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GOE 571 AIRFOIL (goe571-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 571 AIRFOIL (goe571-il)
Reynolds number: 500,000
Max Cl/Cd: 42.76 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe571-il-500000-n5.txt
Download as CSV file: xf-goe571-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 571 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750   0.4922   0.10463   0.09930  -0.1670   0.5382   0.0257
 -12.500   0.4917   0.10179   0.09644  -0.1684   0.5352   0.0258
 -12.250   0.4970   0.09932   0.09397  -0.1693   0.5324   0.0258
 -12.000   0.5006   0.09668   0.09134  -0.1704   0.5291   0.0259
 -11.750   0.5053   0.09412   0.08877  -0.1713   0.5247   0.0259
 -11.500   0.5132   0.09198   0.08662  -0.1717   0.5212   0.0260
 -11.250   0.5258   0.09053   0.08514  -0.1716   0.5162   0.0261
 -11.000   0.5383   0.08910   0.08371  -0.1716   0.5122   0.0263
 -10.750   0.5463   0.08722   0.08184  -0.1719   0.5083   0.0266
 -10.500   0.5528   0.08532   0.07993  -0.1723   0.5041   0.0267
 -10.250   0.5592   0.08353   0.07812  -0.1725   0.5000   0.0270
 -10.000   0.5636   0.08153   0.07610  -0.1727   0.4961   0.0273
  -9.750   0.5674   0.07938   0.07398  -0.1731   0.4928   0.0279
  -9.500   0.5708   0.07731   0.07191  -0.1733   0.4893   0.0277
  -9.250   0.5717   0.07505   0.06966  -0.1734   0.4854   0.0282
  -9.000   0.5485   0.06980   0.06444  -0.1754   0.4839   0.0294
  -8.750   0.5499   0.06796   0.06260  -0.1748   0.4803   0.0293
  -8.500   0.5383   0.06452   0.05919  -0.1751   0.4776   0.0294
  -8.250   0.5121   0.05902   0.05372  -0.1750   0.4762   0.0259
  -8.000   0.5052   0.05686   0.05161  -0.1743   0.4732   0.0258
  -7.750   0.5031   0.05579   0.05056  -0.1729   0.4695   0.0256
  -7.500   0.4841   0.05346   0.04827  -0.1720   0.4669   0.0255
  -7.250   0.4573   0.05142   0.04624  -0.1682   0.4644   0.0253
  -7.000   0.4216   0.04988   0.04470  -0.1611   0.4616   0.0251
  -6.750   0.3896   0.04822   0.04304  -0.1539   0.4594   0.0250
  -6.500   0.3655   0.04614   0.04093  -0.1480   0.4576   0.0247
  -6.250   0.3413   0.04394   0.03868  -0.1416   0.4551   0.0246
  -6.000   0.3169   0.04131   0.03596  -0.1349   0.4530   0.0247
  -5.750   0.2990   0.03893   0.03346  -0.1287   0.4506   0.0248
  -5.500   0.2831   0.03671   0.03110  -0.1223   0.4482   0.0246
  -5.250   0.2673   0.03424   0.02845  -0.1157   0.4458   0.0242
  -5.000   0.2483   0.03123   0.02517  -0.1081   0.4437   0.0241
  -4.500   0.2280   0.02655   0.01990  -0.0951   0.4399   0.0242
  -4.250   0.2297   0.02532   0.01846  -0.0904   0.4376   0.0242
  -4.000   0.2335   0.02429   0.01720  -0.0861   0.4352   0.0245
  -3.750   0.2412   0.02357   0.01632  -0.0824   0.4327   0.0244
  -3.500   0.2488   0.02293   0.01550  -0.0787   0.4302   0.0245
  -3.250   0.2576   0.02246   0.01488  -0.0752   0.4279   0.0247
  -3.000   0.2667   0.02198   0.01424  -0.0718   0.4254   0.0248
  -2.750   0.2777   0.02156   0.01367  -0.0687   0.4232   0.0248
  -2.500   0.2915   0.02117   0.01318  -0.0661   0.4214   0.0250
  -2.250   0.3059   0.02088   0.01278  -0.0636   0.4195   0.0251
  -2.000   0.3199   0.02057   0.01237  -0.0611   0.4171   0.0252
  -1.750   0.3339   0.02032   0.01202  -0.0586   0.4150   0.0253
  -1.500   0.3475   0.02025   0.01184  -0.0561   0.4127   0.0256
  -1.250   0.3611   0.02026   0.01173  -0.0536   0.4105   0.0258
  -1.000   0.3748   0.02013   0.01153  -0.0513   0.4085   0.0258
  -0.750   0.3890   0.01999   0.01133  -0.0491   0.4065   0.0261
  -0.500   0.4062   0.01982   0.01114  -0.0474   0.4050   0.0262
  -0.250   0.4238   0.01976   0.01106  -0.0458   0.4037   0.0262
   0.000   0.4410   0.01970   0.01100  -0.0442   0.4021   0.0263
   0.250   0.4582   0.01967   0.01097  -0.0426   0.4006   0.0267
   0.500   0.4754   0.01969   0.01098  -0.0410   0.3988   0.0267
   0.750   0.4916   0.01976   0.01104  -0.0394   0.3970   0.0270
   1.000   0.5076   0.01987   0.01113  -0.0378   0.3951   0.0271
   1.250   0.5241   0.01999   0.01123  -0.0363   0.3933   0.0274
   1.500   0.5402   0.02017   0.01139  -0.0348   0.3916   0.0276
   1.750   0.5558   0.02040   0.01160  -0.0333   0.3896   0.0278
   2.000   0.5739   0.02059   0.01177  -0.0322   0.3881   0.0280
   2.250   0.5936   0.02075   0.01195  -0.0314   0.3869   0.0283
   2.500   0.6130   0.02097   0.01219  -0.0306   0.3857   0.0287
   2.750   0.6325   0.02123   0.01245  -0.0299   0.3842   0.0290
   3.000   0.6525   0.02149   0.01273  -0.0294   0.3825   0.0293
   3.250   0.6723   0.02180   0.01305  -0.0289   0.3809   0.0296
   3.500   0.6932   0.02212   0.01338  -0.0288   0.3794   0.0299
   3.750   0.7142   0.02247   0.01376  -0.0287   0.3777   0.0310
   4.000   0.7343   0.02289   0.01418  -0.0285   0.3762   0.0312
   4.250   0.7542   0.02336   0.01464  -0.0283   0.3748   0.0324
   4.500   0.7747   0.02383   0.01509  -0.0283   0.3732   0.0331
   4.750   0.7962   0.02428   0.01552  -0.0284   0.3716   0.0333
   5.000   0.8190   0.02475   0.01602  -0.0289   0.3704   0.0345
   5.250   0.8391   0.02530   0.01661  -0.0290   0.3690   0.0344
   5.750   0.8827   0.02642   0.01779  -0.0299   0.3662   0.0394
   6.000   0.9068   0.02702   0.01847  -0.0310   0.3647   0.0528
   6.500   1.2089   0.02827   0.02194  -0.0849   0.3598   1.0000
   6.750   1.2214   0.02913   0.02277  -0.0839   0.3582   1.0000
   7.000   1.2330   0.03007   0.02368  -0.0829   0.3566   1.0000
   7.250   1.2459   0.03093   0.02451  -0.0820   0.3549   1.0000
   7.500   1.2595   0.03180   0.02540  -0.0813   0.3540   1.0000
   7.750   1.2709   0.03284   0.02648  -0.0804   0.3524   1.0000
   8.000   1.2834   0.03383   0.02748  -0.0797   0.3510   1.0000
   8.250   1.2951   0.03487   0.02855  -0.0789   0.3495   1.0000
   8.500   1.3056   0.03603   0.02973  -0.0781   0.3477   1.0000
   8.750   1.3161   0.03718   0.03088  -0.0774   0.3458   1.0000
   9.000   1.3259   0.03841   0.03210  -0.0766   0.3442   1.0000
   9.250   1.3349   0.03969   0.03338  -0.0758   0.3421   1.0000
   9.500   1.3456   0.04084   0.03450  -0.0751   0.3405   1.0000
   9.750   1.3542   0.04220   0.03588  -0.0744   0.3386   1.0000
  10.000   1.3633   0.04357   0.03730  -0.0738   0.3371   1.0000
  10.250   1.3726   0.04494   0.03872  -0.0732   0.3357   1.0000
  10.500   1.3792   0.04654   0.04035  -0.0725   0.3337   1.0000
  10.750   1.3865   0.04809   0.04192  -0.0719   0.3314   1.0000
  11.000   1.3928   0.04973   0.04358  -0.0712   0.3294   1.0000
  11.250   1.3994   0.05134   0.04519  -0.0706   0.3273   1.0000
  11.500   1.4083   0.05274   0.04658  -0.0701   0.3256   1.0000
  11.750   1.4140   0.05446   0.04832  -0.0695   0.3235   1.0000
  12.000   1.4189   0.05632   0.05025  -0.0690   0.3219   1.0000
  12.250   1.4206   0.05848   0.05247  -0.0683   0.3190   1.0000
  12.500   1.4228   0.06062   0.05466  -0.0677   0.3168   1.0000
  12.750   1.4271   0.06254   0.05660  -0.0672   0.3144   1.0000
  13.000   1.4321   0.06440   0.05846  -0.0668   0.3124   1.0000
  13.250   1.4372   0.06622   0.06027  -0.0663   0.3101   1.0000
  13.500   1.4384   0.06851   0.06263  -0.0658   0.3080   1.0000
  13.750   1.4332   0.07149   0.06570  -0.0651   0.3051   1.0000
  14.000   1.4299   0.07429   0.06855  -0.0645   0.3015   1.0000
  14.250   1.4296   0.07677   0.07105  -0.0640   0.2988   1.0000
  14.500   1.4336   0.07879   0.07306  -0.0638   0.2963   1.0000
  14.750   1.4334   0.08130   0.07562  -0.0634   0.2940   1.0000
  15.000   1.4204   0.08526   0.07968  -0.0627   0.2903   1.0000
  15.250   1.4133   0.08855   0.08301  -0.0622   0.2861   1.0000
  15.500   1.4153   0.09086   0.08533  -0.0620   0.2841   1.0000
  15.750   1.4110   0.09388   0.08836  -0.0617   0.2798   1.0000
  16.000   1.3936   0.09848   0.09306  -0.0611   0.2753   1.0000
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