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FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il)
Reynolds number: 50,000
Max Cl/Cd: 4.54 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s196-il-50000.txt
Download as CSV file: xf-fx66s196-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1769   0.12200   0.11623  -0.0733   0.9426   0.3238
 -10.250  -0.3308   0.09826   0.09277  -0.0929   0.9389   0.1440
 -10.000  -0.3517   0.09374   0.08830  -0.0934   0.9324   0.1393
  -9.750  -0.4766   0.08707   0.08161  -0.0958   0.9262   0.1326
  -9.500  -0.4980   0.08516   0.07967  -0.0930   0.9209   0.1305
  -9.250  -0.5198   0.08324   0.07774  -0.0898   0.9164   0.1291
  -9.000  -0.5464   0.08093   0.07536  -0.0870   0.9134   0.1275
  -8.750  -0.5733   0.07849   0.07280  -0.0841   0.9116   0.1256
  -8.500  -0.6002   0.07583   0.06995  -0.0812   0.9103   0.1234
  -8.250  -0.6277   0.07279   0.06655  -0.0780   0.9097   0.1208
  -8.000  -0.6631   0.07058   0.06371  -0.0731   0.9111   0.1177
  -7.750  -0.6708   0.06853   0.06134  -0.0700   0.9126   0.1165
  -7.500  -0.6740   0.06611   0.05870  -0.0673   0.9149   0.1160
  -7.250  -0.6726   0.06370   0.05600  -0.0652   0.9172   0.1156
  -7.000  -0.8116   0.06788   0.06103  -0.0372   1.0000   0.1165
  -6.750  -0.8014   0.06426   0.05712  -0.0367   1.0000   0.1157
  -6.500  -0.7892   0.06092   0.05342  -0.0363   1.0000   0.1149
  -6.250  -0.7749   0.05782   0.04988  -0.0359   1.0000   0.1147
  -6.000  -0.7588   0.05526   0.04681  -0.0354   1.0000   0.1156
  -5.750  -0.7418   0.05280   0.04400  -0.0350   1.0000   0.1187
  -5.500  -0.7244   0.05105   0.04221  -0.0343   1.0000   0.1228
  -5.250  -0.7052   0.04944   0.04033  -0.0336   1.0000   0.1264
  -5.000  -0.6849   0.04803   0.03849  -0.0327   1.0000   0.1312
  -4.750  -0.6667   0.04680   0.03741  -0.0317   1.0000   0.1387
  -4.500  -0.6475   0.04589   0.03640  -0.0303   1.0000   0.1484
  -4.250  -0.6293   0.04515   0.03570  -0.0289   1.0000   0.1621
  -4.000  -0.6126   0.04436   0.03513  -0.0272   1.0000   0.1801
  -3.750  -0.5959   0.04331   0.03437  -0.0260   1.0000   0.2109
  -3.500  -0.5788   0.04035   0.03312  -0.0262   1.0000   0.3403
  -3.250  -0.5860   0.04429   0.03819  -0.0133   1.0000   0.6089
  -3.000  -0.5865   0.04668   0.04049  -0.0042   1.0000   0.6562
  -2.750  -0.5872   0.04830   0.04203   0.0044   1.0000   0.6903
  -2.500  -0.5859   0.04934   0.04295   0.0117   1.0000   0.7213
  -2.250  -0.5834   0.04999   0.04347   0.0182   1.0000   0.7475
  -2.000  -0.5818   0.05043   0.04379   0.0250   1.0000   0.7745
  -1.750  -0.5800   0.05070   0.04392   0.0314   1.0000   0.8028
  -1.500  -0.5772   0.05084   0.04391   0.0373   1.0000   0.8318
  -1.250  -0.5709   0.05100   0.04393   0.0425   1.0000   0.8602
  -1.000  -0.5517   0.05161   0.04436   0.0452   1.0000   0.8888
  -0.750  -0.5246   0.05226   0.04477   0.0445   1.0000   0.9093
  -0.500  -0.4853   0.05337   0.04559   0.0402   0.9968   0.9211
  -0.250  -0.4456   0.05453   0.04650   0.0353   0.9910   0.9283
   0.000  -0.4063   0.05605   0.04776   0.0303   0.9836   0.9360
   0.250  -0.3710   0.05677   0.04827   0.0260   0.9752   0.9413
   0.500  -0.3335   0.05829   0.04958   0.0212   0.9694   0.9462
   0.750  -0.3077   0.05866   0.04979   0.0188   0.9592   0.9506
   1.000  -0.2742   0.05977   0.05074   0.0148   0.9521   0.9545
   1.250  -0.2348   0.06124   0.05204   0.0097   0.9426   0.9584
   1.500  -0.2105   0.06180   0.05249   0.0075   0.9344   0.9623
   1.750  -0.1718   0.06355   0.05410   0.0024   0.9265   0.9664
   2.000  -0.1444   0.06425   0.05471  -0.0004   0.9180   0.9701
   2.250  -0.1050   0.06632   0.05666  -0.0056   0.9101   0.9750
   2.500  -0.0812   0.06677   0.05705  -0.0078   0.9008   0.9792
   2.750  -0.0369   0.06932   0.05951  -0.0139   0.8940   0.9858
   3.000  -0.0125   0.06979   0.05993  -0.0164   0.8836   0.9905
   3.250   0.0267   0.07248   0.06255  -0.0215   0.8777   1.0000
   3.500   0.0224   0.07138   0.06144  -0.0184   0.8665   1.0000
   3.750   0.0323   0.07221   0.06220  -0.0178   0.8599   1.0000
   4.000   0.0388   0.07199   0.06194  -0.0166   0.8489   1.0000
   4.250   0.0495   0.07255   0.06245  -0.0165   0.8419   1.0000
   4.500   0.0732   0.07393   0.06377  -0.0186   0.8332   1.0000
   4.750   0.0889   0.07487   0.06468  -0.0195   0.8257   1.0000
   5.000   0.1181   0.07684   0.06661  -0.0226   0.8177   1.0000
   5.250   0.1353   0.07805   0.06779  -0.0239   0.8109   1.0000
   5.500   0.1640   0.08006   0.06977  -0.0270   0.8027   1.0000
   5.750   0.1826   0.08156   0.07126  -0.0286   0.7957   1.0000
   6.000   0.2120   0.08374   0.07342  -0.0318   0.7872   1.0000
   6.250   0.2292   0.08525   0.07493  -0.0332   0.7799   1.0000
   6.500   0.2598   0.08772   0.07739  -0.0365   0.7716   1.0000
   6.750   0.2744   0.08912   0.07879  -0.0377   0.7634   1.0000
   7.000   0.3065   0.09196   0.08163  -0.0411   0.7557   1.0000
   7.250   0.3181   0.09326   0.08295  -0.0418   0.7476   1.0000
   7.500   0.3499   0.09627   0.08595  -0.0452   0.7400   1.0000
   7.750   0.3593   0.09751   0.08722  -0.0455   0.7315   1.0000
   8.000   0.3908   0.10072   0.09045  -0.0487   0.7243   1.0000
   8.250   0.3974   0.10190   0.09166  -0.0488   0.7157   1.0000
   8.500   0.4295   0.10537   0.09514  -0.0518   0.7085   1.0000
   8.750   0.4336   0.10637   0.09618  -0.0515   0.6987   1.0000
   9.000   0.4681   0.11042   0.10027  -0.0547   0.6922   1.0000
   9.250   0.4684   0.11102   0.10092  -0.0539   0.6816   1.0000
   9.500   0.5063   0.11590   0.10585  -0.0574   0.6761   1.0000
   9.750   0.5019   0.11589   0.10589  -0.0562   0.6647   1.0000
  10.000   0.5210   0.11912   0.10918  -0.0577   0.6589   1.0000
  10.250   0.5342   0.12099   0.11113  -0.0584   0.6480   1.0000
  10.500   0.5418   0.12317   0.11338  -0.0588   0.6402   1.0000
  10.750   0.5662   0.12641   0.11670  -0.0605   0.6311   1.0000
  11.000   0.5681   0.12797   0.11833  -0.0604   0.6213   1.0000
  11.250   0.6045   0.13302   0.12351  -0.0632   0.6138   1.0000
  11.500   0.5982   0.13331   0.12386  -0.0624   0.6023   1.0000
  11.750   0.6099   0.13627   0.12692  -0.0634   0.5953   1.0000
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