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GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.94 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe326-il-1000000.txt
Download as CSV file: xf-goe326-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 326 (PFALZ 55) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3465   0.09212   0.09059  -0.0198   1.0000   0.0147
  -8.000  -0.3456   0.08788   0.08638  -0.0237   1.0000   0.0155
  -7.750  -0.3435   0.08424   0.08278  -0.0267   0.9989   0.0155
  -7.500  -0.3208   0.07853   0.07704  -0.0356   0.9785   0.0156
  -7.250  -0.3041   0.07129   0.06976  -0.0443   0.9496   0.0158
  -7.000  -0.2900   0.06931   0.06769  -0.0448   0.9257   0.0161
  -6.750  -0.2743   0.06694   0.06524  -0.0468   0.9079   0.0165
  -6.500  -0.2562   0.06409   0.06232  -0.0499   0.8930   0.0170
  -6.250  -0.2355   0.06055   0.05867  -0.0541   0.8789   0.0182
  -6.000  -0.2012   0.05297   0.05091  -0.0645   0.8655   0.0196
  -5.250  -0.1330   0.04059   0.03813  -0.0738   0.8266   0.0209
  -5.000  -0.1084   0.03871   0.03614  -0.0750   0.8130   0.0219
  -4.750  -0.0720   0.03329   0.03036  -0.0780   0.8012   0.0246
  -4.500  -0.0481   0.02368   0.02009  -0.0804   0.7911   0.0250
  -4.250  -0.0242   0.02484   0.02131  -0.0806   0.7784   0.0261
  -4.000   0.0015   0.02439   0.02080  -0.0808   0.7673   0.0270
  -3.250   0.0843   0.01631   0.01170  -0.0811   0.7423   0.0295
  -3.000   0.1125   0.01505   0.01004  -0.0809   0.7345   0.0316
  -2.750   0.1405   0.01408   0.00892  -0.0808   0.7270   0.0314
  -2.250   0.1963   0.01219   0.00670  -0.0807   0.7116   0.0313
  -2.000   0.2236   0.01042   0.00468  -0.0807   0.7037   0.0323
  -1.750   0.2517   0.00989   0.00411  -0.0807   0.6949   0.0330
  -1.500   0.2797   0.00954   0.00370  -0.0806   0.6856   0.0336
  -1.250   0.3077   0.00921   0.00330  -0.0806   0.6748   0.0340
  -1.000   0.3358   0.00890   0.00294  -0.0805   0.6620   0.0345
  -0.750   0.3637   0.00864   0.00262  -0.0804   0.6467   0.0351
  -0.500   0.3916   0.00844   0.00235  -0.0803   0.6259   0.0358
  -0.250   0.4191   0.00837   0.00217  -0.0802   0.5965   0.0370
   0.000   0.4465   0.00834   0.00200  -0.0801   0.5668   0.0381
   0.500   0.5015   0.00840   0.00187  -0.0799   0.5253   0.0394
   1.000   0.5573   0.00815   0.00150  -0.0798   0.5015   0.0441
   1.250   0.5853   0.00816   0.00148  -0.0798   0.4910   0.0470
   1.500   0.6132   0.00821   0.00149  -0.0798   0.4800   0.0499
   1.750   0.6413   0.00817   0.00144  -0.0798   0.4699   0.0591
   2.000   0.6693   0.00804   0.00148  -0.0799   0.4602   0.1427
   2.250   0.6940   0.00630   0.00167  -0.0798   0.4500   1.0000
   2.500   0.7218   0.00640   0.00171  -0.0797   0.4398   1.0000
   2.750   0.7496   0.00652   0.00177  -0.0797   0.4293   1.0000
   3.000   0.7772   0.00665   0.00184  -0.0797   0.4181   1.0000
   3.250   0.8047   0.00679   0.00192  -0.0796   0.4063   1.0000
   3.500   0.8322   0.00693   0.00200  -0.0795   0.3943   1.0000
   3.750   0.8596   0.00708   0.00210  -0.0795   0.3814   1.0000
   4.000   0.8869   0.00724   0.00221  -0.0794   0.3689   1.0000
   4.250   0.9140   0.00742   0.00233  -0.0793   0.3564   1.0000
   4.500   0.9411   0.00760   0.00246  -0.0793   0.3448   1.0000
   4.750   0.9680   0.00781   0.00261  -0.0791   0.3300   1.0000
   5.000   0.9945   0.00805   0.00277  -0.0790   0.3116   1.0000
   5.250   1.0210   0.00829   0.00294  -0.0788   0.2955   1.0000
   5.500   1.0472   0.00856   0.00314  -0.0787   0.2779   1.0000
   5.750   1.0731   0.00885   0.00334  -0.0785   0.2585   1.0000
   6.000   1.0987   0.00919   0.00357  -0.0782   0.2361   1.0000
   6.250   1.1231   0.00966   0.00388  -0.0778   0.2047   1.0000
   6.500   1.1434   0.01065   0.00447  -0.0770   0.1357   1.0000
   6.750   1.1667   0.01124   0.00492  -0.0764   0.1124   1.0000
   7.000   1.1916   0.01161   0.00526  -0.0761   0.1019   1.0000
   7.250   1.2164   0.01197   0.00558  -0.0757   0.0912   1.0000
   7.500   1.2389   0.01260   0.00603  -0.0751   0.0645   1.0000
   7.750   1.2554   0.01393   0.00704  -0.0736   0.0181   1.0000
   8.000   1.2783   0.01447   0.00762  -0.0729   0.0148   1.0000
   8.250   1.3018   0.01490   0.00810  -0.0724   0.0140   1.0000
   8.500   1.3245   0.01541   0.00867  -0.0717   0.0131   1.0000
   8.750   1.3461   0.01601   0.00932  -0.0709   0.0122   1.0000
   9.000   1.3653   0.01683   0.01022  -0.0697   0.0113   1.0000
   9.250   1.3852   0.01753   0.01099  -0.0686   0.0107   1.0000
   9.500   1.4061   0.01807   0.01159  -0.0678   0.0103   1.0000
   9.750   1.4256   0.01871   0.01229  -0.0667   0.0098   1.0000
  10.000   1.4439   0.01942   0.01306  -0.0655   0.0094   1.0000
  10.250   1.4608   0.02020   0.01389  -0.0641   0.0090   1.0000
  10.500   1.4754   0.02110   0.01485  -0.0624   0.0086   1.0000
  10.750   1.4835   0.02231   0.01615  -0.0598   0.0083   1.0000
  11.000   1.4776   0.02416   0.01815  -0.0553   0.0080   1.0000
  11.250   1.4838   0.02539   0.01947  -0.0528   0.0079   1.0000
  11.500   1.4928   0.02653   0.02068  -0.0510   0.0078   1.0000
  11.750   1.5003   0.02785   0.02209  -0.0492   0.0076   1.0000
  12.000   1.5068   0.02934   0.02366  -0.0477   0.0074   1.0000
  12.250   1.5131   0.03096   0.02536  -0.0463   0.0072   1.0000
  12.500   1.5184   0.03274   0.02723  -0.0452   0.0070   1.0000
  12.750   1.5231   0.03470   0.02928  -0.0442   0.0068   1.0000
  13.000   1.5258   0.03695   0.03162  -0.0434   0.0066   1.0000
  13.250   1.5276   0.03941   0.03417  -0.0429   0.0065   1.0000
  13.500   1.5278   0.04215   0.03700  -0.0425   0.0064   1.0000
  13.750   1.5269   0.04508   0.04002  -0.0422   0.0062   1.0000
  14.000   1.5242   0.04831   0.04335  -0.0422   0.0061   1.0000
  14.250   1.5196   0.05186   0.04698  -0.0423   0.0061   1.0000
  14.500   1.5130   0.05577   0.05099  -0.0426   0.0060   1.0000
  14.750   1.5044   0.06006   0.05538  -0.0431   0.0059   1.0000
  15.000   1.4937   0.06471   0.06013  -0.0438   0.0058   1.0000
  15.250   1.4813   0.06963   0.06516  -0.0445   0.0057   1.0000
  15.500   1.4675   0.07460   0.07023  -0.0448   0.0056   1.0000
  15.750   1.4574   0.07923   0.07497  -0.0453   0.0056   1.0000
  16.000   1.4528   0.08365   0.07952  -0.0468   0.0055   1.0000
  16.250   1.4469   0.08821   0.08418  -0.0482   0.0055   1.0000
  16.500   1.4405   0.09292   0.08900  -0.0498   0.0055   1.0000
  16.750   1.4334   0.09778   0.09397  -0.0514   0.0054   1.0000
  17.000   1.4260   0.10276   0.09906  -0.0531   0.0054   1.0000
  17.250   1.4183   0.10789   0.10430  -0.0551   0.0054   1.0000
  17.500   1.4102   0.11312   0.10965  -0.0571   0.0053   1.0000
  17.750   1.4020   0.11848   0.11512  -0.0594   0.0053   1.0000
  18.000   1.3939   0.12397   0.12071  -0.0618   0.0053   1.0000
  18.250   1.3851   0.12960   0.12646  -0.0644   0.0052   1.0000
  18.500   1.3763   0.13536   0.13233  -0.0672   0.0052   1.0000
  18.750   1.3671   0.14128   0.13837  -0.0701   0.0052   1.0000
  19.000   1.3580   0.14738   0.14458  -0.0734   0.0052   1.0000
  19.250   1.3487   0.15368   0.15099  -0.0770   0.0051   1.0000
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