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GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 593 AIRFOIL (goe593-il)
Reynolds number: 50,000
Max Cl/Cd: 35.23 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe593-il-50000-n5.txt
Download as CSV file: xf-goe593-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 593 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3562   0.10286   0.09589  -0.0421   1.0000   0.0740
  -9.000  -0.3620   0.09991   0.09304  -0.0414   1.0000   0.0733
  -8.750  -0.3695   0.09711   0.09033  -0.0405   1.0000   0.0723
  -8.500  -0.3807   0.09437   0.08770  -0.0395   1.0000   0.0713
  -8.250  -0.3961   0.09176   0.08521  -0.0382   1.0000   0.0705
  -8.000  -0.4159   0.08931   0.08288  -0.0366   1.0000   0.0696
  -7.750  -0.4348   0.08621   0.07989  -0.0359   1.0000   0.0688
  -7.500  -0.4514   0.08258   0.07632  -0.0359   1.0000   0.0680
  -7.250  -0.4650   0.07891   0.07268  -0.0357   1.0000   0.0678
  -7.000  -0.4769   0.07486   0.06860  -0.0358   1.0000   0.0674
  -6.750  -0.4808   0.07124   0.06492  -0.0360   0.9993   0.0682
  -6.500  -0.4631   0.06570   0.05915  -0.0413   0.9915   0.0698
  -6.250  -0.4454   0.05984   0.05294  -0.0461   0.9839   0.0704
  -6.000  -0.4266   0.05451   0.04716  -0.0497   0.9764   0.0709
  -5.750  -0.4070   0.04979   0.04185  -0.0522   0.9688   0.0734
  -5.500  -0.3832   0.04529   0.03655  -0.0544   0.9623   0.0756
  -5.250  -0.3597   0.04255   0.03347  -0.0552   0.9552   0.0771
  -5.000  -0.3309   0.04075   0.03146  -0.0566   0.9494   0.0797
  -4.750  -0.3056   0.03898   0.02934  -0.0570   0.9420   0.0836
  -4.500  -0.2729   0.03673   0.02646  -0.0585   0.9371   0.0872
  -4.250  -0.2485   0.03506   0.02441  -0.0583   0.9294   0.0895
  -4.000  -0.2162   0.03402   0.02327  -0.0596   0.9237   0.0944
  -3.750  -0.1888   0.03301   0.02193  -0.0597   0.9167   0.1002
  -3.500  -0.1577   0.03191   0.02063  -0.0604   0.9103   0.1053
  -3.250  -0.1222   0.03106   0.01966  -0.0618   0.9054   0.1134
  -3.000  -0.0977   0.03044   0.01894  -0.0613   0.8970   0.1228
  -2.750  -0.0605   0.02968   0.01806  -0.0630   0.8918   0.1373
  -2.500  -0.0332   0.02918   0.01754  -0.0631   0.8840   0.1557
  -2.000   0.0303   0.02811   0.01661  -0.0649   0.8708   0.2199
  -1.750   0.0572   0.02765   0.01635  -0.0650   0.8625   0.2688
  -1.500   0.0930   0.02664   0.01591  -0.0666   0.8576   0.3678
  -1.250   0.1863   0.02487   0.01592  -0.0774   0.8580   1.0000
  -1.000   0.2056   0.02506   0.01581  -0.0760   0.8464   1.0000
  -0.750   0.2387   0.02508   0.01552  -0.0769   0.8385   1.0000
  -0.500   0.2661   0.02516   0.01535  -0.0767   0.8287   1.0000
  -0.250   0.2914   0.02527   0.01524  -0.0762   0.8183   1.0000
   0.000   0.3303   0.02513   0.01489  -0.0779   0.8108   1.0000
   0.250   0.3520   0.02527   0.01486  -0.0766   0.7988   1.0000
   0.500   0.3824   0.02524   0.01468  -0.0768   0.7889   1.0000
   0.750   0.4175   0.02509   0.01438  -0.0776   0.7798   1.0000
   1.000   0.4402   0.02520   0.01437  -0.0765   0.7676   1.0000
   1.250   0.4693   0.02515   0.01422  -0.0763   0.7571   1.0000
   1.500   0.5044   0.02494   0.01391  -0.0770   0.7478   1.0000
   1.750   0.5268   0.02505   0.01394  -0.0757   0.7350   1.0000
   2.000   0.5528   0.02507   0.01389  -0.0750   0.7230   1.0000
   2.250   0.5862   0.02488   0.01363  -0.0753   0.7125   1.0000
   2.500   0.6148   0.02481   0.01351  -0.0749   0.7003   1.0000
   2.750   0.6381   0.02489   0.01355  -0.0737   0.6864   1.0000
   3.000   0.6627   0.02495   0.01357  -0.0727   0.6725   1.0000
   3.250   0.6884   0.02498   0.01357  -0.0718   0.6586   1.0000
   3.500   0.7145   0.02501   0.01357  -0.0710   0.6443   1.0000
   3.750   0.7403   0.02505   0.01358  -0.0702   0.6295   1.0000
   4.000   0.7655   0.02513   0.01365  -0.0693   0.6145   1.0000
   4.250   0.7896   0.02526   0.01375  -0.0682   0.5988   1.0000
   4.500   0.8126   0.02544   0.01391  -0.0670   0.5826   1.0000
   4.750   0.8353   0.02566   0.01413  -0.0658   0.5666   1.0000
   5.000   0.8577   0.02592   0.01437  -0.0646   0.5506   1.0000
   5.250   0.8797   0.02622   0.01465  -0.0634   0.5346   1.0000
   5.500   0.9021   0.02654   0.01496  -0.0623   0.5193   1.0000
   5.750   0.9248   0.02690   0.01531  -0.0612   0.5045   1.0000
   6.000   0.9483   0.02727   0.01565  -0.0603   0.4906   1.0000
   6.500   0.9903   0.02831   0.01675  -0.0580   0.4641   1.0000
   6.750   1.0114   0.02890   0.01737  -0.0570   0.4521   1.0000
   7.000   1.0352   0.02945   0.01793  -0.0563   0.4410   1.0000
   7.250   1.0583   0.03004   0.01858  -0.0556   0.4305   1.0000
   7.500   1.0769   0.03084   0.01948  -0.0543   0.4203   1.0000
   7.750   1.1026   0.03145   0.02011  -0.0540   0.4113   1.0000
   8.000   1.1197   0.03232   0.02112  -0.0526   0.4019   1.0000
   8.250   1.1417   0.03310   0.02200  -0.0518   0.3934   1.0000
   8.500   1.1607   0.03397   0.02300  -0.0507   0.3850   1.0000
   8.750   1.1799   0.03487   0.02403  -0.0496   0.3771   1.0000
   9.000   1.1982   0.03575   0.02506  -0.0484   0.3685   1.0000
   9.250   1.2111   0.03673   0.02619  -0.0464   0.3595   1.0000
   9.500   1.2291   0.03725   0.02673  -0.0449   0.3482   1.0000
   9.750   1.2330   0.03802   0.02758  -0.0415   0.3360   1.0000
  10.000   1.2322   0.03895   0.02863  -0.0376   0.3241   1.0000
  10.250   1.2356   0.03979   0.02953  -0.0344   0.3123   1.0000
  10.500   1.2437   0.04050   0.03029  -0.0319   0.3009   1.0000
  10.750   1.2424   0.04190   0.03189  -0.0288   0.2914   1.0000
  11.000   1.2455   0.04315   0.03327  -0.0263   0.2817   1.0000
  11.250   1.2528   0.04409   0.03428  -0.0242   0.2715   1.0000
  11.500   1.2447   0.04619   0.03662  -0.0213   0.2620   1.0000
  11.750   1.2444   0.04775   0.03829  -0.0191   0.2517   1.0000
  12.000   1.2437   0.04938   0.04005  -0.0171   0.2410   1.0000
  12.250   1.2327   0.05216   0.04304  -0.0152   0.2305   1.0000
  12.500   1.2269   0.05458   0.04558  -0.0137   0.2195   1.0000
  12.750   1.2228   0.05692   0.04799  -0.0125   0.2080   1.0000
  13.000   1.2137   0.06005   0.05124  -0.0116   0.1965   1.0000
  13.250   1.2014   0.06388   0.05523  -0.0113   0.1850   1.0000
  13.500   1.1918   0.06758   0.05901  -0.0111   0.1740   1.0000
  13.750   1.1850   0.07103   0.06249  -0.0111   0.1636   1.0000
  14.000   1.1799   0.07439   0.06587  -0.0111   0.1543   1.0000
  14.250   1.1682   0.07914   0.07073  -0.0119   0.1463   1.0000
  14.500   1.1672   0.08211   0.07364  -0.0120   0.1387   1.0000
  14.750   1.1551   0.08729   0.07899  -0.0133   0.1324   1.0000
  15.000   1.1575   0.08988   0.08149  -0.0133   0.1260   1.0000
  15.250   1.1415   0.09617   0.08801  -0.0154   0.1214   1.0000
  15.500   1.1431   0.09910   0.09095  -0.0158   0.1159   1.0000
  15.750   1.1338   0.10431   0.09627  -0.0175   0.1116   1.0000
  16.000   1.1109   0.11257   0.10475  -0.0211   0.1085   1.0000
  16.250   1.1158   0.11496   0.10713  -0.0215   0.1032   1.0000
  16.500   1.1060   0.12071   0.11297  -0.0239   0.0997   1.0000
  16.750   1.0580   0.13578   0.12822  -0.0320   0.0988   1.0000
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