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GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 425 AIRFOIL (goe425-il)
Reynolds number: 200,000
Max Cl/Cd: 74.01 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe425-il-200000-n5.txt
Download as CSV file: xf-goe425-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 425 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2941   0.10030   0.09592  -0.0485   0.7662   0.0379
 -10.500  -0.3814   0.07098   0.06657  -0.0690   0.7707   0.0348
 -10.250  -0.4063   0.06114   0.05656  -0.0785   0.7622   0.0346
 -10.000  -0.4312   0.05359   0.04876  -0.0869   0.7524   0.0344
  -9.750  -0.4498   0.04881   0.04364  -0.0890   0.7442   0.0344
  -9.500  -0.4559   0.04466   0.03912  -0.0900   0.7361   0.0344
  -9.000  -0.4476   0.03818   0.03178  -0.0900   0.7218   0.0346
  -8.750  -0.4362   0.03572   0.02888  -0.0895   0.7147   0.0347
  -8.500  -0.4208   0.03359   0.02643  -0.0891   0.7080   0.0350
  -8.250  -0.4014   0.03192   0.02462  -0.0888   0.7006   0.0354
  -8.000  -0.3804   0.03066   0.02321  -0.0885   0.6941   0.0358
  -7.750  -0.3587   0.02941   0.02182  -0.0882   0.6873   0.0363
  -7.500  -0.3370   0.02813   0.02031  -0.0878   0.6808   0.0367
  -7.250  -0.3148   0.02686   0.01878  -0.0874   0.6753   0.0369
  -7.000  -0.2914   0.02568   0.01740  -0.0871   0.6687   0.0372
  -6.750  -0.2675   0.02463   0.01613  -0.0867   0.6626   0.0375
  -6.500  -0.2430   0.02368   0.01498  -0.0863   0.6570   0.0378
  -6.250  -0.2179   0.02280   0.01394  -0.0860   0.6503   0.0381
  -6.000  -0.1926   0.02202   0.01298  -0.0856   0.6443   0.0385
  -5.750  -0.1669   0.02131   0.01213  -0.0853   0.6388   0.0390
  -5.500  -0.1407   0.02071   0.01140  -0.0851   0.6327   0.0396
  -5.250  -0.1145   0.02022   0.01074  -0.0848   0.6274   0.0402
  -5.000  -0.0887   0.01952   0.00999  -0.0845   0.6228   0.0407
  -4.750  -0.0627   0.01886   0.00935  -0.0843   0.6171   0.0412
  -4.500  -0.0369   0.01832   0.00878  -0.0840   0.6119   0.0417
  -4.250  -0.0111   0.01785   0.00826  -0.0836   0.6073   0.0422
  -4.000   0.0150   0.01742   0.00782  -0.0834   0.6020   0.0428
  -3.750   0.0411   0.01703   0.00740  -0.0831   0.5971   0.0434
  -3.500   0.0673   0.01668   0.00700  -0.0828   0.5930   0.0442
  -3.250   0.0936   0.01638   0.00663  -0.0826   0.5893   0.0450
  -3.000   0.1203   0.01612   0.00635  -0.0824   0.5846   0.0461
  -2.750   0.1465   0.01581   0.00601  -0.0822   0.5801   0.0474
  -2.500   0.1730   0.01555   0.00570  -0.0820   0.5762   0.0491
  -2.250   0.1998   0.01537   0.00543  -0.0818   0.5728   0.0506
  -2.000   0.2271   0.01520   0.00524  -0.0817   0.5689   0.0523
  -1.750   0.2543   0.01505   0.00506  -0.0816   0.5650   0.0545
  -1.500   0.2814   0.01488   0.00487  -0.0814   0.5612   0.0584
  -1.000   0.3352   0.01451   0.00466  -0.0812   0.5547   0.1214
  -0.750   0.3594   0.01383   0.00458  -0.0811   0.5512   0.2674
  -0.500   0.3838   0.01339   0.00463  -0.0807   0.5476   0.4087
  -0.250   0.4100   0.01329   0.00470  -0.0804   0.5441   0.4807
   0.000   0.4369   0.01327   0.00473  -0.0802   0.5411   0.5249
   0.250   0.4634   0.01325   0.00479  -0.0799   0.5382   0.5655
   0.500   0.4892   0.01319   0.00491  -0.0794   0.5347   0.6110
   0.750   0.5151   0.01313   0.00499  -0.0790   0.5311   0.6528
   1.000   0.5412   0.01308   0.00505  -0.0785   0.5278   0.6881
   1.250   0.5677   0.01305   0.00509  -0.0781   0.5247   0.7197
   1.500   0.5944   0.01302   0.00513  -0.0777   0.5219   0.7619
   1.750   0.6256   0.01291   0.00529  -0.0781   0.5184   0.8479
   2.000   0.6826   0.01294   0.00542  -0.0841   0.5143   0.9626
   2.250   0.7223   0.01308   0.00551  -0.0868   0.5108   1.0000
   2.500   0.7479   0.01323   0.00558  -0.0865   0.5079   1.0000
   2.750   0.7740   0.01340   0.00566  -0.0862   0.5052   1.0000
   3.000   0.7993   0.01357   0.00581  -0.0858   0.5020   1.0000
   3.250   0.8246   0.01373   0.00599  -0.0855   0.4985   1.0000
   3.500   0.8502   0.01391   0.00615  -0.0851   0.4953   1.0000
   3.750   0.8760   0.01408   0.00629  -0.0848   0.4923   1.0000
   4.000   0.9022   0.01426   0.00642  -0.0846   0.4895   1.0000
   4.250   0.9282   0.01446   0.00658  -0.0844   0.4866   1.0000
   4.500   0.9531   0.01465   0.00683  -0.0840   0.4829   1.0000
   4.750   0.9784   0.01485   0.00706  -0.0837   0.4794   1.0000
   5.000   1.0039   0.01505   0.00726  -0.0834   0.4763   1.0000
   5.250   1.0298   0.01524   0.00744  -0.0831   0.4734   1.0000
   5.500   1.0559   0.01545   0.00761  -0.0829   0.4702   1.0000
   5.750   1.0797   0.01566   0.00791  -0.0824   0.4655   1.0000
   6.000   1.1041   0.01585   0.00815  -0.0819   0.4609   1.0000
   6.250   1.1292   0.01602   0.00831  -0.0816   0.4568   1.0000
   6.500   1.1546   0.01623   0.00851  -0.0813   0.4534   1.0000
   6.750   1.1779   0.01648   0.00887  -0.0807   0.4488   1.0000
   7.000   1.2017   0.01671   0.00916  -0.0802   0.4444   1.0000
   7.250   1.2261   0.01692   0.00937  -0.0798   0.4404   1.0000
   7.500   1.2498   0.01714   0.00964  -0.0792   0.4359   1.0000
   7.750   1.2717   0.01739   0.00999  -0.0784   0.4295   1.0000
   8.000   1.2944   0.01757   0.01017  -0.0777   0.4237   1.0000
   8.250   1.3159   0.01784   0.01052  -0.0769   0.4175   1.0000
   8.500   1.3373   0.01812   0.01087  -0.0761   0.4116   1.0000
   8.750   1.3589   0.01836   0.01111  -0.0752   0.4062   1.0000
   9.000   1.3779   0.01870   0.01157  -0.0741   0.3984   1.0000
   9.250   1.3969   0.01900   0.01188  -0.0729   0.3912   1.0000
   9.500   1.4143   0.01939   0.01237  -0.0715   0.3831   1.0000
   9.750   1.4307   0.01978   0.01276  -0.0700   0.3758   1.0000
  10.000   1.4447   0.02024   0.01332  -0.0681   0.3679   1.0000
  10.250   1.4564   0.02077   0.01386  -0.0659   0.3595   1.0000
  10.500   1.4679   0.02142   0.01458  -0.0640   0.3501   1.0000
  10.750   1.4776   0.02217   0.01537  -0.0620   0.3411   1.0000
  11.000   1.4860   0.02308   0.01631  -0.0600   0.3310   1.0000
  11.250   1.4937   0.02413   0.01742  -0.0582   0.3207   1.0000
  11.500   1.4981   0.02545   0.01877  -0.0563   0.3091   1.0000
  11.750   1.4994   0.02712   0.02045  -0.0545   0.2952   1.0000
  12.000   1.4980   0.02917   0.02249  -0.0529   0.2787   1.0000
  12.250   1.4925   0.03171   0.02502  -0.0514   0.2587   1.0000
  12.500   1.4805   0.03496   0.02819  -0.0499   0.2361   1.0000
  12.750   1.4640   0.03878   0.03192  -0.0485   0.2118   1.0000
  13.000   1.4451   0.04298   0.03602  -0.0472   0.1927   1.0000
  13.250   1.4285   0.04708   0.04007  -0.0462   0.1793   1.0000
  13.500   1.4156   0.05098   0.04396  -0.0455   0.1688   1.0000
  13.750   1.4065   0.05463   0.04761  -0.0450   0.1602   1.0000
  14.000   1.3971   0.05838   0.05136  -0.0446   0.1526   1.0000
  14.250   1.3937   0.06156   0.05459  -0.0444   0.1454   1.0000
  14.500   1.3883   0.06503   0.05807  -0.0442   0.1384   1.0000
  14.750   1.3866   0.06811   0.06120  -0.0441   0.1320   1.0000
  15.000   1.3841   0.07133   0.06447  -0.0440   0.1253   1.0000
  15.250   1.3824   0.07450   0.06768  -0.0440   0.1192   1.0000
  15.500   1.3805   0.07774   0.07095  -0.0442   0.1125   1.0000
  15.750   1.3786   0.08099   0.07423  -0.0443   0.1066   1.0000
  16.000   1.3765   0.08430   0.07758  -0.0445   0.1005   1.0000
  16.250   1.3743   0.08768   0.08097  -0.0448   0.0954   1.0000
  16.500   1.3729   0.09097   0.08430  -0.0452   0.0904   1.0000
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