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GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 511 AIRFOIL (goe511-il)
Reynolds number: 200,000
Max Cl/Cd: 57.64 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe511-il-200000.txt
Download as CSV file: xf-goe511-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 511 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000   0.0500   0.09612   0.09267  -0.0964   0.9265   0.0640
  -8.750   0.0445   0.09278   0.08934  -0.1009   0.9176   0.0673
  -8.500   0.0455   0.08804   0.08462  -0.1061   0.9107   0.0684
  -8.250   0.0852   0.08472   0.08128  -0.1075   0.9091   0.0699
  -8.000   0.1132   0.08095   0.07750  -0.1123   0.9071   0.0725
  -7.250   0.1962   0.05711   0.05380  -0.1199   0.8580   0.0835
  -7.000   0.0990   0.06870   0.06525  -0.1132   0.8617   0.0789
  -6.750   0.1224   0.06531   0.06181  -0.1161   0.8567   0.0816
  -6.250   0.1028   0.05892   0.05523  -0.1133   0.8233   0.0873
  -6.000   0.1183   0.05690   0.05320  -0.1118   0.8082   0.0885
  -5.750   0.1415   0.05443   0.05065  -0.1128   0.7930   0.0915
  -5.500   0.1578   0.05008   0.04601  -0.1159   0.7768   0.0987
  -5.250   0.2039   0.04755   0.04334  -0.1206   0.7593   0.1019
  -5.000   0.2295   0.04371   0.03907  -0.1242   0.7397   0.1110
  -4.750   0.2638   0.04194   0.03711  -0.1264   0.7183   0.1134
  -4.500   0.2837   0.04050   0.03543  -0.1260   0.6984   0.1186
  -4.250   0.2341   0.02715   0.02043  -0.1140   0.6926   0.0756
  -4.000   0.2526   0.02538   0.01835  -0.1124   0.6768   0.0743
  -3.750   0.2642   0.02382   0.01645  -0.1090   0.6616   0.0725
  -3.500   0.2757   0.02203   0.01403  -0.1052   0.6484   0.0695
  -3.250   0.2961   0.02114   0.01275  -0.1033   0.6358   0.0689
  -3.000   0.3150   0.02048   0.01184  -0.1012   0.6234   0.0688
  -2.750   0.3338   0.01986   0.01106  -0.0991   0.6118   0.0691
  -2.250   0.3766   0.01901   0.00996  -0.0961   0.5908   0.0715
  -2.000   0.4053   0.01871   0.00946  -0.0961   0.5817   0.0733
  -1.750   0.4237   0.01840   0.00909  -0.0939   0.5724   0.0745
  -1.500   0.4557   0.01817   0.00866  -0.0946   0.5639   0.0759
  -1.250   0.4729   0.01782   0.00835  -0.0923   0.5554   0.0776
  -1.000   0.4982   0.01764   0.00814  -0.0917   0.5473   0.0802
  -0.750   0.5197   0.01756   0.00803  -0.0903   0.5394   0.0837
  -0.500   0.5382   0.01742   0.00789  -0.0882   0.5316   0.0882
  -0.250   0.5680   0.01742   0.00779  -0.0886   0.5241   0.0958
   0.000   0.5801   0.01727   0.00772  -0.0852   0.5167   0.1045
   0.250   0.5994   0.01696   0.00774  -0.0835   0.5100   0.1686
   0.500   0.6262   0.01741   0.00817  -0.0832   0.5033   0.2520
   0.750   0.6401   0.01758   0.00835  -0.0803   0.4964   0.2697
   1.000   0.6622   0.01778   0.00847  -0.0791   0.4902   0.2860
   1.250   0.6875   0.01801   0.00863  -0.0787   0.4841   0.3023
   1.750   0.7215   0.01824   0.00885  -0.0744   0.4721   0.3271
   2.000   0.7502   0.01842   0.00895  -0.0747   0.4663   0.3429
   2.250   0.7605   0.01849   0.00912  -0.0713   0.4607   0.3559
   2.500   0.7789   0.01860   0.00921  -0.0695   0.4553   0.3679
   2.750   0.8022   0.01864   0.00924  -0.0686   0.4507   0.3787
   3.000   0.8236   0.01880   0.00939  -0.0675   0.4462   0.3899
   3.250   0.8363   0.01890   0.00957  -0.0646   0.4416   0.4022
   3.500   1.1381   0.01990   0.01154  -0.1229   0.4281   1.0000
   3.750   1.1496   0.02014   0.01179  -0.1198   0.4245   1.0000
   4.000   1.1629   0.02036   0.01199  -0.1171   0.4207   1.0000
   4.250   1.1792   0.02059   0.01215  -0.1151   0.4173   1.0000
   4.500   1.2019   0.02088   0.01233  -0.1143   0.4140   1.0000
   4.750   1.2265   0.02128   0.01265  -0.1140   0.4107   1.0000
   5.000   1.2334   0.02153   0.01297  -0.1101   0.4078   1.0000
   5.250   1.2456   0.02181   0.01327  -0.1073   0.4049   1.0000
   5.500   1.2611   0.02211   0.01355  -0.1051   0.4020   1.0000
   5.750   1.2799   0.02240   0.01380  -0.1036   0.3994   1.0000
   6.000   1.3039   0.02274   0.01409  -0.1033   0.3969   1.0000
   6.250   1.3433   0.02333   0.01455  -0.1061   0.3941   1.0000
   6.500   1.3470   0.02366   0.01497  -0.1017   0.3921   1.0000
   6.750   1.3534   0.02401   0.01541  -0.0978   0.3896   1.0000
   7.000   1.3638   0.02438   0.01583  -0.0948   0.3871   1.0000
   7.250   1.3762   0.02469   0.01615  -0.0923   0.3841   1.0000
   7.500   1.3941   0.02499   0.01642  -0.0907   0.3814   1.0000
   7.750   1.4201   0.02529   0.01663  -0.0908   0.3784   1.0000
   8.000   1.4431   0.02583   0.01715  -0.0904   0.3756   1.0000
   8.250   1.4416   0.02625   0.01769  -0.0854   0.3732   1.0000
   8.500   1.4461   0.02670   0.01822  -0.0815   0.3705   1.0000
   8.750   1.4547   0.02707   0.01863  -0.0785   0.3673   1.0000
   9.000   1.4704   0.02736   0.01891  -0.0767   0.3643   1.0000
   9.250   1.4947   0.02767   0.01917  -0.0766   0.3617   1.0000
   9.500   1.5302   0.02823   0.01964  -0.0786   0.3590   1.0000
   9.750   1.5252   0.02885   0.02043  -0.0733   0.3570   1.0000
  10.000   1.5240   0.02953   0.02124  -0.0690   0.3546   1.0000
  10.250   1.5281   0.03017   0.02198  -0.0656   0.3519   1.0000
  10.500   1.5384   0.03076   0.02261  -0.0633   0.3495   1.0000
  10.750   1.5548   0.03115   0.02301  -0.0620   0.3468   1.0000
  11.000   1.5806   0.03146   0.02328  -0.0622   0.3444   1.0000
  11.250   1.6156   0.03197   0.02372  -0.0640   0.3418   1.0000
  11.500   1.6019   0.03299   0.02495  -0.0581   0.3396   1.0000
  11.750   1.5933   0.03411   0.02622  -0.0534   0.3372   1.0000
  12.000   1.5906   0.03513   0.02738  -0.0497   0.3343   1.0000
  12.250   1.5982   0.03585   0.02815  -0.0475   0.3315   1.0000
  12.500   1.6190   0.03612   0.02839  -0.0470   0.3286   1.0000
  12.750   1.6590   0.03603   0.02820  -0.0492   0.3256   1.0000
  13.000   1.6463   0.03754   0.02989  -0.0445   0.3230   1.0000
  13.250   1.6222   0.03954   0.03210  -0.0388   0.3200   1.0000
  13.500   1.6122   0.04121   0.03391  -0.0352   0.3168   1.0000
  13.750   1.6201   0.04207   0.03480  -0.0336   0.3138   1.0000
  14.000   1.6493   0.04188   0.03456  -0.0341   0.3108   1.0000
  14.250   1.6791   0.04202   0.03466  -0.0348   0.3076   1.0000
  14.500   1.6289   0.04590   0.03885  -0.0281   0.3042   1.0000
  14.750   1.5998   0.04927   0.04241  -0.0241   0.3002   1.0000
  15.000   1.6093   0.05014   0.04330  -0.0232   0.2966   1.0000
  15.250   1.6500   0.04893   0.04199  -0.0242   0.2935   1.0000
  15.500   1.6274   0.05225   0.04546  -0.0214   0.2895   1.0000
  15.750   1.5601   0.05970   0.05321  -0.0173   0.2837   1.0000
  16.000   1.5803   0.05974   0.05323  -0.0171   0.2799   1.0000
  16.250   1.6326   0.05696   0.05031  -0.0180   0.2767   1.0000
  16.500   1.4926   0.07324   0.06707  -0.0145   0.2677   1.0000
  16.750   1.5223   0.07219   0.06599  -0.0144   0.2645   1.0000
  17.000   1.5791   0.06815   0.06181  -0.0146   0.2617   1.0000
  17.250   1.2055   0.12049   0.11475  -0.0203   0.2293   1.0000
  17.500   1.2394   0.11817   0.11244  -0.0196   0.2294   1.0000
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