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NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 66-018 (naca66-018-il)
Reynolds number: 200,000
Max Cl/Cd: 30.99 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca66-018-il-200000.txt
Download as CSV file: xf-naca66-018-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-018                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.3440   0.11372   0.11030  -0.0700   0.9633   0.0929
 -14.000  -0.7117   0.05922   0.05464  -0.0859   0.9781   0.0462
 -13.750  -0.7205   0.05399   0.04923  -0.0864   0.9747   0.0452
 -13.500  -0.8495   0.06165   0.05655  -0.0762   0.9834   0.0485
 -13.250  -0.8583   0.06464   0.05938  -0.0763   0.9744   0.0549
 -13.000  -0.8971   0.05026   0.04379  -0.0729   0.9692   0.0406
 -12.750  -0.8928   0.04845   0.04165  -0.0721   0.9619   0.0403
 -12.500  -0.8803   0.04554   0.03846  -0.0720   0.9563   0.0403
 -12.250  -0.8555   0.04175   0.03442  -0.0731   0.9522   0.0408
 -12.000  -0.8276   0.03918   0.03164  -0.0742   0.9483   0.0411
 -11.750  -0.7970   0.03702   0.02927  -0.0753   0.9449   0.0414
 -11.500  -0.7657   0.03530   0.02743  -0.0763   0.9408   0.0420
 -11.250  -0.7326   0.03388   0.02587  -0.0774   0.9371   0.0424
 -11.000  -0.7009   0.03278   0.02468  -0.0782   0.9337   0.0436
 -10.750  -0.6712   0.03183   0.02363  -0.0787   0.9301   0.0449
 -10.500  -0.6441   0.03103   0.02270  -0.0788   0.9260   0.0462
 -10.250  -0.6127   0.03022   0.02183  -0.0793   0.9226   0.0479
 -10.000  -0.5834   0.02950   0.02120  -0.0796   0.9195   0.0499
  -9.750  -0.5616   0.02890   0.02058  -0.0790   0.9159   0.0520
  -9.500  -0.5418   0.02830   0.01993  -0.0783   0.9119   0.0543
  -9.250  -0.5253   0.02752   0.01919  -0.0772   0.9083   0.0566
  -9.000  -0.5120   0.02682   0.01852  -0.0758   0.9049   0.0600
  -8.750  -0.4977   0.02629   0.01790  -0.0743   0.9020   0.0640
  -8.500  -0.4892   0.02533   0.01702  -0.0726   0.8984   0.0685
  -8.000  -0.4702   0.02379   0.01550  -0.0689   0.8915   0.0860
  -7.750  -0.4696   0.02266   0.01460  -0.0657   0.8883   0.1139
  -7.500  -0.4850   0.02103   0.01362  -0.0605   0.8850   0.2109
  -7.250  -0.5040   0.01954   0.01273  -0.0549   0.8802   0.3104
  -7.000  -0.5243   0.01839   0.01204  -0.0483   0.8754   0.3926
  -6.750  -0.5430   0.01752   0.01166  -0.0410   0.8717   0.4767
  -6.500  -0.4796   0.02003   0.01496  -0.0435   0.8719   0.6272
  -6.250  -0.5093   0.01911   0.01396  -0.0349   0.8683   0.6492
  -6.000  -0.5291   0.01960   0.01445  -0.0272   0.8638   0.6641
  -5.750  -0.5285   0.02052   0.01532  -0.0221   0.8607   0.6784
  -5.500  -0.4712   0.02236   0.01708  -0.0258   0.8603   0.6912
  -5.250  -0.3123   0.02786   0.02238  -0.0418   0.8653   0.6997
  -5.000  -0.2536   0.02929   0.02370  -0.0458   0.8652   0.7013
  -4.750  -0.2521   0.02954   0.02392  -0.0422   0.8620   0.7135
  -4.500  -0.2071   0.03028   0.02458  -0.0446   0.8610   0.7160
  -4.250  -0.1598   0.03099   0.02521  -0.0475   0.8602   0.7180
  -4.000  -0.1618   0.03119   0.02539  -0.0433   0.8575   0.7302
  -3.750  -0.1204   0.03161   0.02575  -0.0455   0.8569   0.7327
  -3.500  -0.0764   0.03204   0.02612  -0.0482   0.8563   0.7348
  -3.250  -0.0401   0.03238   0.02642  -0.0498   0.8555   0.7384
  -3.000  -0.0407   0.03244   0.02646  -0.0457   0.8535   0.7495
  -2.750   0.0013   0.03261   0.02659  -0.0481   0.8528   0.7515
  -2.500   0.0370   0.03278   0.02673  -0.0497   0.8520   0.7547
  -2.250   0.0131   0.03351   0.02749  -0.0421   0.8485   0.7665
  -2.000   0.0426   0.03403   0.02801  -0.0429   0.8463   0.7689
  -1.750   0.0607   0.03459   0.02858  -0.0417   0.8437   0.7730
  -1.500   0.0233   0.03507   0.02907  -0.0311   0.8389   0.7841
  -1.250   0.0693   0.03508   0.02907  -0.0346   0.8380   0.7859
  -1.000  -0.0647   0.03644   0.03048  -0.0063   0.8282   0.8009
  -0.750  -0.0334   0.03673   0.03077  -0.0073   0.8255   0.8028
  -0.500  -0.1307   0.03609   0.03011   0.0147   0.8188   0.8170
  -0.250  -0.0519   0.03642   0.03043   0.0050   0.8185   0.8161
   0.000  -0.0042   0.03624   0.03024   0.0008   0.8175   0.8179
   0.250   0.0443   0.03642   0.03044  -0.0036   0.8155   0.8189
   0.500   0.1254   0.03612   0.03014  -0.0138   0.8166   0.8192
   0.750   0.0307   0.03673   0.03077   0.0078   0.8025   0.8257
   1.000   0.0642   0.03648   0.03052   0.0064   0.8007   0.8282
   1.250  -0.0725   0.03502   0.02900   0.0352   0.7856   0.8382
   1.500  -0.0291   0.03499   0.02899   0.0321   0.7837   0.8392
   1.750   0.0191   0.03497   0.02898   0.0281   0.7824   0.8399
   2.000  -0.0415   0.03409   0.02808   0.0427   0.7687   0.8461
   2.250  -0.0117   0.03364   0.02762   0.0420   0.7663   0.8482
   2.500   0.0189   0.03318   0.02717   0.0410   0.7638   0.8498
   2.750  -0.0035   0.03256   0.02653   0.0484   0.7512   0.8530
   3.000   0.0387   0.03238   0.02639   0.0459   0.7491   0.8537
   3.250   0.0778   0.03220   0.02626   0.0439   0.7464   0.8544
   3.500   0.0751   0.03200   0.02608   0.0484   0.7346   0.8564
   3.750   0.1184   0.03159   0.02572   0.0458   0.7324   0.8570
   4.000   0.1650   0.03112   0.02532   0.0427   0.7309   0.8575
   4.250   0.1587   0.03099   0.02521   0.0477   0.7177   0.8602
   4.500   0.2056   0.03029   0.02459   0.0448   0.7157   0.8609
   4.750   0.2569   0.02946   0.02385   0.0414   0.7144   0.8615
   5.000   0.2528   0.02933   0.02374   0.0459   0.7011   0.8652
   5.250   0.3100   0.02795   0.02248   0.0421   0.6994   0.8654
   5.500   0.4779   0.02218   0.01691   0.0248   0.6910   0.8599
   5.750   0.5315   0.02046   0.01526   0.0217   0.6783   0.8604
   6.000   0.5296   0.01960   0.01445   0.0272   0.6636   0.8638
   6.250   0.5094   0.01912   0.01398   0.0349   0.6489   0.8683
   6.500   0.4789   0.02003   0.01496   0.0435   0.6264   0.8720
   6.750   0.5427   0.01751   0.01164   0.0410   0.4756   0.8718
   7.000   0.5246   0.01837   0.01202   0.0482   0.3928   0.8754
   7.250   0.5037   0.01956   0.01273   0.0549   0.3091   0.8800
   7.500   0.4847   0.02104   0.01363   0.0605   0.2096   0.8851
   7.750   0.4697   0.02267   0.01460   0.0657   0.1129   0.8884
   8.000   0.4702   0.02380   0.01551   0.0689   0.0852   0.8915
   8.250   0.4779   0.02464   0.01630   0.0710   0.0746   0.8949
   8.500   0.4896   0.02533   0.01701   0.0726   0.0683   0.8984
   8.750   0.4978   0.02630   0.01791   0.0743   0.0639   0.9020
   9.000   0.5123   0.02684   0.01853   0.0757   0.0602   0.9050
   9.250   0.5263   0.02750   0.01918   0.0771   0.0570   0.9083
   9.500   0.5424   0.02830   0.01993   0.0782   0.0541   0.9120
   9.750   0.5626   0.02889   0.02058   0.0789   0.0520   0.9158
  10.000   0.5847   0.02951   0.02120   0.0794   0.0498   0.9194
  10.250   0.6114   0.03016   0.02181   0.0794   0.0481   0.9228
  10.500   0.6453   0.03105   0.02272   0.0786   0.0461   0.9259
  10.750   0.6715   0.03182   0.02362   0.0787   0.0448   0.9302
  11.000   0.7002   0.03274   0.02464   0.0783   0.0434   0.9339
  11.250   0.7333   0.03392   0.02594   0.0773   0.0427   0.9371
  11.500   0.7658   0.03529   0.02742   0.0763   0.0418   0.9409
  11.750   0.7964   0.03697   0.02924   0.0754   0.0413   0.9452
  12.000   0.8260   0.03907   0.03155   0.0744   0.0411   0.9487
  12.250   0.8521   0.04156   0.03427   0.0735   0.0408   0.9529
  12.500   0.8646   0.04384   0.03688   0.0743   0.0411   0.9596
  12.750   0.8574   0.04748   0.04117   0.0761   0.0421   0.9664
  13.000   0.8551   0.05129   0.04542   0.0766   0.0426   0.9729
  13.250   0.8468   0.05643   0.05103   0.0766   0.0444   0.9783
  13.500   0.8508   0.06124   0.05605   0.0756   0.0460   0.9836
  13.750   0.7208   0.05393   0.04917   0.0863   0.0452   0.9747
  14.000   0.7138   0.05905   0.05445   0.0858   0.0461   0.9781
  14.250   0.3437   0.11350   0.11008   0.0699   0.0929   0.9631
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