1246   1.0000
   9.500   1.4446   0.02318   0.01538  -0.0779   0.1094   1.0000
   9.750   1.4622   0.02409   0.01625  -0.0767   0.0807   1.0000
  10.000   1.4674   0.02621   0.01803  -0.0740   0.0516   1.0000
  10.250   1.4729   0.02805   0.01988  -0.0712   0.0428   1.0000
  10.500   1.4809   0.02950   0.02147  -0.0686   0.0386   1.0000
  10.750   1.4828   0.03111   0.02315  -0.0654   0.0361   1.0000
  11.000   1.4779   0.03336   0.02546  -0.0619   0.0344   1.0000
  11.250   1.4805   0.03526   0.02750  -0.0595   0.0331   1.0000
  11.500   1.4831   0.03729   0.02967  -0.0575   0.0318   1.0000
  11.750   1.4853   0.03946   0.03195  -0.0558   0.0305   1.0000
  12.000   1.4866   0.04181   0.03439  -0.0544   0.0293   1.0000
  12.250   1.4857   0.04450   0.03714  -0.0531   0.0282   1.0000
  12.500   1.4825   0.04768   0.04037  -0.0513   0.0273   1.0000
  12.750   1.4858   0.05018   0.04303  -0.0502   0.0268   1.0000
  13.000   1.4884   0.05283   0.04584  -0.0492   0.0263   1.0000
  13.250   1.4904   0.05562   0.04880  -0.0482   0.0258   1.0000
  13.500   1.4917   0.05856   0.05191  -0.0473   0.0253   1.0000
  13.750   1.4915   0.06172   0.05524  -0.0466   0.0249   1.0000
  14.000   1.4901   0.06511   0.05882  -0.0461   0.0245   1.0000
  14.250   1.4872   0.06874   0.06262  -0.0458   0.0242   1.0000
  14.500   1.4818   0.07270   0.06678  -0.0459   0.0239   1.0000
  14.750   1.4748   0.07694   0.07123  -0.0464   0.0236   1.0000
  15.000   1.4663   0.08147   0.07593  -0.0472   0.0234   1.0000
  15.250   1.4567   0.08624   0.08088  -0.0484   0.0231   1.0000
  15.500   1.4464   0.09131   0.08612  -0.0499   0.0229   1.0000
  15.750   1.4348   0.09678   0.09178  -0.0518   0.0227   1.0000
  16.000   1.4220   0.10266   0.09783  -0.0543   0.0225   1.0000
  16.250   1.4077   0.10912   0.10449  -0.0573   0.0224   1.0000
  16.500   1.3901   0.11661   0.11220  -0.0614   0.0225   1.0000
  16.750   1.3671   0.12579   0.12165  -0.0671   0.0227   1.0000
  17.000   1.3382   0.13708   0.13325  -0.0745   0.0232   1.0000
  17.250   1.2714   0.16057   0.15718  -0.0913   0.0252   1.0000
  17.500   1.2241   0.18127   0.17802  -0.1051   0.0267   1.0000
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