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GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 533 AIRFOIL (goe533-il)
Reynolds number: 50,000
Max Cl/Cd: 29.45 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe533-il-50000-n5.txt
Download as CSV file: xf-goe533-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 533 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2585   0.11203   0.10520  -0.0386   1.0000   0.1485
  -9.250  -0.2801   0.11118   0.10454  -0.0401   1.0000   0.1501
  -9.000  -0.2933   0.10939   0.10294  -0.0403   1.0000   0.1504
  -8.500  -0.3049   0.09641   0.09002  -0.0429   1.0000   0.0884
  -8.250  -0.3057   0.09466   0.08838  -0.0401   1.0000   0.0873
  -8.000  -0.3114   0.09254   0.08638  -0.0395   0.9965   0.0866
  -7.750  -0.2929   0.08762   0.08146  -0.0458   0.9814   0.0853
  -7.250  -0.2786   0.06940   0.06292  -0.0736   0.9403   0.0770
  -7.000  -0.2573   0.06483   0.05822  -0.0786   0.9269   0.0762
  -6.750  -0.2369   0.05987   0.05305  -0.0844   0.9136   0.0753
  -6.500  -0.2142   0.05478   0.04763  -0.0903   0.9019   0.0746
  -6.250  -0.1928   0.05036   0.04280  -0.0946   0.8887   0.0749
  -6.000  -0.1711   0.04661   0.03855  -0.0977   0.8754   0.0757
  -5.750  -0.1441   0.04320   0.03456  -0.1005   0.8648   0.0764
  -5.500  -0.1158   0.04045   0.03134  -0.1024   0.8542   0.0767
  -5.250  -0.0890   0.03817   0.02861  -0.1034   0.8430   0.0770
  -5.000  -0.0570   0.03603   0.02613  -0.1048   0.8344   0.0777
  -4.750  -0.0314   0.03456   0.02447  -0.1049   0.8230   0.0788
  -4.500   0.0016   0.03315   0.02286  -0.1059   0.8152   0.0814
  -4.250   0.0264   0.03210   0.02158  -0.1056   0.8036   0.0839
  -4.000   0.0570   0.03089   0.02006  -0.1058   0.7950   0.0863
  -3.750   0.0843   0.02992   0.01883  -0.1054   0.7849   0.0880
  -3.500   0.1121   0.02900   0.01781  -0.1050   0.7760   0.0901
  -3.250   0.1391   0.02827   0.01702  -0.1046   0.7666   0.0935
  -3.000   0.1657   0.02771   0.01632  -0.1040   0.7574   0.0990
  -2.750   0.1935   0.02706   0.01558  -0.1037   0.7486   0.1049
  -2.500   0.2190   0.02656   0.01502  -0.1032   0.7393   0.1116
  -2.250   0.2472   0.02597   0.01435  -0.1031   0.7308   0.1220
  -2.000   0.2729   0.02545   0.01387  -0.1029   0.7215   0.1420
  -1.750   0.3017   0.02436   0.01324  -0.1035   0.7133   0.2208
  -1.500   0.3214   0.02357   0.01358  -0.1020   0.7043   0.4980
  -1.250   0.3404   0.02357   0.01390  -0.0990   0.6961   0.6201
  -1.000   0.3543   0.02369   0.01420  -0.0950   0.6876   0.7157
  -0.750   0.3667   0.02353   0.01421  -0.0903   0.6794   0.7873
  -0.500   0.3856   0.02329   0.01401  -0.0872   0.6719   0.8466
  -0.250   0.4201   0.02317   0.01385  -0.0878   0.6625   0.9041
   0.000   0.4722   0.02309   0.01352  -0.0925   0.6542   1.0000
   0.250   0.4972   0.02345   0.01365  -0.0929   0.6448   1.0000
   0.500   0.5286   0.02363   0.01353  -0.0938   0.6379   1.0000
   0.750   0.5520   0.02413   0.01388  -0.0938   0.6279   1.0000
   1.000   0.5836   0.02431   0.01380  -0.0944   0.6213   1.0000
   1.250   0.6055   0.02491   0.01430  -0.0941   0.6115   1.0000
   1.500   0.6351   0.02517   0.01435  -0.0944   0.6046   1.0000
   1.750   0.6580   0.02575   0.01484  -0.0940   0.5957   1.0000
   2.000   0.6848   0.02613   0.01508  -0.0939   0.5883   1.0000
   2.250   0.7103   0.02660   0.01544  -0.0937   0.5809   1.0000
   2.500   0.7332   0.02718   0.01595  -0.0933   0.5725   1.0000
   2.750   0.7638   0.02738   0.01599  -0.0934   0.5671   1.0000
   3.000   0.7805   0.02830   0.01695  -0.0924   0.5575   1.0000
   3.250   0.8085   0.02862   0.01716  -0.0923   0.5515   1.0000
   3.500   0.8280   0.02942   0.01796  -0.0915   0.5435   1.0000
   3.750   0.8518   0.02997   0.01848  -0.0911   0.5366   1.0000
   4.000   0.8803   0.03027   0.01869  -0.0910   0.5314   1.0000
   4.250   0.8938   0.03144   0.01994  -0.0897   0.5225   1.0000
   4.500   0.9218   0.03174   0.02019  -0.0895   0.5173   1.0000
   4.750   0.9370   0.03283   0.02134  -0.0884   0.5096   1.0000
   5.000   0.9586   0.03351   0.02203  -0.0877   0.5031   1.0000
   5.250   0.9900   0.03362   0.02209  -0.0878   0.4989   1.0000
   5.500   0.9947   0.03533   0.02393  -0.0858   0.4896   1.0000
   5.750   1.0243   0.03540   0.02397  -0.0856   0.4841   1.0000
   6.000   1.0334   0.03674   0.02541  -0.0838   0.4753   1.0000
   6.250   1.0606   0.03680   0.02545  -0.0833   0.4685   1.0000
   6.500   1.0725   0.03780   0.02651  -0.0816   0.4595   1.0000
   6.750   1.0986   0.03784   0.02656  -0.0809   0.4522   1.0000
   7.000   1.1096   0.03891   0.02771  -0.0792   0.4438   1.0000
   7.250   1.1294   0.03945   0.02829  -0.0782   0.4366   1.0000
   7.500   1.1535   0.03984   0.02870  -0.0775   0.4309   1.0000
   7.750   1.1489   0.04201   0.03103  -0.0748   0.4223   1.0000
   8.000   1.1845   0.04163   0.03065  -0.0750   0.4175   1.0000
   8.250   1.1603   0.04495   0.03412  -0.0708   0.4081   1.0000
   8.500   1.1874   0.04503   0.03425  -0.0703   0.4025   1.0000
   8.750   1.1709   0.04823   0.03756  -0.0675   0.3940   1.0000
   9.000   1.1797   0.04970   0.03912  -0.0662   0.3871   1.0000
   9.250   1.2256   0.04839   0.03786  -0.0664   0.3836   1.0000
   9.500   1.1634   0.05613   0.04574  -0.0636   0.3705   1.0000
   9.750   1.2047   0.05470   0.04437  -0.0629   0.3675   1.0000
  10.000   1.1471   0.06364   0.05343  -0.0627   0.3531   1.0000
  10.250   1.1867   0.06193   0.05179  -0.0614   0.3506   1.0000
  10.750   1.1716   0.06975   0.05978  -0.0611   0.3335   1.0000
  11.250   1.1518   0.07909   0.06930  -0.0620   0.3166   1.0000
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