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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 200,000
Max Cl/Cd: 78.33 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe330-il-200000.txt
Download as CSV file: xf-goe330-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 330 (PFALZ 59) 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  -0.2869   0.11586   0.11257  -0.0306   1.0000   0.0332
  -9.250  -0.2952   0.11466   0.11142  -0.0281   1.0000   0.0337
  -9.000  -0.3031   0.11336   0.11017  -0.0259   1.0000   0.0341
  -8.750  -0.2927   0.11007   0.10689  -0.0286   0.9979   0.0351
  -8.500  -0.2773   0.10628   0.10309  -0.0332   0.9949   0.0365
  -8.250  -0.2652   0.10311   0.09992  -0.0398   0.9898   0.0381
  -8.000  -0.2572   0.10051   0.09734  -0.0505   0.9818   0.0386
  -7.750  -0.2423   0.09527   0.09211  -0.0564   0.9753   0.0390
  -7.500  -0.2247   0.09109   0.08792  -0.0521   0.9754   0.0401
  -7.250  -0.2034   0.08745   0.08426  -0.0556   0.9722   0.0416
  -7.000  -0.1869   0.08397   0.08077  -0.0599   0.9654   0.0432
  -6.750  -0.1625   0.07984   0.07662  -0.0677   0.9596   0.0456
  -6.500  -0.1202   0.07472   0.07127  -0.0905   0.9476   0.0475
  -6.250  -0.1085   0.06975   0.06640  -0.0875   0.9456   0.0484
  -6.000  -0.0815   0.06638   0.06303  -0.0890   0.9436   0.0502
  -5.750  -0.0562   0.06307   0.05967  -0.0931   0.9367   0.0531
  -5.250   0.0269   0.05241   0.04864  -0.1130   0.9275   0.0592
  -5.000   0.0419   0.05016   0.04639  -0.1123   0.9186   0.0606
  -4.750   0.0747   0.04707   0.04320  -0.1160   0.9145   0.0641
  -4.500   0.1124   0.04309   0.03866  -0.1221   0.9060   0.0703
  -4.250   0.1369   0.03994   0.03558  -0.1231   0.9006   0.0717
  -4.000   0.1684   0.03736   0.03293  -0.1251   0.8970   0.0745
  -3.750   0.2015   0.03756   0.03235  -0.1258   0.8864   0.0821
  -3.500   0.2255   0.03224   0.02722  -0.1275   0.8821   0.0846
  -3.250   0.2458   0.03066   0.02563  -0.1267   0.8720   0.0881
  -3.000   0.2789   0.02861   0.02315  -0.1280   0.8669   0.0980
  -2.750   0.2999   0.02701   0.02156  -0.1273   0.8569   0.1013
  -2.500   0.3307   0.02547   0.01968  -0.1279   0.8511   0.1133
  -2.250   0.3552   0.02497   0.01903  -0.1271   0.8409   0.1241
  -2.000   0.3805   0.02296   0.01699  -0.1272   0.8333   0.1337
  -1.500   0.4439   0.01917   0.01207  -0.1253   0.8161   0.0792
  -1.250   0.4740   0.01831   0.01073  -0.1244   0.8076   0.0697
  -1.000   0.5000   0.01708   0.00939  -0.1238   0.7976   0.0685
  -0.750   0.5293   0.01622   0.00834  -0.1236   0.7897   0.0685
  -0.500   0.5548   0.01581   0.00782  -0.1227   0.7781   0.0695
  -0.250   0.5806   0.01486   0.00689  -0.1222   0.7676   0.0728
   0.000   0.6082   0.01432   0.00631  -0.1218   0.7582   0.0751
   0.250   0.6337   0.01389   0.00587  -0.1211   0.7462   0.0781
   0.500   0.6595   0.01357   0.00551  -0.1203   0.7337   0.0821
   0.750   0.6848   0.01302   0.00502  -0.1197   0.7209   0.0915
   1.000   0.7106   0.01259   0.00463  -0.1190   0.7075   0.1240
   1.250   0.7519   0.01055   0.00450  -0.1219   0.6932   1.0000
   1.500   0.7773   0.01064   0.00439  -0.1211   0.6778   1.0000
   1.750   0.8023   0.01077   0.00433  -0.1203   0.6609   1.0000
   2.000   0.8269   0.01095   0.00431  -0.1195   0.6429   1.0000
   2.250   0.8513   0.01119   0.00435  -0.1186   0.6245   1.0000
   2.500   0.8751   0.01144   0.00444  -0.1177   0.6057   1.0000
   2.750   0.8984   0.01169   0.00458  -0.1167   0.5865   1.0000
   3.000   0.9218   0.01194   0.00471  -0.1158   0.5680   1.0000
   3.250   0.9451   0.01219   0.00485  -0.1149   0.5505   1.0000
   3.500   0.9684   0.01244   0.00500  -0.1140   0.5341   1.0000
   3.750   0.9917   0.01270   0.00516  -0.1131   0.5189   1.0000
   4.000   1.0151   0.01297   0.00534  -0.1123   0.5050   1.0000
   4.250   1.0386   0.01326   0.00555  -0.1115   0.4926   1.0000
   4.500   1.0623   0.01358   0.00579  -0.1108   0.4818   1.0000
   4.750   1.0860   0.01392   0.00604  -0.1101   0.4716   1.0000
   5.000   1.1098   0.01424   0.00633  -0.1094   0.4617   1.0000
   5.250   1.1340   0.01463   0.00664  -0.1089   0.4532   1.0000
   5.500   1.1579   0.01495   0.00699  -0.1083   0.4449   1.0000
   5.750   1.1827   0.01537   0.00734  -0.1079   0.4379   1.0000
   6.000   1.2065   0.01570   0.00772  -0.1073   0.4303   1.0000
   6.250   1.2318   0.01616   0.00811  -0.1070   0.4238   1.0000
   6.500   1.2549   0.01648   0.00855  -0.1063   0.4165   1.0000
   6.750   1.2794   0.01692   0.00894  -0.1058   0.4095   1.0000
   7.000   1.3007   0.01724   0.00935  -0.1048   0.4001   1.0000
   7.250   1.3212   0.01759   0.00972  -0.1036   0.3891   1.0000
   7.500   1.3411   0.01794   0.01004  -0.1024   0.3778   1.0000
   7.750   1.3591   0.01818   0.01040  -0.1007   0.3662   1.0000
   8.000   1.3774   0.01849   0.01078  -0.0992   0.3549   1.0000
   8.250   1.3950   0.01882   0.01116  -0.0976   0.3436   1.0000
   8.500   1.4105   0.01916   0.01153  -0.0956   0.3303   1.0000
   8.750   1.4250   0.01952   0.01195  -0.0934   0.3161   1.0000
   9.000   1.4369   0.01989   0.01239  -0.0909   0.2987   1.0000
   9.250   1.4453   0.02043   0.01294  -0.0878   0.2743   1.0000
   9.500   1.4510   0.02128   0.01366  -0.0846   0.2398   1.0000
   9.750   1.4500   0.02271   0.01481  -0.0808   0.1960   1.0000
  10.000   1.4446   0.02467   0.01646  -0.0768   0.1574   1.0000
  10.250   1.4332   0.02726   0.01859  -0.0726   0.0854   1.0000
  10.500   1.4165   0.03044   0.02144  -0.0683   0.0465   1.0000
  10.750   1.4162   0.03252   0.02354  -0.0658   0.0395   1.0000
  11.000   1.4167   0.03462   0.02574  -0.0636   0.0363   1.0000
  11.250   1.4151   0.03699   0.02826  -0.0615   0.0343   1.0000
  11.500   1.4166   0.03917   0.03063  -0.0598   0.0333   1.0000
  11.750   1.4153   0.04168   0.03331  -0.0582   0.0323   1.0000
  12.000   1.4119   0.04451   0.03631  -0.0568   0.0315   1.0000
  12.250   1.4066   0.04767   0.03962  -0.0557   0.0307   1.0000
  12.500   1.3996   0.05117   0.04325  -0.0548   0.0300   1.0000
  12.750   1.3912   0.05502   0.04722  -0.0543   0.0293   1.0000
  13.000   1.3814   0.05916   0.05147  -0.0539   0.0287   1.0000
  13.250   1.3710   0.06347   0.05588  -0.0537   0.0281   1.0000
  13.500   1.3610   0.06771   0.06019  -0.0534   0.0276   1.0000
  13.750   1.3545   0.07135   0.06388  -0.0527   0.0271   1.0000
  14.000   1.3555   0.07426   0.06688  -0.0522   0.0268   1.0000
  14.250   1.3578   0.07694   0.06966  -0.0517   0.0265   1.0000
  14.500   1.3618   0.07930   0.07209  -0.0508   0.0261   1.0000
  14.750   1.3680   0.08131   0.07418  -0.0498   0.0258   1.0000
  15.000   1.3760   0.08304   0.07598  -0.0485   0.0254   1.0000
  15.250   1.3843   0.08483   0.07785  -0.0474   0.0250   1.0000
  15.500   1.3913   0.08690   0.08001  -0.0465   0.0243   1.0000
  15.750   1.3979   0.08905   0.08225  -0.0458   0.0237   1.0000
  16.000   1.4064   0.09092   0.08420  -0.0448   0.0232   1.0000
  16.250   1.4150   0.09291   0.08632  -0.0437   0.0230   1.0000
  16.500   1.4209   0.09543   0.08899  -0.0430   0.0229   1.0000
  16.750   1.4233   0.09858   0.09234  -0.0427   0.0230   1.0000
  17.000   1.4209   0.10250   0.09650  -0.0431   0.0232   1.0000
  17.250   1.4146   0.10709   0.10135  -0.0440   0.0235   1.0000
  17.500   1.4055   0.11223   0.10675  -0.0455   0.0239   1.0000
  17.750   1.3948   0.11778   0.11256  -0.0475   0.0243   1.0000
  18.000   1.3828   0.12370   0.11872  -0.0499   0.0248   1.0000
  18.250   1.3701   0.12990   0.12514  -0.0528   0.0253   1.0000
  18.500   1.3571   0.13633   0.13177  -0.0560   0.0257   1.0000
  18.750   1.3442   0.14292   0.13854  -0.0593   0.0263   1.0000
  19.000   1.3570   0.14498   0.14068  -0.0581   0.0276   1.0000
  19.250   1.3353   0.15355   0.14951  -0.0650   0.0283   1.0000
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