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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.24 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe509-il-1000000.txt
Download as CSV file: xf-goe509-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 509 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6110   0.03431   0.03203  -0.0905   0.9775   0.0122
 -10.500  -0.6140   0.02485   0.02176  -0.0933   0.9738   0.0123
 -10.250  -0.5950   0.02144   0.01795  -0.0943   0.9723   0.0127
 -10.000  -0.5600   0.02024   0.01664  -0.0966   0.9715   0.0132
  -9.750  -0.5456   0.01957   0.01588  -0.0941   0.9667   0.0134
  -9.500  -0.5178   0.01869   0.01489  -0.0946   0.9643   0.0138
  -9.250  -0.4900   0.01758   0.01361  -0.0950   0.9621   0.0141
  -9.000  -0.4586   0.01673   0.01262  -0.0961   0.9602   0.0146
  -8.750  -0.4270   0.01590   0.01163  -0.0971   0.9579   0.0150
  -8.500  -0.4111   0.01540   0.01103  -0.0945   0.9517   0.0152
  -8.250  -0.3877   0.01430   0.00980  -0.0939   0.9469   0.0161
  -8.000  -0.3602   0.01379   0.00922  -0.0937   0.9429   0.0166
  -7.750  -0.3404   0.01350   0.00890  -0.0919   0.9356   0.0172
  -7.500  -0.3134   0.01313   0.00844  -0.0916   0.9300   0.0179
  -7.250  -0.2930   0.01277   0.00801  -0.0898   0.9198   0.0185
  -7.000  -0.2720   0.01209   0.00721  -0.0883   0.9058   0.0191
  -6.750  -0.2458   0.01160   0.00664  -0.0878   0.8792   0.0200
  -6.500  -0.2183   0.01142   0.00625  -0.0874   0.8419   0.0208
  -6.250  -0.1947   0.01128   0.00595  -0.0864   0.8194   0.0216
  -6.000  -0.1704   0.01116   0.00569  -0.0854   0.8058   0.0224
  -5.750  -0.1476   0.01074   0.00515  -0.0843   0.7945   0.0236
  -5.500  -0.1227   0.01059   0.00499  -0.0836   0.7849   0.0247
  -5.250  -0.0978   0.01050   0.00482  -0.0828   0.7753   0.0257
  -5.000  -0.0725   0.01037   0.00463  -0.0821   0.7660   0.0269
  -4.750  -0.0479   0.01013   0.00431  -0.0812   0.7576   0.0278
  -4.500  -0.0240   0.00980   0.00395  -0.0803   0.7488   0.0295
  -4.250   0.0014   0.00972   0.00383  -0.0797   0.7396   0.0308
  -4.000   0.0262   0.00959   0.00364  -0.0789   0.7298   0.0321
  -3.750   0.0520   0.00951   0.00352  -0.0782   0.7210   0.0331
  -3.250   0.1005   0.00901   0.00293  -0.0764   0.7028   0.0367
  -3.000   0.1254   0.00892   0.00281  -0.0757   0.6934   0.0385
  -2.750   0.1504   0.00885   0.00267  -0.0749   0.6823   0.0396
  -2.500   0.1742   0.00863   0.00240  -0.0739   0.6702   0.0421
  -2.250   0.1981   0.00854   0.00227  -0.0729   0.6553   0.0443
  -2.000   0.2219   0.00849   0.00216  -0.0719   0.6384   0.0464
  -1.750   0.2450   0.00853   0.00209  -0.0707   0.6169   0.0483
  -1.500   0.2669   0.00844   0.00192  -0.0693   0.5904   0.0529
  -1.250   0.2877   0.00854   0.00186  -0.0677   0.5515   0.0570
  -1.000   0.3063   0.00872   0.00182  -0.0657   0.4954   0.0632
  -0.750   0.3272   0.00886   0.00183  -0.0642   0.4640   0.0714
  -0.500   0.3494   0.00884   0.00181  -0.0630   0.4495   0.0900
  -0.250   0.3709   0.00874   0.00179  -0.0616   0.4398   0.1338
   0.000   0.3910   0.00854   0.00184  -0.0600   0.4323   0.2310
   0.250   0.4145   0.00858   0.00189  -0.0591   0.4248   0.2599
   0.500   0.4389   0.00861   0.00193  -0.0583   0.4189   0.2778
   0.750   0.4630   0.00868   0.00198  -0.0574   0.4137   0.2901
   1.000   0.4871   0.00872   0.00203  -0.0566   0.4095   0.3025
   1.250   0.5119   0.00872   0.00206  -0.0559   0.4061   0.3153
   1.500   0.5363   0.00875   0.00210  -0.0551   0.4024   0.3279
   1.750   0.5600   0.00880   0.00215  -0.0542   0.3979   0.3408
   2.000   0.5833   0.00885   0.00221  -0.0532   0.3935   0.3545
   2.250   0.6071   0.00880   0.00226  -0.0523   0.3905   0.3856
   2.500   0.6123   0.00798   0.00227  -0.0476   0.3876   0.7104
   2.750   0.7478   0.00807   0.00296  -0.0719   0.3763   0.9742
   3.000   0.7867   0.00826   0.00314  -0.0743   0.3726   0.9813
   3.250   0.8250   0.00843   0.00328  -0.0766   0.3684   0.9852
   3.500   0.8674   0.00862   0.00340  -0.0800   0.3608   0.9879
   3.750   0.9062   0.00871   0.00350  -0.0825   0.3561   0.9906
   4.000   0.9420   0.00887   0.00362  -0.0844   0.3499   0.9935
   4.250   0.9819   0.00896   0.00368  -0.0872   0.3430   0.9953
   4.500   1.0200   0.00905   0.00373  -0.0897   0.3340   0.9972
   4.750   1.0560   0.00914   0.00380  -0.0917   0.3257   0.9989
   5.000   1.0880   0.00928   0.00387  -0.0928   0.3116   1.0000
   5.250   1.1078   0.00946   0.00400  -0.0913   0.2976   1.0000
   5.500   1.1260   0.00973   0.00416  -0.0895   0.2764   1.0000
   5.750   1.1415   0.01013   0.00441  -0.0872   0.2481   1.0000
   6.000   1.1557   0.01060   0.00471  -0.0846   0.2197   1.0000
   6.500   1.1871   0.01138   0.00530  -0.0801   0.1865   1.0000
   6.750   1.2052   0.01163   0.00553  -0.0783   0.1795   1.0000
   7.000   1.2222   0.01192   0.00578  -0.0763   0.1725   1.0000
   7.250   1.2399   0.01217   0.00603  -0.0744   0.1667   1.0000
   7.500   1.2562   0.01246   0.00629  -0.0723   0.1597   1.0000
   7.750   1.2728   0.01273   0.00655  -0.0702   0.1541   1.0000
   8.000   1.2888   0.01299   0.00680  -0.0680   0.1469   1.0000
   8.250   1.3004   0.01329   0.00707  -0.0649   0.1374   1.0000
   8.500   1.3062   0.01378   0.00743  -0.0608   0.1155   1.0000
   8.750   1.2997   0.01480   0.00820  -0.0546   0.0763   1.0000
   9.000   1.2967   0.01580   0.00903  -0.0492   0.0435   1.0000
   9.250   1.3038   0.01645   0.00964  -0.0457   0.0347   1.0000
   9.500   1.3144   0.01697   0.01020  -0.0429   0.0324   1.0000
   9.750   1.3251   0.01752   0.01077  -0.0402   0.0309   1.0000
  10.000   1.3354   0.01811   0.01141  -0.0375   0.0289   1.0000
  10.250   1.3473   0.01865   0.01200  -0.0351   0.0281   1.0000
  10.500   1.3592   0.01921   0.01261  -0.0328   0.0274   1.0000
  10.750   1.3701   0.01984   0.01330  -0.0305   0.0266   1.0000
  11.000   1.3801   0.02056   0.01407  -0.0281   0.0256   1.0000
  11.250   1.3882   0.02141   0.01497  -0.0257   0.0246   1.0000
  11.500   1.3905   0.02266   0.01630  -0.0226   0.0231   1.0000
  11.750   1.3996   0.02355   0.01725  -0.0205   0.0226   1.0000
  12.000   1.4110   0.02434   0.01810  -0.0189   0.0219   1.0000
  12.250   1.4211   0.02525   0.01905  -0.0172   0.0211   1.0000
  12.500   1.4299   0.02630   0.02015  -0.0156   0.0204   1.0000
  12.750   1.4370   0.02753   0.02143  -0.0139   0.0196   1.0000
  13.000   1.4398   0.02914   0.02310  -0.0121   0.0189   1.0000
  13.250   1.4365   0.03134   0.02539  -0.0101   0.0181   1.0000
  13.500   1.4457   0.03260   0.02672  -0.0090   0.0178   1.0000
  13.750   1.4526   0.03408   0.02826  -0.0080   0.0172   1.0000
  14.000   1.4607   0.03549   0.02972  -0.0071   0.0165   1.0000
  14.250   1.4665   0.03717   0.03145  -0.0062   0.0160   1.0000
  14.500   1.4692   0.03921   0.03353  -0.0054   0.0153   1.0000
  14.750   1.4667   0.04186   0.03627  -0.0045   0.0149   1.0000
  15.000   1.4563   0.04547   0.03998  -0.0038   0.0143   1.0000
  15.250   1.4554   0.04818   0.04278  -0.0035   0.0142   1.0000
  15.500   1.4591   0.05046   0.04514  -0.0033   0.0138   1.0000
  15.750   1.4556   0.05365   0.04841  -0.0033   0.0134   1.0000
  16.000   1.4560   0.05645   0.05129  -0.0034   0.0130   1.0000
  16.250   1.4497   0.06024   0.05518  -0.0038   0.0128   1.0000
  16.500   1.4467   0.06368   0.05869  -0.0043   0.0125   1.0000
  16.750   1.4373   0.06809   0.06320  -0.0051   0.0124   1.0000
  17.000   1.4308   0.07219   0.06738  -0.0059   0.0120   1.0000
  17.250   1.4192   0.07706   0.07235  -0.0070   0.0118   1.0000
  17.500   1.4010   0.08293   0.07831  -0.0085   0.0114   1.0000
  17.750   1.3865   0.08829   0.08378  -0.0099   0.0114   1.0000
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