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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 200,000
Max Cl/Cd: 75.9 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe426-il-200000.txt
Download as CSV file: xf-goe426-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 426 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2658   0.10014   0.09676  -0.0450   1.0000   0.0584
  -9.250  -0.2739   0.09877   0.09546  -0.0427   1.0000   0.0591
  -9.000  -0.2703   0.09612   0.09286  -0.0440   0.9975   0.0606
  -8.750  -0.2545   0.09092   0.08766  -0.0527   0.9892   0.0639
  -8.500  -0.2544   0.08187   0.07863  -0.0702   0.9755   0.0661
  -8.250  -0.2211   0.07998   0.07671  -0.0675   0.9732   0.0675
  -8.000  -0.1927   0.07688   0.07360  -0.0709   0.9676   0.0699
  -7.750  -0.1713   0.07177   0.06847  -0.0799   0.9568   0.0740
  -7.500  -0.1801   0.05966   0.05613  -0.1031   0.9288   0.0780
  -7.250  -0.1544   0.05817   0.05471  -0.1014   0.9180   0.0794
  -7.000  -0.1374   0.05603   0.05252  -0.1018   0.9030   0.0813
  -6.750  -0.1404   0.05192   0.04794  -0.1075   0.8808   0.0888
  -6.500  -0.1366   0.04716   0.04298  -0.1086   0.8653   0.0913
  -6.250  -0.1179   0.04512   0.04099  -0.1077   0.8519   0.0930
  -6.000  -0.1010   0.04329   0.03907  -0.1072   0.8381   0.0959
  -5.750  -0.0915   0.04028   0.03549  -0.1086   0.8237   0.1059
  -5.500  -0.0712   0.03825   0.03353  -0.1079   0.8112   0.1086
  -5.250  -0.0515   0.03677   0.03188  -0.1076   0.7976   0.1152
  -5.000  -0.0344   0.03426   0.02908  -0.1078   0.7849   0.1235
  -4.750  -0.0126   0.03280   0.02751  -0.1075   0.7730   0.1296
  -4.500   0.0076   0.03090   0.02532  -0.1074   0.7618   0.1408
  -4.250   0.0387   0.02394   0.01682  -0.1062   0.7516   0.0742
  -4.000   0.0638   0.02215   0.01471  -0.1057   0.7413   0.0718
  -3.750   0.0902   0.02039   0.01243  -0.1049   0.7311   0.0679
  -3.500   0.1173   0.01965   0.01140  -0.1043   0.7206   0.0662
  -3.250   0.1445   0.01895   0.01048  -0.1039   0.7119   0.0658
  -3.000   0.1707   0.01809   0.00952  -0.1035   0.7017   0.0659
  -2.750   0.1976   0.01725   0.00855  -0.1031   0.6941   0.0663
  -2.500   0.2234   0.01650   0.00781  -0.1027   0.6849   0.0676
  -2.250   0.2501   0.01606   0.00731  -0.1024   0.6780   0.0701
  -2.000   0.2761   0.01565   0.00692  -0.1020   0.6695   0.0722
  -1.750   0.3029   0.01528   0.00647  -0.1017   0.6630   0.0740
  -1.500   0.3292   0.01499   0.00616  -0.1013   0.6557   0.0761
  -1.250   0.3556   0.01459   0.00576  -0.1010   0.6490   0.0800
  -1.000   0.3827   0.01443   0.00555  -0.1009   0.6431   0.0868
  -0.750   0.4094   0.01420   0.00535  -0.1006   0.6362   0.0998
  -0.500   0.4315   0.01280   0.00514  -0.1003   0.6308   0.4350
  -0.250   0.4509   0.01227   0.00540  -0.0983   0.6252   0.6697
   0.000   0.4720   0.01211   0.00551  -0.0963   0.6192   0.7674
   0.250   0.4943   0.01194   0.00548  -0.0944   0.6143   0.8477
   0.500   0.5401   0.01182   0.00545  -0.0974   0.6081   0.9569
   0.750   0.5798   0.01191   0.00540  -0.1001   0.6019   1.0000
   1.000   0.6070   0.01207   0.00539  -0.1001   0.5973   1.0000
   1.250   0.6329   0.01225   0.00551  -0.0998   0.5916   1.0000
   1.500   0.6596   0.01241   0.00558  -0.0997   0.5861   1.0000
   1.750   0.6874   0.01259   0.00562  -0.0997   0.5816   1.0000
   2.000   0.7135   0.01280   0.00579  -0.0995   0.5761   1.0000
   2.250   0.7402   0.01298   0.00591  -0.0993   0.5706   1.0000
   2.500   0.7680   0.01318   0.00600  -0.0993   0.5661   1.0000
   2.750   0.7944   0.01341   0.00621  -0.0992   0.5610   1.0000
   3.000   0.8206   0.01361   0.00640  -0.0989   0.5552   1.0000
   3.250   0.8482   0.01382   0.00652  -0.0989   0.5504   1.0000
   3.500   0.8750   0.01409   0.00676  -0.0988   0.5457   1.0000
   3.750   0.9006   0.01432   0.00702  -0.0985   0.5399   1.0000
   4.000   0.9280   0.01453   0.00717  -0.0984   0.5349   1.0000
   4.250   0.9551   0.01482   0.00741  -0.0984   0.5300   1.0000
   4.500   0.9799   0.01506   0.00774  -0.0979   0.5242   1.0000
   4.750   1.0069   0.01530   0.00794  -0.0978   0.5192   1.0000
   5.000   1.0348   0.01561   0.00818  -0.0979   0.5146   1.0000
   5.250   1.0583   0.01587   0.00855  -0.0973   0.5083   1.0000
   5.500   1.0849   0.01610   0.00878  -0.0971   0.5030   1.0000
   5.750   1.1133   0.01643   0.00904  -0.0973   0.4987   1.0000
   6.000   1.1357   0.01672   0.00949  -0.0965   0.4925   1.0000
   6.250   1.1618   0.01696   0.00975  -0.0963   0.4870   1.0000
   6.500   1.1903   0.01727   0.00998  -0.0965   0.4826   1.0000
   6.750   1.2117   0.01760   0.01049  -0.0955   0.4763   1.0000
   7.000   1.2374   0.01786   0.01079  -0.0952   0.4710   1.0000
   7.250   1.2656   0.01813   0.01100  -0.0953   0.4662   1.0000
   7.500   1.2857   0.01841   0.01147  -0.0942   0.4591   1.0000
   7.750   1.3119   0.01856   0.01162  -0.0939   0.4533   1.0000
   8.000   1.3349   0.01882   0.01198  -0.0932   0.4468   1.0000
   8.250   1.3575   0.01892   0.01213  -0.0923   0.4392   1.0000
   8.500   1.3800   0.01902   0.01227  -0.0914   0.4314   1.0000
   8.750   1.4010   0.01897   0.01226  -0.0902   0.4217   1.0000
   9.000   1.4183   0.01900   0.01239  -0.0884   0.4105   1.0000
   9.250   1.4353   0.01902   0.01243  -0.0866   0.3985   1.0000
   9.500   1.4512   0.01912   0.01254  -0.0846   0.3860   1.0000
   9.750   1.4663   0.01935   0.01281  -0.0826   0.3742   1.0000
  10.000   1.4797   0.01969   0.01326  -0.0804   0.3624   1.0000
  10.250   1.4917   0.02009   0.01371  -0.0779   0.3505   1.0000
  10.500   1.4994   0.02055   0.01421  -0.0748   0.3381   1.0000
  10.750   1.5051   0.02114   0.01483  -0.0715   0.3247   1.0000
  11.000   1.5085   0.02190   0.01561  -0.0682   0.3092   1.0000
  11.250   1.5086   0.02290   0.01662  -0.0648   0.2897   1.0000
  11.500   1.5041   0.02428   0.01795  -0.0612   0.2669   1.0000
  11.750   1.4942   0.02622   0.01979  -0.0576   0.2354   1.0000
  12.000   1.4752   0.02911   0.02248  -0.0541   0.1967   1.0000
  12.250   1.4510   0.03291   0.02605  -0.0512   0.1592   1.0000
  12.500   1.4272   0.03718   0.03015  -0.0491   0.1309   1.0000
  12.750   1.4042   0.04177   0.03462  -0.0477   0.1071   1.0000
  13.000   1.3822   0.04660   0.03934  -0.0468   0.0847   1.0000
  13.250   1.3623   0.05153   0.04417  -0.0465   0.0688   1.0000
  13.500   1.3455   0.05638   0.04898  -0.0464   0.0595   1.0000
  13.750   1.3327   0.06096   0.05361  -0.0466   0.0536   1.0000
  14.000   1.3208   0.06558   0.05824  -0.0469   0.0502   1.0000
  14.250   1.3126   0.06985   0.06260  -0.0473   0.0473   1.0000
  14.500   1.3074   0.07381   0.06664  -0.0478   0.0447   1.0000
  14.750   1.3012   0.07795   0.07083  -0.0484   0.0429   1.0000
  15.000   1.2943   0.08216   0.07506  -0.0489   0.0413   1.0000
  15.250   1.2953   0.08542   0.07842  -0.0494   0.0394   1.0000
  15.500   1.2956   0.08878   0.08184  -0.0499   0.0378   1.0000
  15.750   1.2964   0.09199   0.08507  -0.0503   0.0365   1.0000
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