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GOE 563 AIRFOIL (goe563-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 563 AIRFOIL (goe563-il)
Reynolds number: 50,000
Max Cl/Cd: 35.87 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe563-il-50000.txt
Download as CSV file: xf-goe563-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 563 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4670   0.12417   0.11670  -0.0182   1.0000   0.2045
 -10.000  -0.4414   0.11829   0.11072  -0.0165   1.0000   0.2146
  -9.750  -0.4675   0.11870   0.11130  -0.0192   1.0000   0.2192
  -9.500  -0.4436   0.11312   0.10567  -0.0174   1.0000   0.2328
  -9.250  -0.4306   0.10891   0.10146  -0.0166   1.0000   0.2428
  -9.000  -0.4407   0.10693   0.09959  -0.0174   1.0000   0.2516
  -8.750  -0.4391   0.10444   0.09715  -0.0170   1.0000   0.2639
  -8.500  -0.4244   0.10029   0.09300  -0.0158   1.0000   0.2756
  -8.250  -0.4205   0.09722   0.08999  -0.0151   1.0000   0.2873
  -8.000  -0.4186   0.09448   0.08731  -0.0142   1.0000   0.3013
  -7.750  -0.4154   0.09187   0.08474  -0.0128   1.0000   0.3192
  -7.500  -0.4194   0.08983   0.08279  -0.0112   1.0000   0.3376
  -7.250  -0.4287   0.08814   0.08122  -0.0092   1.0000   0.3544
  -7.000  -0.4416   0.08666   0.07987  -0.0065   1.0000   0.3705
  -6.750  -0.4052   0.08158   0.07470  -0.0052   1.0000   0.3947
  -6.500  -0.4196   0.08035   0.07362  -0.0018   1.0000   0.4152
  -6.250  -0.3993   0.07662   0.06988   0.0001   1.0000   0.4397
  -6.000  -0.3919   0.07413   0.06744   0.0033   1.0000   0.4710
  -5.750  -0.3935   0.07240   0.06578   0.0077   1.0000   0.5070
  -5.500  -0.3679   0.06880   0.06215   0.0097   1.0000   0.5460
  -5.000  -0.4550   0.04814   0.04035  -0.0310   1.0000   0.1866
  -4.750  -0.4393   0.04366   0.03527  -0.0316   1.0000   0.1751
  -4.500  -0.4214   0.04061   0.03181  -0.0311   1.0000   0.1719
  -4.250  -0.4027   0.03769   0.02857  -0.0304   1.0000   0.1691
  -4.000  -0.3822   0.03499   0.02543  -0.0298   1.0000   0.1666
  -3.750  -0.3607   0.03275   0.02273  -0.0290   1.0000   0.1671
  -3.500  -0.3386   0.03100   0.02047  -0.0281   1.0000   0.1719
  -3.250  -0.3166   0.02926   0.01854  -0.0272   1.0000   0.1774
  -3.000  -0.2934   0.02778   0.01682  -0.0263   1.0000   0.1829
  -2.750  -0.2692   0.02643   0.01516  -0.0255   1.0000   0.1910
  -2.500  -0.2459   0.02524   0.01393  -0.0246   1.0000   0.2071
  -2.250  -0.2212   0.02403   0.01272  -0.0239   1.0000   0.2280
  -2.000  -0.1954   0.02279   0.01158  -0.0232   1.0000   0.2670
  -1.750  -0.1715   0.02157   0.01086  -0.0225   1.0000   0.3385
  -1.500  -0.1178   0.01836   0.01004  -0.0243   1.0000   1.0000
  -1.250  -0.0989   0.01854   0.00974  -0.0232   1.0000   1.0000
  -1.000  -0.0804   0.01874   0.00960  -0.0221   1.0000   1.0000
  -0.750  -0.0618   0.01898   0.00956  -0.0210   1.0000   1.0000
  -0.500  -0.0432   0.01925   0.00957  -0.0200   1.0000   1.0000
  -0.250  -0.0246   0.01956   0.00967  -0.0191   1.0000   1.0000
   0.000  -0.0060   0.01990   0.00983  -0.0183   1.0000   1.0000
   0.250   0.0125   0.02027   0.01005  -0.0175   1.0000   1.0000
   0.500   0.0309   0.02069   0.01032  -0.0167   1.0000   1.0000
   0.750   0.0492   0.02114   0.01066  -0.0160   1.0000   1.0000
   1.000   0.0673   0.02164   0.01106  -0.0154   1.0000   1.0000
   1.250   0.0852   0.02218   0.01152  -0.0148   1.0000   1.0000
   1.500   0.1028   0.02277   0.01204  -0.0142   1.0000   1.0000
   1.750   0.1202   0.02341   0.01263  -0.0138   1.0000   1.0000
   2.000   0.1372   0.02410   0.01330  -0.0134   1.0000   1.0000
   2.250   0.1538   0.02486   0.01404  -0.0130   1.0000   1.0000
   2.500   0.2134   0.02652   0.01573  -0.0208   0.9794   1.0000
   2.750   0.2745   0.02799   0.01727  -0.0283   0.9566   1.0000
   3.000   0.3248   0.02899   0.01837  -0.0335   0.9321   1.0000
   3.250   0.3800   0.02989   0.01940  -0.0391   0.9077   1.0000
   3.500   0.4359   0.03046   0.02016  -0.0441   0.8821   1.0000
   3.750   0.4846   0.03073   0.02063  -0.0475   0.8544   1.0000
   4.000   0.5371   0.03067   0.02083  -0.0508   0.8259   1.0000
   4.250   0.5973   0.03000   0.02046  -0.0543   0.7960   1.0000
   4.500   0.6664   0.02821   0.01905  -0.0573   0.7638   1.0000
   4.750   0.7190   0.02629   0.01738  -0.0570   0.7253   1.0000
   5.000   0.7662   0.02460   0.01588  -0.0559   0.6836   1.0000
   5.250   0.7999   0.02381   0.01513  -0.0537   0.6356   1.0000
   5.500   0.8299   0.02349   0.01469  -0.0513   0.5842   1.0000
   5.750   0.8536   0.02380   0.01482  -0.0487   0.5307   1.0000
   6.000   0.8766   0.02448   0.01524  -0.0463   0.4781   1.0000
   6.250   0.8956   0.02551   0.01604  -0.0438   0.4266   1.0000
   6.500   0.9118   0.02650   0.01670  -0.0409   0.3753   1.0000
   6.750   0.9250   0.02757   0.01740  -0.0380   0.3259   1.0000
   7.000   0.9399   0.02901   0.01865  -0.0356   0.2804   1.0000
   7.250   0.9541   0.03076   0.02020  -0.0330   0.2346   1.0000
   7.500   0.9703   0.03270   0.02188  -0.0308   0.1957   1.0000
   7.750   0.9905   0.03505   0.02427  -0.0292   0.1707   1.0000
   8.000   1.0120   0.03728   0.02645  -0.0280   0.1534   1.0000
   8.250   1.0316   0.04010   0.02962  -0.0265   0.1425   1.0000
   8.500   1.0485   0.04293   0.03269  -0.0249   0.1335   1.0000
   8.750   1.0650   0.04590   0.03593  -0.0234   0.1269   1.0000
   9.000   1.0788   0.04952   0.03979  -0.0218   0.1227   1.0000
   9.250   1.0789   0.05320   0.04411  -0.0188   0.1198   1.0000
   9.500   1.0775   0.05701   0.04839  -0.0161   0.1173   1.0000
   9.750   1.0725   0.06114   0.05291  -0.0136   0.1161   1.0000
  10.000   1.0600   0.06576   0.05791  -0.0110   0.1167   1.0000
  10.250   1.0401   0.07053   0.06298  -0.0086   0.1179   1.0000
  10.500   1.0148   0.07515   0.06780  -0.0064   0.1193   1.0000
  10.750   0.9902   0.08009   0.07286  -0.0053   0.1208   1.0000
  11.000   0.9691   0.08562   0.07846  -0.0058   0.1222   1.0000
  11.250   0.9579   0.09152   0.08439  -0.0067   0.1234   1.0000
  11.500   0.8808   0.10769   0.10055  -0.0192   0.1369   1.0000
  11.750   0.7868   0.14206   0.13462  -0.0494   0.2828   1.0000
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