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GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il)
Reynolds number: 100,000
Max Cl/Cd: 65.55 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe417a-il-100000.txt
Download as CSV file: xf-goe417a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417A (GEW. PLATTE) AIRFOIL                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3465   0.10608   0.10109  -0.0151   1.0000   0.0332
  -7.500  -0.3505   0.10449   0.09955  -0.0135   1.0000   0.0336
  -7.250  -0.3525   0.10278   0.09788  -0.0123   1.0000   0.0340
  -7.000  -0.3517   0.10083   0.09597  -0.0118   1.0000   0.0345
  -6.750  -0.3497   0.09887   0.09405  -0.0116   1.0000   0.0350
  -6.500  -0.3462   0.09699   0.09220  -0.0117   1.0000   0.0355
  -6.250  -0.3392   0.09589   0.09112  -0.0133   1.0000   0.0362
  -6.000  -0.3246   0.09628   0.09149  -0.0182   1.0000   0.0366
  -5.750  -0.3070   0.09572   0.09090  -0.0231   1.0000   0.0368
  -5.500  -0.3101   0.09005   0.08531  -0.0186   1.0000   0.0371
  -5.250  -0.3079   0.08612   0.08142  -0.0164   1.0000   0.0375
  -5.000  -0.3017   0.08311   0.07844  -0.0158   1.0000   0.0379
  -4.750  -0.2933   0.08042   0.07575  -0.0159   1.0000   0.0386
  -4.500  -0.2826   0.07793   0.07326  -0.0165   1.0000   0.0393
  -4.250  -0.2700   0.07553   0.07086  -0.0175   1.0000   0.0401
  -4.000  -0.2557   0.07322   0.06854  -0.0188   1.0000   0.0410
  -3.750  -0.2392   0.07101   0.06630  -0.0205   1.0000   0.0421
  -3.500  -0.2165   0.06932   0.06456  -0.0234   1.0000   0.0435
  -3.250  -0.1627   0.07115   0.06608  -0.0330   1.0000   0.0447
  -3.000  -0.1634   0.06620   0.06125  -0.0304   1.0000   0.0451
  -2.750  -0.1574   0.06275   0.05785  -0.0290   1.0000   0.0458
  -2.500  -0.1449   0.06017   0.05527  -0.0289   1.0000   0.0467
  -2.250  -0.1282   0.05806   0.05313  -0.0296   1.0000   0.0479
  -2.000  -0.1022   0.05601   0.05103  -0.0321   0.9983   0.0495
  -1.750  -0.0511   0.05397   0.04883  -0.0393   0.9908   0.0526
  -1.500   0.0242   0.05483   0.04926  -0.0497   0.9820   0.0548
  -1.250   0.0431   0.04977   0.04433  -0.0512   0.9747   0.0561
  -1.000   0.0780   0.04710   0.04162  -0.0548   0.9672   0.0591
  -0.750   0.1268   0.04617   0.04049  -0.0598   0.9581   0.0650
  -0.500   0.1700   0.04478   0.03890  -0.0637   0.9485   0.0671
  -0.250   0.2035   0.04178   0.03593  -0.0667   0.9419   0.0703
   0.000   0.2393   0.04048   0.03451  -0.0690   0.9311   0.0757
   0.250   0.2862   0.03927   0.03309  -0.0729   0.9235   0.0800
   0.500   0.3176   0.03730   0.03111  -0.0746   0.9135   0.0852
   0.750   0.3565   0.03644   0.03005  -0.0766   0.9032   0.0922
   1.000   0.4031   0.03543   0.02885  -0.0800   0.8961   0.1034
   1.250   0.4346   0.03418   0.02750  -0.0809   0.8840   0.1158
   1.500   0.4671   0.03174   0.02514  -0.0824   0.8738   0.1340
   1.750   0.5115   0.02976   0.02312  -0.0855   0.8659   0.1779
   2.000   0.5420   0.02821   0.02158  -0.0860   0.8529   0.2493
   2.250   0.5742   0.02639   0.01982  -0.0866   0.8416   0.3120
   2.500   0.6210   0.02416   0.01763  -0.0892   0.8356   0.3563
   2.750   0.6593   0.02286   0.01631  -0.0902   0.8237   0.3661
   3.000   0.7090   0.02183   0.01512  -0.0927   0.8135   0.3455
   3.250   0.7673   0.02081   0.01389  -0.0962   0.8046   0.2945
   3.500   0.8140   0.02011   0.01294  -0.0975   0.7902   0.2221
   3.750   0.8617   0.01938   0.01201  -0.0994   0.7749   0.1690
   4.000   0.9137   0.01869   0.01122  -0.1026   0.7588   0.1359
   4.250   0.9595   0.01823   0.01068  -0.1050   0.7386   0.1192
   4.500   1.0021   0.01785   0.01023  -0.1070   0.7153   0.1134
   4.750   1.0365   0.01750   0.00985  -0.1073   0.6839   0.1164
   5.000   1.0619   0.01734   0.00955  -0.1057   0.6455   0.1167
   5.250   1.0813   0.01734   0.00944  -0.1031   0.6038   0.1190
   5.500   1.0993   0.01751   0.00939  -0.1003   0.5588   0.1251
   5.750   1.1159   0.01781   0.00951  -0.0974   0.5129   0.1411
   6.000   1.1825   0.01804   0.01021  -0.1061   0.3922   1.0000
   6.250   1.1913   0.01903   0.01062  -0.1023   0.3170   1.0000
   6.500   1.1993   0.02031   0.01134  -0.0987   0.2509   1.0000
   6.750   1.2073   0.02177   0.01232  -0.0951   0.1818   1.0000
   7.000   1.2166   0.02323   0.01325  -0.0917   0.1082   1.0000
   7.250   1.2260   0.02463   0.01436  -0.0883   0.0876   1.0000
   7.500   1.2345   0.02608   0.01568  -0.0847   0.0796   1.0000
   7.750   1.2457   0.02735   0.01702  -0.0815   0.0748   1.0000
   8.000   1.2564   0.02881   0.01847  -0.0784   0.0707   1.0000
   8.250   1.2695   0.03075   0.02032  -0.0759   0.0669   1.0000
   8.500   1.2888   0.03228   0.02195  -0.0742   0.0640   1.0000
   8.750   1.3128   0.03423   0.02401  -0.0733   0.0619   1.0000
   9.000   1.3394   0.03648   0.02635  -0.0729   0.0603   1.0000
   9.250   1.3653   0.03915   0.02907  -0.0727   0.0578   1.0000
   9.500   1.3944   0.04397   0.03399  -0.0735   0.0558   1.0000
   9.750   1.4104   0.04697   0.03735  -0.0715   0.0557   1.0000
  10.000   1.4237   0.05013   0.04092  -0.0691   0.0560   1.0000
  10.250   1.4324   0.05232   0.04349  -0.0659   0.0565   1.0000
  10.500   1.4353   0.05446   0.04616  -0.0616   0.0577   1.0000
  10.750   1.4221   0.05786   0.05030  -0.0556   0.0598   1.0000
  11.000   1.4068   0.06213   0.05511  -0.0503   0.0618   1.0000
  11.250   1.3915   0.06610   0.05944  -0.0455   0.0630   1.0000
  11.500   1.3733   0.06976   0.06336  -0.0407   0.0642   1.0000
  11.750   1.3535   0.07352   0.06734  -0.0366   0.0650   1.0000
  12.000   1.3380   0.07793   0.07191  -0.0338   0.0662   1.0000
  12.250   1.1979   0.07549   0.06992  -0.0210   0.0652   1.0000
  12.500   1.1690   0.08096   0.07557  -0.0201   0.0658   1.0000
  12.750   1.1377   0.08697   0.08170  -0.0203   0.0661   1.0000
  13.000   1.1049   0.09355   0.08843  -0.0217   0.0665   1.0000
  13.250   1.0971   0.09905   0.09402  -0.0221   0.0685   1.0000
  13.500   1.0527   0.10687   0.10200  -0.0262   0.0686   1.0000
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