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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 200,000
Max Cl/Cd: 83.43 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe240-il-200000.txt
Download as CSV file: xf-goe240-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3239   0.08837   0.08524  -0.0225   1.0000   0.0324
  -6.750  -0.3295   0.08665   0.08359  -0.0212   1.0000   0.0329
  -6.500  -0.3446   0.08587   0.08291  -0.0181   1.0000   0.0331
  -6.250  -0.3187   0.08163   0.07865  -0.0252   0.9956   0.0347
  -6.000  -0.2571   0.07624   0.07309  -0.0468   0.9870   0.0379
  -5.750  -0.2251   0.06965   0.06644  -0.0547   0.9833   0.0388
  -5.500  -0.2096   0.06633   0.06315  -0.0536   0.9775   0.0404
  -5.250  -0.1747   0.06246   0.05922  -0.0596   0.9729   0.0436
  -5.000  -0.1065   0.05653   0.05292  -0.0776   0.9658   0.0487
  -4.750  -0.0891   0.05271   0.04918  -0.0778   0.9612   0.0502
  -4.500  -0.0548   0.04957   0.04598  -0.0818   0.9581   0.0537
  -4.250  -0.0036   0.04493   0.04100  -0.0912   0.9523   0.0610
  -4.000   0.0225   0.04227   0.03837  -0.0928   0.9469   0.0635
  -3.750   0.0783   0.03927   0.03478  -0.1004   0.9431   0.0729
  -3.500   0.0989   0.03591   0.03154  -0.1010   0.9355   0.0747
  -3.250   0.1436   0.03575   0.03080  -0.1041   0.9300   0.0857
  -3.000   0.1669   0.03104   0.02626  -0.1057   0.9239   0.0880
  -2.750   0.1947   0.02905   0.02423  -0.1065   0.9167   0.0917
  -2.500   0.2301   0.02702   0.02178  -0.1082   0.9106   0.1014
  -2.250   0.2567   0.02518   0.01992  -0.1085   0.9027   0.1052
  -2.000   0.2872   0.02359   0.01810  -0.1091   0.8954   0.1172
  -1.750   0.3165   0.02225   0.01656  -0.1094   0.8868   0.1309
  -1.500   0.3546   0.01856   0.01192  -0.1085   0.8780   0.0743
  -1.250   0.3842   0.01696   0.01008  -0.1080   0.8687   0.0676
  -1.000   0.4128   0.01562   0.00843  -0.1074   0.8579   0.0646
  -0.750   0.4403   0.01490   0.00754  -0.1067   0.8467   0.0658
  -0.500   0.4681   0.01426   0.00675  -0.1062   0.8369   0.0666
  -0.250   0.4958   0.01364   0.00598  -0.1056   0.8274   0.0665
   0.000   0.5224   0.01318   0.00547  -0.1050   0.8161   0.0674
   0.250   0.5491   0.01283   0.00509  -0.1043   0.8053   0.0693
   0.500   0.5759   0.01261   0.00480  -0.1037   0.7948   0.0722
   0.750   0.6024   0.01230   0.00453  -0.1032   0.7835   0.0786
   1.000   0.6287   0.01211   0.00437  -0.1026   0.7711   0.0946
   1.250   0.6528   0.01101   0.00429  -0.1021   0.7585   0.4586
   1.500   0.6808   0.01001   0.00415  -0.1014   0.7445   1.0000
   1.750   0.7066   0.01007   0.00406  -0.1006   0.7287   1.0000
   2.000   0.7324   0.01012   0.00398  -0.0998   0.7119   1.0000
   2.250   0.7583   0.01017   0.00393  -0.0991   0.6952   1.0000
   2.500   0.7843   0.01024   0.00389  -0.0984   0.6783   1.0000
   2.750   0.8100   0.01030   0.00389  -0.0978   0.6581   1.0000
   3.000   0.8356   0.01039   0.00387  -0.0971   0.6366   1.0000
   3.250   0.8609   0.01050   0.00389  -0.0964   0.6128   1.0000
   3.500   0.8859   0.01068   0.00392  -0.0956   0.5884   1.0000
   3.750   0.9106   0.01092   0.00401  -0.0949   0.5637   1.0000
   4.000   0.9353   0.01121   0.00417  -0.0942   0.5407   1.0000
   4.250   0.9601   0.01153   0.00440  -0.0935   0.5199   1.0000
   4.500   0.9848   0.01187   0.00464  -0.0929   0.4999   1.0000
   4.750   1.0093   0.01217   0.00490  -0.0923   0.4774   1.0000
   5.000   1.0335   0.01249   0.00515  -0.0916   0.4537   1.0000
   5.250   1.0574   0.01281   0.00544  -0.0909   0.4289   1.0000
   5.500   1.0812   0.01316   0.00572  -0.0902   0.4037   1.0000
   5.750   1.1043   0.01357   0.00605  -0.0894   0.3788   1.0000
   6.000   1.1268   0.01404   0.00643  -0.0885   0.3548   1.0000
   6.250   1.1489   0.01456   0.00688  -0.0876   0.3295   1.0000
   6.500   1.1704   0.01512   0.00734  -0.0867   0.3025   1.0000
   6.750   1.1917   0.01569   0.00782  -0.0858   0.2757   1.0000
   7.000   1.2129   0.01627   0.00830  -0.0848   0.2507   1.0000
   7.250   1.2343   0.01682   0.00882  -0.0839   0.2269   1.0000
   7.500   1.2550   0.01743   0.00935  -0.0830   0.2073   1.0000
   7.750   1.2758   0.01802   0.00992  -0.0820   0.1898   1.0000
   8.000   1.2963   0.01863   0.01053  -0.0810   0.1766   1.0000
   8.250   1.3164   0.01927   0.01119  -0.0800   0.1619   1.0000
   8.500   1.3352   0.02000   0.01188  -0.0788   0.1416   1.0000
   8.750   1.3527   0.02086   0.01263  -0.0774   0.1095   1.0000
   9.000   1.3573   0.02296   0.01425  -0.0744   0.0529   1.0000
   9.250   1.3667   0.02455   0.01595  -0.0718   0.0401   1.0000
   9.500   1.3778   0.02585   0.01732  -0.0694   0.0338   1.0000
   9.750   1.3873   0.02703   0.01864  -0.0668   0.0307   1.0000
  10.000   1.3968   0.02815   0.01986  -0.0644   0.0280   1.0000
  10.250   1.4010   0.02968   0.02145  -0.0615   0.0262   1.0000
  10.500   1.4007   0.03157   0.02346  -0.0584   0.0253   1.0000
  10.750   1.4030   0.03338   0.02541  -0.0558   0.0247   1.0000
  11.000   1.4043   0.03540   0.02756  -0.0534   0.0241   1.0000
  11.250   1.4054   0.03757   0.02986  -0.0513   0.0236   1.0000
  11.500   1.4067   0.03988   0.03229  -0.0494   0.0231   1.0000
  11.750   1.4086   0.04227   0.03481  -0.0477   0.0227   1.0000
  12.000   1.4114   0.04469   0.03734  -0.0460   0.0224   1.0000
  12.250   1.4152   0.04708   0.03984  -0.0445   0.0219   1.0000
  12.500   1.4188   0.04952   0.04238  -0.0432   0.0214   1.0000
  12.750   1.4213   0.05210   0.04505  -0.0420   0.0207   1.0000
  13.000   1.4239   0.05493   0.04797  -0.0407   0.0201   1.0000
  13.250   1.4276   0.05801   0.05120  -0.0391   0.0198   1.0000
  13.500   1.4303   0.06128   0.05467  -0.0378   0.0197   1.0000
  13.750   1.4296   0.06487   0.05849  -0.0368   0.0197   1.0000
  14.000   1.4258   0.06865   0.06251  -0.0361   0.0197   1.0000
  14.250   1.4192   0.07267   0.06676  -0.0359   0.0197   1.0000
  14.500   1.4104   0.07697   0.07129  -0.0360   0.0198   1.0000
  14.750   1.3994   0.08158   0.07613  -0.0367   0.0199   1.0000
  15.000   1.3860   0.08669   0.08149  -0.0380   0.0201   1.0000
  15.250   1.3700   0.09249   0.08755  -0.0400   0.0203   1.0000
  15.500   1.3506   0.09925   0.09460  -0.0429   0.0205   1.0000
  15.750   1.3290   0.10699   0.10262  -0.0467   0.0209   1.0000
  16.000   1.3035   0.11603   0.11194  -0.0520   0.0213   1.0000
  16.250   1.2758   0.12630   0.12246  -0.0587   0.0216   1.0000
  16.500   1.2482   0.13750   0.13389  -0.0663   0.0220   1.0000
  16.750   1.2197   0.15002   0.14660  -0.0750   0.0224   1.0000
  17.000   1.1859   0.16563   0.16237  -0.0858   0.0230   1.0000
  17.250   1.1502   0.18402   0.18082  -0.0975   0.0242   1.0000
  17.500   1.1399   0.19349   0.19025  -0.1026   0.0251   1.0000
  17.750   0.8929   0.16397   0.16094  -0.0647   0.0255   1.0000
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