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GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 547 AIRFOIL (goe547-il)
Reynolds number: 50,000
Max Cl/Cd: 35.24 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe547-il-50000-n5.txt
Download as CSV file: xf-goe547-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 547 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4147   0.10088   0.09410  -0.0441   1.0000   0.0770
  -8.500  -0.4191   0.09829   0.09158  -0.0424   1.0000   0.0766
  -8.250  -0.4288   0.09590   0.08928  -0.0406   1.0000   0.0762
  -8.000  -0.4453   0.09354   0.08703  -0.0391   1.0000   0.0763
  -7.750  -0.4559   0.09073   0.08430  -0.0383   1.0000   0.0761
  -7.500  -0.4654   0.08760   0.08124  -0.0380   1.0000   0.0758
  -7.250  -0.4735   0.08422   0.07790  -0.0381   1.0000   0.0755
  -7.000  -0.4803   0.08043   0.07414  -0.0387   1.0000   0.0751
  -6.750  -0.4849   0.07646   0.07016  -0.0395   1.0000   0.0744
  -6.500  -0.4876   0.07212   0.06577  -0.0407   1.0000   0.0736
  -6.250  -0.4709   0.06550   0.05891  -0.0474   0.9945   0.0727
  -6.000  -0.4506   0.05893   0.05194  -0.0540   0.9880   0.0722
  -5.750  -0.4276   0.05301   0.04545  -0.0597   0.9818   0.0741
  -5.500  -0.4008   0.04794   0.03963  -0.0644   0.9761   0.0758
  -5.250  -0.3752   0.04426   0.03535  -0.0666   0.9704   0.0762
  -5.000  -0.3455   0.04116   0.03160  -0.0689   0.9654   0.0768
  -4.750  -0.3179   0.03869   0.02866  -0.0702   0.9600   0.0777
  -4.500  -0.2890   0.03669   0.02634  -0.0714   0.9548   0.0790
  -4.250  -0.2576   0.03526   0.02468  -0.0729   0.9503   0.0824
  -4.000  -0.2312   0.03404   0.02316  -0.0733   0.9439   0.0864
  -3.750  -0.1981   0.03276   0.02144  -0.0746   0.9392   0.0896
  -3.500  -0.1690   0.03167   0.02006  -0.0750   0.9339   0.0917
  -3.250  -0.1411   0.03070   0.01904  -0.0753   0.9281   0.0950
  -3.000  -0.1070   0.02990   0.01810  -0.0767   0.9237   0.0997
  -2.750  -0.0806   0.02931   0.01728  -0.0765   0.9173   0.1054
  -2.500  -0.0503   0.02870   0.01666  -0.0774   0.9118   0.1164
  -2.250  -0.0144   0.02812   0.01614  -0.0793   0.9078   0.1374
  -2.000   0.0096   0.02765   0.01585  -0.0791   0.9005   0.1710
  -1.750   0.0421   0.02696   0.01566  -0.0806   0.8956   0.2814
  -1.500   0.0706   0.02648   0.01580  -0.0811   0.8906   0.4257
  -1.250   0.0931   0.02631   0.01588  -0.0801   0.8835   0.5191
  -1.000   0.1216   0.02586   0.01586  -0.0797   0.8790   0.6464
  -0.750   0.1680   0.02519   0.01576  -0.0828   0.8745   1.0000
  -0.500   0.1950   0.02549   0.01573  -0.0831   0.8675   1.0000
  -0.250   0.2314   0.02573   0.01566  -0.0850   0.8632   1.0000
   0.000   0.2502   0.02615   0.01587  -0.0839   0.8544   1.0000
   0.250   0.2837   0.02642   0.01590  -0.0852   0.8495   1.0000
   0.500   0.3049   0.02684   0.01617  -0.0845   0.8417   1.0000
   0.750   0.3348   0.02716   0.01633  -0.0851   0.8360   1.0000
   1.000   0.3610   0.02755   0.01658  -0.0852   0.8295   1.0000
   1.250   0.3853   0.02796   0.01688  -0.0849   0.8224   1.0000
   1.750   0.4355   0.02880   0.01756  -0.0846   0.8088   1.0000
   2.000   0.4697   0.02902   0.01772  -0.0858   0.8042   1.0000
   2.250   0.4859   0.02964   0.01830  -0.0843   0.7949   1.0000
   2.500   0.5191   0.02985   0.01850  -0.0853   0.7898   1.0000
   2.750   0.5363   0.03046   0.01909  -0.0839   0.7804   1.0000
   3.000   0.5700   0.03060   0.01925  -0.0848   0.7748   1.0000
   3.250   0.5880   0.03115   0.01981  -0.0834   0.7646   1.0000
   3.500   0.6272   0.03095   0.01966  -0.0847   0.7589   1.0000
   3.750   0.6470   0.03127   0.02003  -0.0833   0.7468   1.0000
   4.000   0.6715   0.03139   0.02020  -0.0824   0.7355   1.0000
   4.250   0.7152   0.03074   0.01965  -0.0839   0.7287   1.0000
   4.500   0.7342   0.03103   0.02003  -0.0823   0.7161   1.0000
   4.750   0.7557   0.03126   0.02035  -0.0810   0.7043   1.0000
   5.000   0.7837   0.03122   0.02044  -0.0805   0.6942   1.0000
   5.250   0.8187   0.03089   0.02027  -0.0808   0.6853   1.0000
   5.500   0.8389   0.03116   0.02067  -0.0793   0.6727   1.0000
   5.750   0.8625   0.03125   0.02091  -0.0781   0.6603   1.0000
   6.000   0.8898   0.03109   0.02095  -0.0773   0.6473   1.0000
   6.250   0.9178   0.03082   0.02085  -0.0764   0.6330   1.0000
   6.500   0.9444   0.03049   0.02070  -0.0751   0.6161   1.0000
   6.750   0.9727   0.03001   0.02038  -0.0739   0.5971   1.0000
   7.000   0.9928   0.02985   0.02040  -0.0716   0.5747   1.0000
   7.250   1.0134   0.02968   0.02036  -0.0695   0.5500   1.0000
   7.500   1.0266   0.02995   0.02075  -0.0666   0.5227   1.0000
   7.750   1.0436   0.03017   0.02110  -0.0643   0.4951   1.0000
   8.000   1.0622   0.03029   0.02131  -0.0621   0.4633   1.0000
   8.250   1.0772   0.03057   0.02151  -0.0593   0.4240   1.0000
   8.500   1.0884   0.03121   0.02194  -0.0564   0.3818   1.0000
   8.750   1.0951   0.03228   0.02279  -0.0533   0.3424   1.0000
   9.000   1.1005   0.03360   0.02397  -0.0504   0.3090   1.0000
   9.250   1.1051   0.03509   0.02539  -0.0477   0.2786   1.0000
   9.500   1.1070   0.03680   0.02701  -0.0449   0.2474   1.0000
   9.750   1.1061   0.03875   0.02889  -0.0423   0.2144   1.0000
  10.000   1.1040   0.04089   0.03090  -0.0400   0.1805   1.0000
  10.250   1.1006   0.04328   0.03305  -0.0379   0.1493   1.0000
  10.500   1.0981   0.04586   0.03541  -0.0361   0.1250   1.0000
  10.750   1.0965   0.04857   0.03799  -0.0344   0.1075   1.0000
  11.000   1.0963   0.05130   0.04071  -0.0329   0.0917   1.0000
  11.250   1.0987   0.05388   0.04334  -0.0315   0.0778   1.0000
  11.500   1.1011   0.05650   0.04601  -0.0304   0.0688   1.0000
  11.750   1.1061   0.05904   0.04865  -0.0291   0.0624   1.0000
  12.000   1.1092   0.06171   0.05133  -0.0281   0.0571   1.0000
  12.250   1.1170   0.06417   0.05398  -0.0270   0.0527   1.0000
  12.500   1.1264   0.06659   0.05664  -0.0259   0.0487   1.0000
  12.750   1.1366   0.06903   0.05921  -0.0249   0.0462   1.0000
  13.000   1.1482   0.07158   0.06178  -0.0239   0.0438   1.0000
  13.250   1.1526   0.07490   0.06548  -0.0233   0.0423   1.0000
  13.500   1.1519   0.07870   0.06963  -0.0230   0.0408   1.0000
  13.750   1.1470   0.08286   0.07408  -0.0231   0.0396   1.0000
  14.000   1.1396   0.08738   0.07887  -0.0237   0.0387   1.0000
  14.250   1.1297   0.09232   0.08407  -0.0247   0.0379   1.0000
  14.500   1.1175   0.09781   0.08980  -0.0263   0.0376   1.0000
  14.750   1.1022   0.10405   0.09629  -0.0287   0.0374   1.0000
  15.000   1.0830   0.11144   0.10392  -0.0322   0.0375   1.0000
  15.250   1.0587   0.12058   0.11331  -0.0374   0.0381   1.0000
  15.500   1.0286   0.13238   0.12533  -0.0447   0.0391   1.0000
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