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GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 548 AIRFOIL (goe548-il)
Reynolds number: 500,000
Max Cl/Cd: 94.96 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe548-il-500000.txt
Download as CSV file: xf-goe548-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 548 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6669   0.05611   0.05362  -0.0693   1.0000   0.0122
 -11.250  -0.6929   0.05222   0.04967  -0.0695   1.0000   0.0122
 -11.000  -0.7191   0.04973   0.04709  -0.0672   1.0000   0.0121
 -10.750  -0.7456   0.04613   0.04332  -0.0667   0.9986   0.0121
 -10.500  -0.7566   0.04212   0.03901  -0.0676   0.9940   0.0120
 -10.250  -0.7642   0.03740   0.03388  -0.0673   0.9884   0.0121
 -10.000  -0.7622   0.03239   0.02838  -0.0677   0.9848   0.0122
  -9.750  -0.7452   0.03116   0.02709  -0.0677   0.9822   0.0128
  -9.500  -0.7302   0.02982   0.02558  -0.0668   0.9783   0.0134
  -9.250  -0.7091   0.02828   0.02385  -0.0670   0.9756   0.0139
  -9.000  -0.6880   0.02602   0.02128  -0.0673   0.9735   0.0144
  -8.750  -0.6645   0.02384   0.01878  -0.0676   0.9721   0.0150
  -8.500  -0.6495   0.02233   0.01704  -0.0658   0.9683   0.0153
  -8.250  -0.6280   0.02120   0.01571  -0.0651   0.9651   0.0159
  -8.000  -0.6057   0.01925   0.01352  -0.0648   0.9627   0.0166
  -7.750  -0.5776   0.01823   0.01242  -0.0655   0.9610   0.0180
  -7.500  -0.5456   0.01773   0.01187  -0.0668   0.9598   0.0193
  -7.250  -0.5128   0.01714   0.01118  -0.0681   0.9588   0.0209
  -7.000  -0.4974   0.01630   0.01024  -0.0659   0.9541   0.0222
  -6.750  -0.4725   0.01556   0.00948  -0.0656   0.9510   0.0243
  -6.500  -0.4405   0.01512   0.00899  -0.0667   0.9491   0.0269
  -6.250  -0.4084   0.01440   0.00820  -0.0679   0.9476   0.0303
  -6.000  -0.3728   0.01401   0.00783  -0.0698   0.9466   0.0348
  -5.750  -0.3362   0.01368   0.00743  -0.0718   0.9458   0.0385
  -5.500  -0.3021   0.01287   0.00660  -0.0736   0.9449   0.0448
  -5.250  -0.2861   0.01266   0.00635  -0.0711   0.9384   0.0481
  -5.000  -0.2530   0.01214   0.00576  -0.0725   0.9363   0.0516
  -4.750  -0.2196   0.01156   0.00516  -0.0739   0.9343   0.0577
  -4.500  -0.1839   0.01118   0.00471  -0.0757   0.9327   0.0624
  -4.250  -0.1479   0.01066   0.00421  -0.0776   0.9310   0.0718
  -4.000  -0.1279   0.01032   0.00394  -0.0759   0.9238   0.0885
  -3.750  -0.0986   0.00936   0.00347  -0.0767   0.9193   0.2090
  -3.250  -0.0471   0.00841   0.00302  -0.0762   0.9070   0.3563
  -3.000  -0.0156   0.00808   0.00282  -0.0771   0.9028   0.4106
  -2.750   0.0046   0.00786   0.00274  -0.0754   0.8949   0.4548
  -2.500   0.0326   0.00760   0.00261  -0.0755   0.8895   0.5073
  -2.250   0.0542   0.00742   0.00254  -0.0741   0.8816   0.5486
  -2.000   0.0806   0.00721   0.00243  -0.0737   0.8751   0.5917
  -1.750   0.1024   0.00706   0.00237  -0.0723   0.8666   0.6266
  -1.500   0.1286   0.00688   0.00227  -0.0718   0.8598   0.6623
  -1.250   0.1493   0.00672   0.00223  -0.0701   0.8500   0.6979
  -1.000   0.1729   0.00656   0.00218  -0.0690   0.8417   0.7402
  -0.750   0.1956   0.00640   0.00215  -0.0677   0.8322   0.7852
  -0.500   0.2192   0.00631   0.00214  -0.0666   0.8217   0.8173
  -0.250   0.2448   0.00623   0.00208  -0.0658   0.8097   0.8434
   0.000   0.2715   0.00618   0.00204  -0.0654   0.7973   0.8672
   0.250   0.3013   0.00617   0.00201  -0.0656   0.7838   0.8885
   0.500   0.3337   0.00621   0.00202  -0.0664   0.7713   0.9094
   0.750   0.3717   0.00633   0.00208  -0.0685   0.7584   0.9277
   1.250   0.4495   0.00666   0.00228  -0.0732   0.7338   0.9507
   1.500   0.4858   0.00681   0.00239  -0.0750   0.7216   0.9577
   1.750   0.5236   0.00698   0.00251  -0.0772   0.7110   0.9629
   2.000   0.5565   0.00714   0.00263  -0.0783   0.7007   0.9702
   2.250   0.5953   0.00728   0.00273  -0.0808   0.6883   0.9739
   2.500   0.6304   0.00741   0.00284  -0.0824   0.6732   0.9798
   2.750   0.6663   0.00752   0.00295  -0.0843   0.6585   0.9848
   3.000   0.7039   0.00761   0.00302  -0.0866   0.6360   0.9895
   3.250   0.7372   0.00784   0.00307  -0.0879   0.5860   0.9953
   3.500   0.7739   0.00815   0.00316  -0.0902   0.5363   1.0000
   3.750   0.7844   0.00841   0.00327  -0.0868   0.5034   1.0000
   4.000   0.7920   0.00878   0.00342  -0.0828   0.4572   1.0000
   4.250   0.7996   0.00921   0.00361  -0.0789   0.4036   1.0000
   4.500   0.8062   0.00974   0.00384  -0.0748   0.3400   1.0000
   4.750   0.8063   0.01064   0.00425  -0.0696   0.2405   1.0000
   5.000   0.8128   0.01135   0.00465  -0.0656   0.1826   1.0000
   5.250   0.8228   0.01193   0.00500  -0.0622   0.1384   1.0000
   5.500   0.8285   0.01272   0.00543  -0.0581   0.0809   1.0000
   5.750   0.8360   0.01344   0.00589  -0.0543   0.0319   1.0000
   6.000   0.8486   0.01391   0.00634  -0.0512   0.0242   1.0000
   6.250   0.8616   0.01428   0.00678  -0.0483   0.0222   1.0000
   6.500   0.8747   0.01465   0.00722  -0.0454   0.0211   1.0000
   6.750   0.8851   0.01521   0.00783  -0.0421   0.0191   1.0000
   7.000   0.8939   0.01590   0.00861  -0.0385   0.0177   1.0000
   7.250   0.9062   0.01645   0.00921  -0.0357   0.0174   1.0000
   7.500   0.9188   0.01702   0.00985  -0.0330   0.0167   1.0000
   7.750   0.9299   0.01770   0.01060  -0.0301   0.0162   1.0000
   8.000   0.9406   0.01845   0.01140  -0.0272   0.0159   1.0000
   8.250   0.9506   0.01929   0.01230  -0.0243   0.0154   1.0000
   8.500   0.9605   0.02021   0.01327  -0.0215   0.0150   1.0000
   8.750   0.9713   0.02114   0.01424  -0.0190   0.0144   1.0000
   9.000   0.9818   0.02216   0.01530  -0.0166   0.0139   1.0000
   9.250   0.9902   0.02397   0.01712  -0.0141   0.0131   1.0000
   9.500   1.0110   0.02581   0.01898  -0.0133   0.0129   1.0000
   9.750   1.0414   0.02778   0.02100  -0.0139   0.0128   1.0000
  10.000   1.0521   0.02855   0.02192  -0.0115   0.0125   1.0000
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