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FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il)
Reynolds number: 200,000
Max Cl/Cd: 49.91 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66196v-il-200000.txt
Download as CSV file: xf-fx66196v-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.1550   0.09956   0.09566  -0.1028   0.8314   0.0722
 -12.000  -0.3078   0.06523   0.06115  -0.1241   0.8381   0.0428
 -11.750  -0.3303   0.05996   0.05571  -0.1260   0.8244   0.0413
 -11.500  -0.4276   0.05263   0.04760  -0.1267   0.8097   0.0363
 -11.250  -0.4217   0.04880   0.04361  -0.1263   0.7994   0.0353
 -11.000  -0.4311   0.04584   0.04047  -0.1251   0.7879   0.0348
 -10.750  -0.4437   0.04329   0.03768  -0.1229   0.7773   0.0345
 -10.500  -0.4529   0.04104   0.03513  -0.1202   0.7688   0.0342
 -10.250  -0.4555   0.03861   0.03243  -0.1181   0.7594   0.0340
 -10.000  -0.4523   0.03657   0.03003  -0.1162   0.7522   0.0344
  -9.750  -0.4462   0.03498   0.02812  -0.1143   0.7437   0.0352
  -9.500  -0.4349   0.03336   0.02612  -0.1129   0.7374   0.0356
  -9.250  -0.4213   0.03191   0.02439  -0.1116   0.7295   0.0360
  -9.000  -0.4000   0.02930   0.02153  -0.1111   0.7237   0.0365
  -8.750  -0.3759   0.02738   0.01956  -0.1110   0.7172   0.0378
  -8.500  -0.3538   0.02625   0.01835  -0.1104   0.7108   0.0392
  -8.250  -0.3316   0.02536   0.01731  -0.1099   0.7057   0.0411
  -8.000  -0.3108   0.02461   0.01646  -0.1091   0.6993   0.0434
  -7.750  -0.2886   0.02346   0.01523  -0.1083   0.6942   0.0457
  -7.500  -0.2689   0.02253   0.01429  -0.1075   0.6901   0.0484
  -7.250  -0.2504   0.02186   0.01362  -0.1064   0.6846   0.0517
  -7.000  -0.2324   0.02111   0.01280  -0.1053   0.6799   0.0560
  -6.750  -0.2157   0.02031   0.01199  -0.1043   0.6762   0.0616
  -6.500  -0.1989   0.01955   0.01121  -0.1032   0.6722   0.0687
  -6.250  -0.1813   0.01880   0.01049  -0.1024   0.6678   0.0810
  -6.000  -0.1643   0.01782   0.00961  -0.1016   0.6641   0.1080
  -5.750  -0.1534   0.01593   0.00847  -0.1010   0.6610   0.2442
  -5.500  -0.1369   0.01521   0.00864  -0.1000   0.6579   0.4513
  -5.250  -0.1104   0.01565   0.00899  -0.0997   0.6540   0.4923
  -5.000  -0.0833   0.01614   0.00942  -0.0993   0.6506   0.5140
  -4.750  -0.0555   0.01661   0.00980  -0.0989   0.6476   0.5309
  -4.500  -0.0274   0.01707   0.01016  -0.0986   0.6451   0.5451
  -4.250  -0.0001   0.01753   0.01054  -0.0982   0.6425   0.5580
  -4.000   0.0258   0.01792   0.01090  -0.0978   0.6393   0.5708
  -3.750   0.0522   0.01846   0.01149  -0.0969   0.6362   0.5818
  -3.500   0.0789   0.01886   0.01188  -0.0962   0.6334   0.5920
  -3.250   0.1066   0.01904   0.01190  -0.0963   0.6311   0.6021
  -3.000   0.1342   0.01927   0.01211  -0.0959   0.6291   0.6071
  -2.750   0.1615   0.01940   0.01216  -0.0960   0.6271   0.6122
  -2.500   0.1880   0.01934   0.01200  -0.0966   0.6246   0.6175
  -2.250   0.2141   0.01935   0.01200  -0.0966   0.6222   0.6200
  -2.000   0.2407   0.01943   0.01205  -0.0966   0.6200   0.6231
  -1.750   0.2680   0.01947   0.01205  -0.0969   0.6180   0.6267
  -1.500   0.2963   0.01944   0.01191  -0.0975   0.6163   0.6295
  -1.250   0.3252   0.01941   0.01175  -0.0984   0.6147   0.6327
  -1.000   0.3538   0.01943   0.01168  -0.0990   0.6133   0.6349
  -0.750   0.3810   0.01955   0.01178  -0.0993   0.6118   0.6368
  -0.500   0.4056   0.01972   0.01199  -0.0993   0.6099   0.6389
  -0.250   0.4308   0.01991   0.01220  -0.0994   0.6080   0.6416
   0.000   0.4568   0.02007   0.01235  -0.0996   0.6060   0.6445
   0.250   0.4837   0.02020   0.01244  -0.1000   0.6040   0.6475
   0.500   0.5110   0.02034   0.01253  -0.1006   0.6024   0.6499
   0.750   0.5377   0.02049   0.01269  -0.1008   0.6011   0.6519
   1.000   0.5647   0.02067   0.01288  -0.1011   0.5999   0.6544
   1.250   0.5923   0.02087   0.01307  -0.1015   0.5988   0.6571
   1.500   0.6202   0.02111   0.01328  -0.1020   0.5977   0.6598
   1.750   0.6460   0.02148   0.01364  -0.1023   0.5965   0.6628
   2.000   0.6648   0.02206   0.01430  -0.1017   0.5942   0.6659
   2.250   0.6839   0.02263   0.01500  -0.1010   0.5923   0.6682
   2.500   0.7041   0.02318   0.01564  -0.1004   0.5903   0.6710
   2.750   0.7266   0.02363   0.01613  -0.1001   0.5884   0.6743
   3.000   0.7503   0.02406   0.01659  -0.1001   0.5869   0.6780
   3.250   0.7748   0.02451   0.01706  -0.1002   0.5857   0.6823
   3.500   0.7993   0.02489   0.01750  -0.1001   0.5846   0.6858
   3.750   0.8252   0.02524   0.01789  -0.1003   0.5835   0.6900
   4.000   0.8534   0.02554   0.01821  -0.1008   0.5824   0.6947
   4.250   0.8466   0.02763   0.02049  -0.0970   0.5790   0.6990
   4.500   0.7558   0.03397   0.02713  -0.0836   0.5699   0.7017
   4.750   0.7887   0.03392   0.02713  -0.0844   0.5690   0.7071
   5.000   0.8228   0.03393   0.02715  -0.0856   0.5682   0.7134
   5.250   0.8559   0.03390   0.02721  -0.0865   0.5675   0.7190
   5.500   0.8965   0.03349   0.02683  -0.0884   0.5670   0.7263
   5.750   0.9385   0.03300   0.02640  -0.0903   0.5665   0.7337
   6.000   0.6002   0.05779   0.05129  -0.0626   0.5268   0.7312
   6.250   0.6265   0.05808   0.05167  -0.0627   0.5243   0.7392
   6.500   0.6571   0.05810   0.05177  -0.0630   0.5227   0.7488
   6.750   0.6912   0.05779   0.05154  -0.0634   0.5216   0.7606
   7.000   0.6698   0.06130   0.05515  -0.0611   0.5100   0.7692
   7.250   0.7005   0.06111   0.05507  -0.0612   0.5080   0.7846
   7.500   0.7346   0.06063   0.05473  -0.0615   0.5068   0.8054
   7.750   0.7177   0.06430   0.05854  -0.0601   0.4958   0.8262
   8.000   0.7473   0.06453   0.05901  -0.0608   0.4935   0.8747
   8.250   0.7872   0.06420   0.05884  -0.0629   0.4919   1.0000
   8.500   0.7809   0.06729   0.06194  -0.0624   0.4819   1.0000
   8.750   0.8090   0.06742   0.06208  -0.0628   0.4788   1.0000
   9.000   0.8432   0.06694   0.06162  -0.0632   0.4771   1.0000
   9.250   0.8796   0.06621   0.06093  -0.0636   0.4760   1.0000
   9.500   0.9158   0.06546   0.06024  -0.0640   0.4752   1.0000
   9.750   0.9524   0.06466   0.05949  -0.0643   0.4745   1.0000
  10.250   1.3928   0.03057   0.02567  -0.0856   0.5039   1.0000
  10.500   1.0052   0.06655   0.06156  -0.0633   0.4593   1.0000
  10.750   1.3138   0.03752   0.03279  -0.0730   0.4901   1.0000
  11.000   1.4293   0.02864   0.02388  -0.0784   0.4774   1.0000
  12.000   1.3676   0.03814   0.03376  -0.0659   0.4418   1.0000
  12.250   1.3611   0.04052   0.03620  -0.0644   0.4294   1.0000
  12.500   1.3078   0.04813   0.04390  -0.0618   0.4154   1.0000
  12.750   1.2533   0.05657   0.05239  -0.0600   0.3964   1.0000
  13.000   1.2850   0.05524   0.05110  -0.0598   0.3786   1.0000
  13.250   1.3510   0.04876   0.04386  -0.0587   0.2967   1.0000
  13.500   1.3289   0.05315   0.04795  -0.0571   0.2588   1.0000
  13.750   1.3075   0.05783   0.05241  -0.0558   0.2263   1.0000
  14.000   1.2840   0.06296   0.05729  -0.0549   0.1909   1.0000
  14.250   1.2616   0.06821   0.06228  -0.0542   0.1558   1.0000
  14.500   1.2387   0.07367   0.06743  -0.0538   0.1167   1.0000
  14.750   1.2176   0.07910   0.07255  -0.0535   0.0813   1.0000
  15.000   1.2016   0.08411   0.07734  -0.0534   0.0594   1.0000
  15.250   1.1926   0.08838   0.08153  -0.0534   0.0486   1.0000
  15.500   1.1865   0.09240   0.08554  -0.0535   0.0428   1.0000
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