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FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il)
Reynolds number: 50,000
Max Cl/Cd: 7.82 at α=12°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66196v-il-50000-n5.txt
Download as CSV file: xf-fx66196v-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-196 V1 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2707   0.10855   0.10239  -0.0822   0.9493   0.0524
 -12.250  -0.2735   0.10008   0.09389  -0.0890   0.9385   0.0521
 -12.000  -0.2846   0.09082   0.08456  -0.0966   0.9278   0.0516
 -11.750  -0.3043   0.08166   0.07526  -0.1045   0.9162   0.0510
 -11.500  -0.3248   0.07387   0.06725  -0.1114   0.9035   0.0504
 -11.250  -0.3433   0.06764   0.06073  -0.1166   0.8899   0.0501
 -11.000  -0.3572   0.06293   0.05571  -0.1198   0.8761   0.0501
 -10.750  -0.3693   0.05915   0.05161  -0.1215   0.8625   0.0506
 -10.500  -0.3797   0.05618   0.04834  -0.1216   0.8490   0.0513
 -10.250  -0.3890   0.05374   0.04559  -0.1207   0.8360   0.0521
 -10.000  -0.3962   0.05167   0.04317  -0.1190   0.8247   0.0530
  -9.750  -0.3949   0.04938   0.04041  -0.1178   0.8160   0.0542
  -9.500  -0.3840   0.04732   0.03815  -0.1167   0.8060   0.0555
  -9.250  -0.3629   0.04541   0.03608  -0.1164   0.7989   0.0574
  -9.000  -0.3460   0.04401   0.03452  -0.1155   0.7902   0.0603
  -8.750  -0.3234   0.04250   0.03265  -0.1149   0.7838   0.0646
  -8.500  -0.2915   0.04125   0.03131  -0.1145   0.7763   0.0690
  -8.250  -0.2611   0.04020   0.03013  -0.1140   0.7706   0.0748
  -8.000  -0.2409   0.03943   0.02926  -0.1126   0.7635   0.0815
  -7.750  -0.2259   0.03865   0.02844  -0.1109   0.7571   0.0887
  -7.500  -0.2157   0.03782   0.02758  -0.1090   0.7514   0.0971
  -7.250  -0.2093   0.03715   0.02686  -0.1069   0.7443   0.1066
  -7.000  -0.2037   0.03609   0.02587  -0.1050   0.7392   0.1190
  -6.750  -0.2033   0.03522   0.02511  -0.1027   0.7329   0.1346
  -6.500  -0.2050   0.03408   0.02420  -0.1003   0.7270   0.1577
  -6.250  -0.2059   0.03249   0.02296  -0.0983   0.7227   0.2037
  -6.000  -0.2122   0.03156   0.02279  -0.0950   0.7162   0.2867
  -5.750  -0.1951   0.03320   0.02511  -0.0905   0.7115   0.4318
  -5.500  -0.1792   0.03362   0.02516  -0.0892   0.7079   0.4865
  -5.250  -0.1637   0.03483   0.02618  -0.0865   0.7033   0.5192
  -5.000  -0.1477   0.03641   0.02767  -0.0829   0.6982   0.5451
  -4.750  -0.1290   0.03740   0.02844  -0.0802   0.6944   0.5708
  -4.500  -0.1024   0.03841   0.02925  -0.0776   0.6917   0.5893
  -4.250  -0.0925   0.03898   0.02970  -0.0749   0.6868   0.6034
  -4.000  -0.0796   0.03954   0.03013  -0.0724   0.6820   0.6141
  -3.750  -0.0605   0.03971   0.03012  -0.0710   0.6787   0.6236
  -3.500  -0.0411   0.03945   0.02961  -0.0706   0.6762   0.6344
  -3.250  -0.0275   0.03990   0.02995  -0.0685   0.6728   0.6402
  -3.000  -0.0283   0.04038   0.03036  -0.0662   0.6676   0.6480
  -2.750  -0.0136   0.04060   0.03044  -0.0649   0.6644   0.6534
  -2.500   0.0070   0.04064   0.03031  -0.0644   0.6620   0.6593
  -2.250   0.0313   0.04039   0.02983  -0.0651   0.6600   0.6665
  -2.000   0.0201   0.04164   0.03113  -0.0610   0.6537   0.6703
  -1.750   0.0292   0.04216   0.03156  -0.0596   0.6499   0.6750
  -1.500   0.0487   0.04232   0.03154  -0.0599   0.6473   0.6802
  -1.250   0.0711   0.04248   0.03156  -0.0601   0.6455   0.6843
  -1.000   0.0957   0.04262   0.03156  -0.0602   0.6440   0.6880
  -0.750   0.0616   0.04505   0.03410  -0.0551   0.6371   0.6923
  -0.500   0.0760   0.04571   0.03462  -0.0551   0.6338   0.6973
  -0.250   0.0955   0.04615   0.03496  -0.0549   0.6315   0.7008
   0.000   0.1190   0.04650   0.03521  -0.0551   0.6297   0.7044
   0.250   0.1440   0.04689   0.03547  -0.0558   0.6283   0.7085
   0.500   0.1337   0.04901   0.03757  -0.0540   0.6235   0.7131
   0.750   0.1433   0.05009   0.03862  -0.0532   0.6201   0.7166
   1.000   0.1607   0.05088   0.03934  -0.0532   0.6176   0.7201
   1.250   0.1822   0.05158   0.03995  -0.0536   0.6156   0.7239
   1.500   0.2083   0.05215   0.04041  -0.0546   0.6138   0.7285
   1.750   0.2300   0.05283   0.04104  -0.0548   0.6117   0.7327
   2.000   0.2244   0.05473   0.04297  -0.0530   0.6072   0.7370
   2.250   0.2373   0.05592   0.04412  -0.0529   0.6045   0.7419
   2.500   0.2570   0.05683   0.04498  -0.0533   0.6018   0.7469
   2.750   0.2796   0.05752   0.04565  -0.0535   0.5995   0.7514
   3.000   0.3059   0.05817   0.04627  -0.0542   0.5977   0.7567
   3.250   0.3120   0.05982   0.04791  -0.0538   0.5945   0.7624
   3.500   0.3170   0.06130   0.04945  -0.0528   0.5906   0.7677
   3.750   0.3335   0.06239   0.05054  -0.0529   0.5874   0.7746
   4.000   0.3549   0.06326   0.05144  -0.0530   0.5847   0.7818
   4.250   0.3796   0.06406   0.05225  -0.0535   0.5827   0.7900
   4.500   0.3865   0.06556   0.05380  -0.0528   0.5787   0.7979
   4.750   0.3937   0.06700   0.05531  -0.0521   0.5739   0.8071
   5.000   0.4115   0.06798   0.05635  -0.0520   0.5705   0.8170
   5.250   0.4353   0.06875   0.05720  -0.0522   0.5679   0.8294
   5.500   0.4530   0.06977   0.05830  -0.0520   0.5646   0.8441
   5.750   0.4519   0.07155   0.06021  -0.0508   0.5590   0.8616
   6.000   0.4704   0.07253   0.06132  -0.0510   0.5550   0.8891
   6.250   0.4993   0.07310   0.06205  -0.0525   0.5518   0.9897
   6.500   0.5090   0.07504   0.06397  -0.0530   0.5470   1.0000
   6.750   0.5216   0.07687   0.06581  -0.0539   0.5417   1.0000
   7.000   0.5475   0.07813   0.06706  -0.0552   0.5379   1.0000
   7.250   0.5790   0.07916   0.06809  -0.0566   0.5354   1.0000
   7.500   0.5736   0.08164   0.07060  -0.0562   0.5273   1.0000
   7.750   0.5977   0.08286   0.07182  -0.0570   0.5229   1.0000
   8.000   0.6294   0.08375   0.07275  -0.0580   0.5201   1.0000
   8.250   0.6228   0.08628   0.07533  -0.0574   0.5110   1.0000
   8.500   0.6482   0.08738   0.07647  -0.0581   0.5069   1.0000
   8.750   0.6570   0.08931   0.07845  -0.0581   0.5005   1.0000
   9.000   0.6700   0.09100   0.08022  -0.0582   0.4941   1.0000
   9.250   0.6968   0.09203   0.08133  -0.0588   0.4906   1.0000
   9.750   0.7189   0.09556   0.08501  -0.0589   0.4769   1.0000
  10.000   0.7270   0.09751   0.08704  -0.0589   0.4697   1.0000
  10.250   0.7438   0.09889   0.08854  -0.0590   0.4631   1.0000
  10.500   0.7729   0.09958   0.08933  -0.0595   0.4595   1.0000
  10.750   0.7690   0.10221   0.09206  -0.0592   0.4490   1.0000
  11.000   0.7987   0.10275   0.09274  -0.0595   0.4453   1.0000
  11.250   0.7943   0.10552   0.09561  -0.0594   0.4346   1.0000
  11.500   0.8235   0.10594   0.09617  -0.0596   0.4305   1.0000
  11.750   0.8205   0.10870   0.09904  -0.0596   0.4197   1.0000
  12.000   0.8511   0.10879   0.09928  -0.0597   0.4157   1.0000
  12.250   0.8496   0.11142   0.10205  -0.0597   0.4045   1.0000
  12.500   0.8560   0.11345   0.10422  -0.0598   0.3950   1.0000
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