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GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 693 AIRFOIL (goe693-il)
Reynolds number: 50,000
Max Cl/Cd: 35.62 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe693-il-50000-n5.txt
Download as CSV file: xf-goe693-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 693 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  -0.3805   0.10327   0.09580  -0.0433   1.0000   0.0855
  -9.250  -0.3838   0.09997   0.09256  -0.0438   1.0000   0.0860
  -9.000  -0.3899   0.09664   0.08932  -0.0443   1.0000   0.0863
  -8.750  -0.3996   0.09330   0.08608  -0.0444   1.0000   0.0861
  -8.500  -0.4144   0.08997   0.08288  -0.0442   1.0000   0.0855
  -8.250  -0.4360   0.08662   0.07967  -0.0437   1.0000   0.0847
  -8.000  -0.4584   0.08218   0.07533  -0.0446   1.0000   0.0836
  -7.750  -0.4857   0.07635   0.06953  -0.0463   1.0000   0.0823
  -7.500  -0.5094   0.07017   0.06325  -0.0475   1.0000   0.0814
  -7.250  -0.5203   0.06573   0.05867  -0.0472   1.0000   0.0813
  -7.000  -0.5233   0.06240   0.05522  -0.0462   1.0000   0.0817
  -6.750  -0.5210   0.06000   0.05274  -0.0449   1.0000   0.0825
  -6.500  -0.4966   0.05733   0.04990  -0.0476   0.9943   0.0851
  -6.250  -0.4724   0.05302   0.04520  -0.0515   0.9871   0.0880
  -6.000  -0.4474   0.04818   0.03979  -0.0553   0.9802   0.0901
  -5.750  -0.4195   0.04373   0.03464  -0.0586   0.9739   0.0922
  -5.500  -0.3918   0.04059   0.03092  -0.0606   0.9672   0.0951
  -5.250  -0.3601   0.03936   0.02961  -0.0625   0.9613   0.0994
  -5.000  -0.3307   0.03744   0.02728  -0.0640   0.9546   0.1043
  -4.750  -0.2982   0.03514   0.02429  -0.0657   0.9486   0.1089
  -4.500  -0.2656   0.03410   0.02325  -0.0674   0.9433   0.1144
  -4.250  -0.2371   0.03299   0.02179  -0.0681   0.9359   0.1224
  -4.000  -0.2023   0.03189   0.02056  -0.0700   0.9310   0.1298
  -3.750  -0.1733   0.03110   0.01943  -0.0705   0.9240   0.1405
  -3.500  -0.1419   0.03040   0.01877  -0.0717   0.9179   0.1503
  -3.250  -0.1049   0.02972   0.01798  -0.0737   0.9138   0.1639
  -3.000  -0.0801   0.02926   0.01741  -0.0735   0.9055   0.1758
  -2.750  -0.0451   0.02878   0.01686  -0.0750   0.9006   0.1912
  -2.500  -0.0153   0.02843   0.01645  -0.0757   0.8943   0.2067
  -2.250   0.0155   0.02809   0.01606  -0.0765   0.8879   0.2230
  -2.000   0.0526   0.02764   0.01565  -0.0784   0.8837   0.2438
  -1.750   0.0766   0.02743   0.01547  -0.0780   0.8758   0.2637
  -1.500   0.1102   0.02698   0.01516  -0.0793   0.8706   0.2958
  -1.250   0.1392   0.02652   0.01499  -0.0799   0.8647   0.3479
  -1.000   0.1636   0.02587   0.01495  -0.0795   0.8578   0.4582
  -0.750   0.2178   0.02454   0.01501  -0.0826   0.8551   0.9869
  -0.500   0.2450   0.02480   0.01498  -0.0828   0.8475   1.0000
  -0.250   0.2745   0.02499   0.01492  -0.0833   0.8406   1.0000
   0.000   0.3018   0.02522   0.01494  -0.0833   0.8334   1.0000
   0.500   0.3574   0.02559   0.01497  -0.0834   0.8171   1.0000
   0.750   0.3902   0.02554   0.01478  -0.0839   0.8084   1.0000
   1.000   0.4153   0.02567   0.01479  -0.0832   0.7971   1.0000
   1.250   0.4540   0.02541   0.01440  -0.0845   0.7902   1.0000
   1.500   0.4747   0.02569   0.01462  -0.0832   0.7783   1.0000
   1.750   0.5015   0.02584   0.01469  -0.0828   0.7691   1.0000
   2.000   0.5311   0.02591   0.01470  -0.0828   0.7609   1.0000
   2.250   0.5540   0.02622   0.01498  -0.0819   0.7508   1.0000
   2.500   0.5864   0.02619   0.01490  -0.0823   0.7436   1.0000
   2.750   0.6072   0.02658   0.01529  -0.0811   0.7324   1.0000
   3.000   0.6416   0.02645   0.01513  -0.0816   0.7257   1.0000
   3.250   0.6615   0.02687   0.01559  -0.0803   0.7138   1.0000
   3.500   0.6854   0.02715   0.01589  -0.0795   0.7031   1.0000
   3.750   0.7177   0.02706   0.01580  -0.0796   0.6949   1.0000
   4.000   0.7382   0.02744   0.01623  -0.0783   0.6821   1.0000
   4.250   0.7619   0.02766   0.01649  -0.0773   0.6699   1.0000
   4.500   0.7895   0.02766   0.01653  -0.0767   0.6583   1.0000
   4.750   0.8193   0.02750   0.01642  -0.0763   0.6466   1.0000
   5.000   0.8416   0.02766   0.01662  -0.0749   0.6317   1.0000
   5.250   0.8644   0.02776   0.01678  -0.0736   0.6165   1.0000
   5.500   0.8871   0.02787   0.01696  -0.0723   0.6010   1.0000
   5.750   0.9096   0.02799   0.01714  -0.0710   0.5853   1.0000
   6.000   0.9322   0.02810   0.01731  -0.0696   0.5690   1.0000
   6.250   0.9546   0.02823   0.01750  -0.0683   0.5526   1.0000
   6.500   0.9755   0.02846   0.01778  -0.0668   0.5356   1.0000
   6.750   0.9953   0.02879   0.01819  -0.0653   0.5185   1.0000
   7.000   1.0158   0.02914   0.01861  -0.0638   0.5019   1.0000
   7.250   1.0362   0.02950   0.01905  -0.0624   0.4851   1.0000
   7.500   1.0567   0.02989   0.01949  -0.0610   0.4684   1.0000
   7.750   1.0772   0.03033   0.01998  -0.0596   0.4519   1.0000
   8.000   1.0966   0.03081   0.02048  -0.0581   0.4343   1.0000
   8.250   1.1153   0.03131   0.02100  -0.0564   0.4156   1.0000
   8.500   1.1329   0.03190   0.02155  -0.0547   0.3966   1.0000
   8.750   1.1459   0.03274   0.02243  -0.0525   0.3770   1.0000
   9.000   1.1582   0.03361   0.02332  -0.0503   0.3579   1.0000
   9.250   1.1687   0.03455   0.02426  -0.0479   0.3395   1.0000
   9.500   1.1790   0.03558   0.02533  -0.0455   0.3222   1.0000
   9.750   1.1896   0.03670   0.02651  -0.0434   0.3064   1.0000
  10.000   1.1999   0.03789   0.02779  -0.0414   0.2917   1.0000
  10.250   1.2106   0.03914   0.02914  -0.0395   0.2782   1.0000
  10.500   1.2210   0.04043   0.03053  -0.0377   0.2655   1.0000
  10.750   1.2302   0.04176   0.03198  -0.0358   0.2533   1.0000
  11.000   1.2384   0.04315   0.03342  -0.0339   0.2415   1.0000
  11.250   1.2434   0.04477   0.03518  -0.0320   0.2294   1.0000
  11.500   1.2450   0.04658   0.03707  -0.0301   0.2167   1.0000
  11.750   1.2430   0.04862   0.03913  -0.0281   0.2034   1.0000
  12.000   1.2387   0.05092   0.04142  -0.0265   0.1897   1.0000
  12.250   1.2337   0.05351   0.04399  -0.0251   0.1762   1.0000
  12.500   1.2294   0.05626   0.04677  -0.0240   0.1636   1.0000
  12.750   1.2262   0.05906   0.04962  -0.0230   0.1524   1.0000
  13.000   1.2213   0.06217   0.05284  -0.0224   0.1415   1.0000
  13.250   1.2146   0.06576   0.05666  -0.0221   0.1306   1.0000
  13.500   1.2074   0.06949   0.06057  -0.0221   0.1202   1.0000
  13.750   1.1999   0.07337   0.06455  -0.0223   0.1108   1.0000
  14.000   1.1918   0.07739   0.06861  -0.0228   0.1025   1.0000
  14.250   1.1837   0.08175   0.07306  -0.0234   0.0943   1.0000
  14.500   1.1760   0.08602   0.07729  -0.0241   0.0879   1.0000
  14.750   1.1688   0.09045   0.08179  -0.0248   0.0817   1.0000
  15.000   1.1631   0.09462   0.08591  -0.0255   0.0768   1.0000
  15.250   1.1552   0.09966   0.09120  -0.0268   0.0719   1.0000
  15.500   1.1501   0.10400   0.09556  -0.0279   0.0679   1.0000
  15.750   1.1448   0.10862   0.10027  -0.0291   0.0648   1.0000
  16.000   1.1347   0.11465   0.10658  -0.0314   0.0623   1.0000
  16.250   1.1248   0.12074   0.11289  -0.0339   0.0602   1.0000
  16.500   1.1165   0.12657   0.11885  -0.0365   0.0583   1.0000
  16.750   1.1204   0.12930   0.12150  -0.0373   0.0558   1.0000
  17.000   1.1010   0.13842   0.13089  -0.0422   0.0551   1.0000
  17.250   1.0757   0.14976   0.14246  -0.0488   0.0548   1.0000
  17.500   1.0429   0.16455   0.15737  -0.0575   0.0549   1.0000
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