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

FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.43 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s196-il-1000000.txt
Download as CSV file: xf-fx66s196-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-196 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
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.6469   0.10633   0.10424  -0.0619   1.0000   0.0091
 -17.500  -0.7096   0.09053   0.08813  -0.0705   1.0000   0.0088
 -17.250  -0.7045   0.08653   0.08412  -0.0737   0.9994   0.0091
 -17.000  -0.7055   0.07793   0.07532  -0.0829   0.9488   0.0092
 -16.750  -0.7071   0.06788   0.06498  -0.0955   0.9364   0.0091
 -16.500  -0.6837   0.05962   0.05637  -0.1103   0.9116   0.0093
 -16.250  -0.6700   0.05520   0.05157  -0.1169   0.8615   0.0095
 -16.000  -0.6711   0.05226   0.04840  -0.1182   0.8286   0.0096
 -15.750  -0.6781   0.04896   0.04488  -0.1190   0.8076   0.0096
 -15.500  -0.6742   0.04690   0.04268  -0.1196   0.7893   0.0099
 -15.250  -0.6736   0.04458   0.04021  -0.1200   0.7734   0.0099
 -15.000  -0.6765   0.04199   0.03744  -0.1202   0.7609   0.0100
 -14.750  -0.6731   0.04011   0.03544  -0.1203   0.7500   0.0101
 -14.500  -0.6657   0.03866   0.03386  -0.1204   0.7395   0.0103
 -14.250  -0.6610   0.03699   0.03207  -0.1204   0.7305   0.0104
 -14.000  -0.6599   0.03509   0.03002  -0.1200   0.7221   0.0107
 -13.750  -0.6612   0.03297   0.02777  -0.1191   0.7149   0.0108
 -13.500  -0.6583   0.03134   0.02604  -0.1184   0.7078   0.0111
 -13.250  -0.6537   0.02981   0.02442  -0.1176   0.7017   0.0112
 -13.000  -0.6424   0.02885   0.02343  -0.1173   0.6954   0.0115
 -12.750  -0.6333   0.02774   0.02225  -0.1167   0.6899   0.0118
 -12.500  -0.6240   0.02660   0.02104  -0.1160   0.6844   0.0119
 -12.250  -0.6137   0.02560   0.01997  -0.1153   0.6787   0.0122
 -12.000  -0.6026   0.02465   0.01894  -0.1145   0.6736   0.0125
 -11.750  -0.5908   0.02374   0.01797  -0.1138   0.6684   0.0128
 -11.500  -0.5785   0.02291   0.01707  -0.1130   0.6631   0.0130
 -11.250  -0.5681   0.02196   0.01605  -0.1119   0.6585   0.0132
 -11.000  -0.5552   0.02117   0.01520  -0.1110   0.6540   0.0134
 -10.750  -0.5426   0.02042   0.01437  -0.1100   0.6496   0.0135
 -10.500  -0.5374   0.01929   0.01315  -0.1082   0.6451   0.0138
 -10.250  -0.5320   0.01819   0.01200  -0.1064   0.6419   0.0140
 -10.000  -0.5272   0.01725   0.01102  -0.1043   0.6382   0.0145
  -9.750  -0.5232   0.01663   0.01035  -0.1015   0.6346   0.0148
  -9.500  -0.5093   0.01620   0.00985  -0.1000   0.6309   0.0152
  -9.250  -0.4920   0.01576   0.00938  -0.0989   0.6278   0.0156
  -9.000  -0.4737   0.01530   0.00888  -0.0980   0.6250   0.0161
  -8.750  -0.4538   0.01489   0.00843  -0.0972   0.6218   0.0166
  -8.500  -0.4335   0.01449   0.00796  -0.0965   0.6187   0.0169
  -8.250  -0.4124   0.01412   0.00753  -0.0958   0.6157   0.0174
  -8.000  -0.3930   0.01358   0.00695  -0.0950   0.6128   0.0185
  -7.750  -0.3696   0.01324   0.00659  -0.0947   0.6104   0.0194
  -7.500  -0.3454   0.01293   0.00626  -0.0945   0.6078   0.0204
  -7.250  -0.3207   0.01266   0.00594  -0.0943   0.6050   0.0214
  -7.000  -0.2976   0.01226   0.00549  -0.0939   0.6019   0.0235
  -6.750  -0.2729   0.01201   0.00521  -0.0937   0.5986   0.0260
  -6.500  -0.2480   0.01166   0.00486  -0.0936   0.5964   0.0305
  -6.250  -0.2224   0.01135   0.00457  -0.0936   0.5940   0.0367
  -6.000  -0.1968   0.01106   0.00431  -0.0936   0.5917   0.0457
  -5.750  -0.1707   0.01081   0.00408  -0.0936   0.5894   0.0570
  -5.500  -0.1451   0.01051   0.00385  -0.0937   0.5872   0.0755
  -5.250  -0.1195   0.01023   0.00362  -0.0937   0.5849   0.0987
  -4.750  -0.0687   0.00946   0.00315  -0.0938   0.5813   0.1831
  -4.500  -0.0444   0.00890   0.00286  -0.0938   0.5797   0.2555
  -4.250  -0.0219   0.00813   0.00250  -0.0936   0.5780   0.3661
  -4.000   0.0018   0.00761   0.00238  -0.0933   0.5764   0.4682
  -3.750   0.0311   0.00768   0.00240  -0.0937   0.5747   0.5013
  -3.500   0.0601   0.00774   0.00242  -0.0941   0.5731   0.5151
  -3.250   0.0888   0.00778   0.00244  -0.0944   0.5714   0.5230
  -3.000   0.1179   0.00788   0.00244  -0.0947   0.5696   0.5282
  -2.750   0.1464   0.00793   0.00247  -0.0950   0.5675   0.5331
  -2.500   0.1756   0.00797   0.00250  -0.0954   0.5665   0.5380
  -2.250   0.2049   0.00805   0.00253  -0.0958   0.5655   0.5434
  -2.000   0.2336   0.00804   0.00256  -0.0961   0.5643   0.5489
  -1.750   0.2627   0.00808   0.00258  -0.0965   0.5630   0.5519
  -1.500   0.2918   0.00811   0.00259  -0.0969   0.5616   0.5541
  -1.250   0.3208   0.00819   0.00263  -0.0973   0.5602   0.5578
  -1.000   0.3495   0.00823   0.00267  -0.0976   0.5589   0.5633
  -0.750   0.3784   0.00828   0.00272  -0.0980   0.5576   0.5665
  -0.500   0.4072   0.00833   0.00275  -0.0983   0.5564   0.5684
  -0.250   0.4361   0.00838   0.00278  -0.0987   0.5551   0.5699
   0.000   0.4649   0.00845   0.00281  -0.0991   0.5536   0.5708
   0.250   0.4938   0.00855   0.00288  -0.0996   0.5520   0.5718
   0.500   0.5227   0.00859   0.00291  -0.1000   0.5510   0.5730
   0.750   0.5515   0.00862   0.00294  -0.1004   0.5502   0.5741
   1.000   0.5803   0.00865   0.00297  -0.1008   0.5493   0.5747
   1.250   0.6091   0.00867   0.00300  -0.1012   0.5483   0.5750
   1.500   0.6378   0.00870   0.00303  -0.1016   0.5471   0.5753
   1.750   0.6663   0.00872   0.00306  -0.1020   0.5460   0.5757
   2.000   0.6948   0.00873   0.00308  -0.1024   0.5448   0.5763
   2.250   0.7233   0.00875   0.00311  -0.1027   0.5437   0.5769
   2.500   0.7517   0.00878   0.00315  -0.1031   0.5426   0.5775
   2.750   0.7800   0.00881   0.00320  -0.1035   0.5414   0.5781
   3.000   0.8083   0.00886   0.00325  -0.1038   0.5400   0.5787
   3.250   0.8365   0.00893   0.00333  -0.1041   0.5383   0.5794
   3.500   0.8651   0.00907   0.00346  -0.1046   0.5363   0.5802
   3.750   0.8929   0.00909   0.00353  -0.1048   0.5354   0.5811
   4.000   0.9206   0.00912   0.00360  -0.1051   0.5342   0.5818
   4.250   0.9483   0.00915   0.00367  -0.1053   0.5327   0.5826
   4.500   0.9760   0.00919   0.00375  -0.1056   0.5313   0.5833
   4.750   1.0036   0.00923   0.00382  -0.1058   0.5296   0.5841
   5.000   1.0310   0.00927   0.00388  -0.1060   0.5277   0.5850
   5.250   1.0582   0.00931   0.00394  -0.1061   0.5258   0.5859
   5.500   1.0855   0.00940   0.00404  -0.1063   0.5234   0.5871
   5.750   1.1134   0.00955   0.00420  -0.1067   0.5210   0.5882
   6.000   1.1394   0.00956   0.00427  -0.1066   0.5193   0.5895
   6.250   1.1652   0.00957   0.00434  -0.1065   0.5164   0.5905
   6.500   1.1909   0.00958   0.00439  -0.1063   0.5132   0.5916
   6.750   1.2156   0.00960   0.00444  -0.1060   0.5088   0.5935
   7.000   1.2405   0.00968   0.00455  -0.1057   0.5046   0.5953
   7.250   1.2647   0.00967   0.00463  -0.1053   0.5005   0.5971
   7.500   1.2885   0.00969   0.00470  -0.1048   0.4954   0.5991
   7.750   1.3105   0.00975   0.00479  -0.1040   0.4881   0.6013
   8.000   1.3342   0.00979   0.00489  -0.1035   0.4811   0.6036
   8.250   1.3556   0.00990   0.00502  -0.1026   0.4749   0.6060
   8.500   1.3757   0.01001   0.00515  -0.1014   0.4630   0.6087
   8.750   1.3886   0.01020   0.00534  -0.0988   0.4490   0.6121
   9.000   1.3992   0.01051   0.00564  -0.0959   0.4344   0.6157
   9.250   1.4022   0.01109   0.00614  -0.0918   0.4070   0.6197
   9.500   1.3888   0.01227   0.00713  -0.0852   0.3705   0.6234
   9.750   1.3719   0.01384   0.00855  -0.0790   0.3323   0.6282
  10.000   1.3537   0.01589   0.01045  -0.0735   0.2992   0.6333
  10.250   1.3417   0.01805   0.01250  -0.0696   0.2701   0.6386
  10.500   1.3245   0.02091   0.01525  -0.0659   0.2398   0.6445
  10.750   1.3081   0.02406   0.01829  -0.0630   0.2094   0.6510
  11.000   1.3024   0.02665   0.02083  -0.0613   0.1905   0.6588
  11.250   1.2911   0.02980   0.02391  -0.0594   0.1649   0.6668
  11.500   1.2828   0.03286   0.02691  -0.0580   0.1426   0.6762
  11.750   1.2751   0.03605   0.03003  -0.0569   0.1199   0.6870
  12.000   1.2692   0.03924   0.03316  -0.0562   0.0986   0.6996
  12.250   1.2668   0.04232   0.03619  -0.0559   0.0785   0.7143
  12.500   1.2675   0.04531   0.03916  -0.0561   0.0622   0.7305
  12.750   1.2726   0.04830   0.04215  -0.0571   0.0471   0.7528
  13.000   1.2884   0.05110   0.04504  -0.0597   0.0369   0.7913
  13.250   1.3165   0.05518   0.04927  -0.0666   0.0231   0.8646
  13.500   1.3481   0.05905   0.05329  -0.0732   0.0161   1.0000
  13.750   1.3545   0.06122   0.05549  -0.0729   0.0142   1.0000
  14.000   1.3572   0.06376   0.05805  -0.0725   0.0124   1.0000
  14.250   1.3650   0.06578   0.06011  -0.0722   0.0115   1.0000
  14.500   1.3705   0.06808   0.06244  -0.0719   0.0107   1.0000
  14.750   1.3736   0.07065   0.06504  -0.0716   0.0099   1.0000
  15.000   1.3797   0.07290   0.06734  -0.0714   0.0093   1.0000
  15.250   1.3847   0.07532   0.06980  -0.0712   0.0090   1.0000
  15.500   1.3909   0.07757   0.07210  -0.0710   0.0086   1.0000
  15.750   1.3952   0.08004   0.07461  -0.0709   0.0081   1.0000
  16.000   1.3993   0.08261   0.07722  -0.0708   0.0079   1.0000
  16.250   1.3958   0.08607   0.08075  -0.0705   0.0073   1.0000
<< Back to FX 66-S-196 AIRFOIL (fx66s196-il)

Polar data table (+)

Polar graphs


<< Back to FX 66-S-196 AIRFOIL (fx66s196-il)