Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 6-H-20 AIRFOIL (n6h20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 6-H-20 AIRFOIL (n6h20-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.05 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n6h20-il-1000000.txt
Download as CSV file: xf-n6h20-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 6-H-20 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1064   0.10445   0.10144  -0.0481   0.6027   0.0246
 -11.750  -0.1448   0.09925   0.09597  -0.0618   0.6046   0.0251
 -11.500  -0.1449   0.08824   0.08524  -0.0562   0.6023   0.0266
 -11.250  -0.1411   0.08521   0.08221  -0.0574   0.6017   0.0267
 -11.000  -0.1389   0.08191   0.07892  -0.0587   0.6011   0.0268
 -10.750  -0.1390   0.07823   0.07525  -0.0602   0.6006   0.0270
 -10.500  -0.1383   0.07489   0.07192  -0.0616   0.5999   0.0272
 -10.250  -0.1468   0.07011   0.06715  -0.0640   0.5994   0.0273
 -10.000  -0.1677   0.06402   0.06106  -0.0675   0.5989   0.0275
  -9.750  -0.4914   0.03878   0.03457  -0.0484   0.6013   0.0265
  -9.500  -0.5065   0.03584   0.03133  -0.0422   0.6006   0.0265
  -9.250  -0.5115   0.03340   0.02864  -0.0373   0.5998   0.0264
  -9.000  -0.5080   0.03153   0.02654  -0.0336   0.5989   0.0264
  -8.750  -0.5033   0.02943   0.02419  -0.0300   0.5981   0.0263
  -8.500  -0.5001   0.02623   0.02062  -0.0263   0.5973   0.0265
  -8.250  -0.4843   0.02415   0.01831  -0.0246   0.5965   0.0266
  -8.000  -0.4627   0.02284   0.01686  -0.0238   0.5957   0.0269
  -7.750  -0.4398   0.02227   0.01626  -0.0232   0.5948   0.0272
  -7.500  -0.4155   0.02142   0.01530  -0.0227   0.5939   0.0274
  -7.250  -0.3920   0.02122   0.01510  -0.0221   0.5927   0.0277
  -7.000  -0.3669   0.02062   0.01441  -0.0219   0.5913   0.0280
  -6.750  -0.3410   0.02005   0.01377  -0.0217   0.5909   0.0285
  -6.500  -0.3105   0.01913   0.01274  -0.0224   0.5905   0.0287
  -6.250  -0.2775   0.01828   0.01179  -0.0235   0.5900   0.0290
  -6.000  -0.2409   0.01747   0.01089  -0.0254   0.5894   0.0292
  -5.750  -0.1967   0.01662   0.00996  -0.0289   0.5888   0.0296
  -5.500  -0.1561   0.01601   0.00928  -0.0316   0.5881   0.0299
  -5.250  -0.1208   0.01562   0.00885  -0.0332   0.5873   0.0302
  -5.000  -0.0859   0.01527   0.00846  -0.0347   0.5864   0.0304
  -4.750  -0.0381   0.01460   0.00776  -0.0387   0.5857   0.0310
  -4.500  -0.0010   0.01420   0.00740  -0.0407   0.5849   0.0318
  -4.250   0.0315   0.01393   0.00713  -0.0418   0.5842   0.0321
  -4.000   0.0624   0.01372   0.00693  -0.0425   0.5834   0.0326
  -3.750   0.0932   0.01352   0.00673  -0.0432   0.5827   0.0331
  -3.500   0.1229   0.01333   0.00654  -0.0437   0.5820   0.0336
  -3.250   0.1520   0.01317   0.00638  -0.0441   0.5813   0.0341
  -3.000   0.1807   0.01303   0.00623  -0.0444   0.5806   0.0345
  -2.750   0.2091   0.01290   0.00609  -0.0447   0.5799   0.0351
  -2.500   0.2371   0.01278   0.00596  -0.0449   0.5791   0.0356
  -2.250   0.2650   0.01261   0.00580  -0.0451   0.5782   0.0366
  -2.000   0.2918   0.01256   0.00576  -0.0451   0.5772   0.0378
  -1.750   0.3177   0.01262   0.00583  -0.0450   0.5755   0.0391
  -1.500   0.3444   0.01248   0.00571  -0.0450   0.5748   0.0402
  -1.250   0.3705   0.01238   0.00563  -0.0449   0.5742   0.0418
  -1.000   0.3963   0.01228   0.00557  -0.0447   0.5735   0.0440
  -0.750   0.4218   0.01221   0.00552  -0.0445   0.5727   0.0466
  -0.500   0.4463   0.01212   0.00550  -0.0441   0.5720   0.0561
  -0.250   0.4677   0.01193   0.00551  -0.0431   0.5712   0.1039
   0.000   0.4809   0.01158   0.00553  -0.0407   0.5702   0.2212
   0.250   0.4847   0.01109   0.00538  -0.0364   0.5690   0.3341
   0.500   0.4792   0.01044   0.00506  -0.0304   0.5678   0.4500
   0.750   0.4551   0.00970   0.00457  -0.0205   0.5669   0.5356
   1.000   0.4195   0.00933   0.00438  -0.0076   0.5660   0.6033
   1.250   0.3813   0.00869   0.00408   0.0062   0.5651   0.7239
   1.500   0.3907   0.00892   0.00461   0.0103   0.5642   0.8296
   1.750   0.4155   0.00919   0.00484   0.0108   0.5634   0.8395
   2.000   0.4536   0.00972   0.00541   0.0086   0.5624   0.8454
   2.250   0.4881   0.01030   0.00598   0.0071   0.5610   0.8510
   2.500   0.5176   0.01083   0.00651   0.0066   0.5598   0.8559
   2.750   0.5796   0.01192   0.00769  -0.0002   0.5592   0.8608
   3.000   0.8292   0.01534   0.01110  -0.0435   0.5577   0.8646
   3.250   0.8480   0.01520   0.01098  -0.0422   0.5562   0.8653
   3.500   0.8603   0.01507   0.01086  -0.0397   0.5551   0.8667
   3.750   0.7117   0.01335   0.00915  -0.0054   0.5541   0.8708
   4.000   0.8845   0.01489   0.01069  -0.0341   0.5521   0.8736
   4.250   0.8446   0.01415   0.00996  -0.0212   0.5510   0.8739
   4.500   1.0412   0.01628   0.01205  -0.0539   0.5484   0.8900
   4.750   1.0697   0.01618   0.01193  -0.0545   0.5464   0.8903
   5.000   1.0950   0.01615   0.01190  -0.0546   0.5445   0.8905
   5.250   1.1209   0.01606   0.01186  -0.0548   0.5430   0.8907
   5.500   1.1456   0.01599   0.01184  -0.0548   0.5415   0.8909
   5.750   1.1691   0.01592   0.01180  -0.0546   0.5397   0.8911
   6.000   1.1924   0.01584   0.01175  -0.0544   0.5377   0.8912
   6.250   1.2155   0.01575   0.01168  -0.0541   0.5355   0.8914
   6.500   1.2378   0.01569   0.01163  -0.0537   0.5337   0.8916
   6.750   1.2594   0.01564   0.01158  -0.0531   0.5317   0.8917
   7.000   1.2794   0.01562   0.01157  -0.0523   0.5293   0.8919
   7.250   1.2964   0.01561   0.01162  -0.0509   0.5274   0.8920
   7.500   1.0405   0.01254   0.00848   0.0033   0.5271   0.8781
   7.750   1.0268   0.01264   0.00864   0.0099   0.5245   0.8785
   8.000   1.0172   0.01307   0.00908   0.0154   0.5214   0.8788
   8.250   1.0217   0.01341   0.00943   0.0184   0.5186   0.8790
   8.500   1.0350   0.01359   0.00957   0.0201   0.5153   0.8791
   8.750   1.0218   0.01458   0.01062   0.0254   0.5113   0.8794
   9.000   1.0158   0.01546   0.01153   0.0296   0.5065   0.8797
   9.250   1.0198   0.01604   0.01207   0.0323   0.5014   0.8800
   9.500   1.0143   0.01706   0.01313   0.0362   0.4970   0.8803
   9.750   1.0060   0.01822   0.01431   0.0404   0.4903   0.8806
  10.000   1.0098   0.01894   0.01499   0.0429   0.4847   0.8809
  10.250   0.9960   0.02053   0.01659   0.0474   0.4748   0.8812
  10.500   0.9894   0.02189   0.01793   0.0509   0.4657   0.8815
  10.750   0.9893   0.02300   0.01901   0.0536   0.4575   0.8817
  11.000   0.9824   0.02452   0.02051   0.0568   0.4459   0.8820
  11.250   0.9748   0.02613   0.02207   0.0601   0.4333   0.8822
  11.500   0.9734   0.02747   0.02337   0.0625   0.4227   0.8826
  11.750   0.9635   0.02933   0.02517   0.0657   0.4084   0.8830
  12.000   0.9622   0.03079   0.02659   0.0679   0.3963   0.8831
  12.250   0.9475   0.03308   0.02878   0.0713   0.3780   0.8833
  12.500   0.9515   0.03436   0.03003   0.0727   0.3672   0.8834
  12.750   0.9402   0.03662   0.03220   0.0755   0.3498   0.8836
  13.000   0.9433   0.03807   0.03361   0.0768   0.3382   0.8837
  13.250   0.9447   0.03965   0.03515   0.0782   0.3273   0.8838
  13.500   0.9419   0.04158   0.03701   0.0798   0.3142   0.8840
  13.750   0.9486   0.04292   0.03832   0.0806   0.3027   0.8841
  14.000   0.9498   0.04466   0.04002   0.0817   0.2893   0.8842
  14.250   0.9497   0.04655   0.04184   0.0828   0.2745   0.8843
  14.750   0.9473   0.05062   0.04576   0.0849   0.2434   0.8846
  15.000   0.9493   0.05248   0.04754   0.0857   0.2313   0.8847
  15.250   0.9567   0.05394   0.04898   0.0860   0.2241   0.8848
  15.500   0.9645   0.05543   0.05047   0.0862   0.2181   0.8850
  15.750   0.9756   0.05669   0.05175   0.0862   0.2137   0.8851
  16.000   0.9840   0.05815   0.05320   0.0862   0.2080   0.8852
  16.250   0.9946   0.05946   0.05451   0.0862   0.2033   0.8854
  16.500   1.0076   0.06059   0.05566   0.0859   0.1970   0.8855
  16.750   1.0128   0.06239   0.05745   0.0860   0.1903   0.8856
  17.000   1.0203   0.06401   0.05905   0.0860   0.1771   0.8858
  17.250   1.0013   0.06800   0.06275   0.0871   0.1333   0.8859
  17.500   0.9964   0.07077   0.06543   0.0876   0.1185   0.8860
  17.750   0.9994   0.07289   0.06753   0.0875   0.1118   0.8861
  18.000   1.0048   0.07487   0.06954   0.0873   0.1074   0.8862
  18.250   1.0119   0.07667   0.07135   0.0870   0.1032   0.8864
  18.500   1.0172   0.07867   0.07336   0.0867   0.0986   0.8865
  18.750   1.0235   0.08063   0.07535   0.0863   0.0946   0.8866
  19.000   1.0327   0.08229   0.07704   0.0858   0.0910   0.8867
  19.250   1.0384   0.08429   0.07904   0.0853   0.0860   0.8868
<< Back to NACA 6-H-20 AIRFOIL (n6h20-il)

Polar data table (+)

Polar graphs


<< Back to NACA 6-H-20 AIRFOIL (n6h20-il)