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FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 61-163 AIRFOIL (fx61163-il)
Reynolds number: 200,000
Max Cl/Cd: 72.65 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61163-il-200000-n5.txt
Download as CSV file: xf-fx61163-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-163 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5533   0.06026   0.05608  -0.0681   1.0001   0.0102
 -10.750  -0.5702   0.05639   0.05209  -0.0684   1.0001   0.0102
 -10.500  -0.5861   0.05307   0.04865  -0.0678   1.0001   0.0102
 -10.250  -0.6025   0.05020   0.04565  -0.0662   1.0001   0.0102
 -10.000  -0.6128   0.04693   0.04217  -0.0659   0.9920   0.0102
  -9.750  -0.6101   0.04292   0.03781  -0.0683   0.9597   0.0102
  -9.500  -0.5898   0.03842   0.03286  -0.0731   0.9292   0.0103
  -9.250  -0.5566   0.03462   0.02865  -0.0785   0.9029   0.0105
  -9.000  -0.5194   0.03210   0.02579  -0.0832   0.8726   0.0109
  -8.750  -0.4875   0.03053   0.02394  -0.0860   0.8418   0.0116
  -8.500  -0.4622   0.02896   0.02202  -0.0869   0.8157   0.0123
  -8.250  -0.4390   0.02738   0.02009  -0.0869   0.7953   0.0128
  -8.000  -0.4162   0.02590   0.01829  -0.0863   0.7785   0.0130
  -7.750  -0.3933   0.02463   0.01678  -0.0857   0.7647   0.0132
  -7.500  -0.3705   0.02355   0.01550  -0.0849   0.7525   0.0134
  -7.250  -0.3480   0.02260   0.01440  -0.0842   0.7415   0.0137
  -7.000  -0.3258   0.02174   0.01342  -0.0835   0.7319   0.0139
  -6.750  -0.3056   0.02072   0.01233  -0.0829   0.7230   0.0144
  -6.500  -0.2838   0.01991   0.01145  -0.0827   0.7149   0.0150
  -6.250  -0.2611   0.01919   0.01064  -0.0826   0.7079   0.0158
  -6.000  -0.2375   0.01850   0.00986  -0.0827   0.7015   0.0167
  -5.750  -0.2128   0.01792   0.00915  -0.0830   0.6952   0.0182
  -5.500  -0.1880   0.01727   0.00842  -0.0834   0.6897   0.0207
  -5.250  -0.1618   0.01674   0.00780  -0.0838   0.6838   0.0238
  -5.000  -0.1351   0.01617   0.00715  -0.0843   0.6788   0.0296
  -4.750  -0.1078   0.01553   0.00654  -0.0851   0.6745   0.0516
  -4.500  -0.0801   0.01406   0.00574  -0.0875   0.6697   0.1936
  -4.250  -0.0488   0.01225   0.00544  -0.0909   0.6651   0.5217
  -4.000  -0.0215   0.01270   0.00598  -0.0902   0.6612   0.5853
  -3.750   0.0068   0.01313   0.00635  -0.0899   0.6568   0.6103
  -3.500   0.0344   0.01349   0.00663  -0.0894   0.6525   0.6230
  -3.250   0.0636   0.01361   0.00659  -0.0897   0.6487   0.6299
  -3.000   0.0920   0.01371   0.00657  -0.0897   0.6451   0.6337
  -2.750   0.1220   0.01373   0.00648  -0.0904   0.6408   0.6396
  -2.500   0.1512   0.01378   0.00642  -0.0907   0.6368   0.6440
  -2.250   0.1793   0.01388   0.00644  -0.0907   0.6332   0.6472
  -2.000   0.2085   0.01395   0.00640  -0.0911   0.6300   0.6511
  -1.750   0.2399   0.01391   0.00625  -0.0922   0.6259   0.6570
  -1.500   0.2675   0.01399   0.00631  -0.0921   0.6222   0.6593
  -1.250   0.2957   0.01407   0.00633  -0.0922   0.6188   0.6620
  -0.750   0.3549   0.01413   0.00626  -0.0933   0.6114   0.6691
  -0.500   0.3849   0.01413   0.00620  -0.0941   0.6071   0.6726
  -0.250   0.4129   0.01420   0.00624  -0.0941   0.6033   0.6747
   0.000   0.4414   0.01428   0.00626  -0.0943   0.6000   0.6770
   0.250   0.4700   0.01432   0.00632  -0.0947   0.5959   0.6799
   0.500   0.4997   0.01435   0.00633  -0.0953   0.5920   0.6834
   0.750   0.5305   0.01438   0.00629  -0.0962   0.5885   0.6869
   1.000   0.5585   0.01447   0.00636  -0.0963   0.5853   0.6888
   1.250   0.5861   0.01453   0.00648  -0.0964   0.5810   0.6910
   1.500   0.6144   0.01458   0.00656  -0.0967   0.5767   0.6934
   1.750   0.6434   0.01464   0.00660  -0.0971   0.5726   0.6962
   2.000   0.6732   0.01469   0.00663  -0.0978   0.5684   0.6994
   2.250   0.7022   0.01473   0.00671  -0.0983   0.5633   0.7021
   2.500   0.7299   0.01479   0.00681  -0.0984   0.5591   0.7038
   2.750   0.7580   0.01488   0.00690  -0.0985   0.5556   0.7058
   3.000   0.7856   0.01496   0.00707  -0.0987   0.5506   0.7082
   3.250   0.8139   0.01503   0.00718  -0.0990   0.5456   0.7108
   3.500   0.8432   0.01510   0.00725  -0.0995   0.5415   0.7135
   3.750   0.8725   0.01518   0.00739  -0.1002   0.5362   0.7163
   4.000   0.8992   0.01524   0.00753  -0.1001   0.5302   0.7180
   4.250   0.9263   0.01531   0.00765  -0.1001   0.5248   0.7199
   4.500   0.9532   0.01540   0.00785  -0.1001   0.5180   0.7221
   4.750   0.9808   0.01549   0.00798  -0.1002   0.5126   0.7244
   5.000   1.0083   0.01559   0.00818  -0.1004   0.5052   0.7271
   5.250   1.0362   0.01566   0.00827  -0.1007   0.4974   0.7298
   5.500   1.0629   0.01576   0.00847  -0.1007   0.4885   0.7319
   5.750   1.0886   0.01586   0.00863  -0.1004   0.4804   0.7338
   6.000   1.1139   0.01597   0.00884  -0.1002   0.4698   0.7359
   6.250   1.1394   0.01612   0.00906  -0.0999   0.4591   0.7381
   6.500   1.1649   0.01628   0.00928  -0.0998   0.4483   0.7404
   6.750   1.1895   0.01648   0.00950  -0.0994   0.4335   0.7430
   7.000   1.2137   0.01673   0.00976  -0.0991   0.4169   0.7457
   7.250   1.2358   0.01701   0.01008  -0.0983   0.4016   0.7475
   7.500   1.2578   0.01734   0.01045  -0.0976   0.3872   0.7493
   7.750   1.2791   0.01771   0.01087  -0.0967   0.3721   0.7513
   8.000   1.2997   0.01814   0.01134  -0.0958   0.3564   0.7537
   8.250   1.3181   0.01867   0.01186  -0.0946   0.3373   0.7564
   8.500   1.3352   0.01928   0.01245  -0.0933   0.3138   0.7590
   8.750   1.3479   0.02007   0.01316  -0.0913   0.2870   0.7612
   9.000   1.3567   0.02096   0.01398  -0.0888   0.2584   0.7631
   9.250   1.3602   0.02197   0.01491  -0.0855   0.2320   0.7653
   9.500   1.3638   0.02322   0.01607  -0.0826   0.2056   0.7679
   9.750   1.3668   0.02462   0.01740  -0.0799   0.1820   0.7708
  10.000   1.3678   0.02626   0.01900  -0.0775   0.1608   0.7737
  10.250   1.3679   0.02812   0.02081  -0.0754   0.1399   0.7762
  10.500   1.3665   0.03025   0.02291  -0.0736   0.1220   0.7783
  10.750   1.3661   0.03251   0.02514  -0.0722   0.1042   0.7807
  11.000   1.3653   0.03498   0.02759  -0.0712   0.0892   0.7833
  11.250   1.3656   0.03745   0.03008  -0.0704   0.0764   0.7861
  11.500   1.3662   0.04001   0.03265  -0.0698   0.0666   0.7892
  11.750   1.3654   0.04267   0.03534  -0.0691   0.0589   0.7918
  12.000   1.3658   0.04525   0.03800  -0.0685   0.0523   0.7944
  12.250   1.3658   0.04792   0.04075  -0.0680   0.0463   0.7973
  12.500   1.3653   0.05068   0.04357  -0.0676   0.0396   0.8002
  12.750   1.3648   0.05349   0.04647  -0.0673   0.0349   0.8032
  13.000   1.3621   0.05654   0.04957  -0.0669   0.0306   0.8060
  13.250   1.3605   0.05950   0.05263  -0.0666   0.0271   0.8088
  13.500   1.3572   0.06274   0.05593  -0.0665   0.0239   0.8120
  13.750   1.3552   0.06596   0.05925  -0.0665   0.0214   0.8156
  14.250   1.3487   0.07282   0.06632  -0.0667   0.0169   0.8233
  14.500   1.3468   0.07619   0.06982  -0.0669   0.0147   0.8277
  14.750   1.3434   0.07987   0.07360  -0.0673   0.0130   0.8324
  15.000   1.3383   0.08378   0.07763  -0.0678   0.0115   0.8371
  15.250   1.3349   0.08750   0.08150  -0.0683   0.0101   0.8425
  15.500   1.3302   0.09153   0.08564  -0.0690   0.0091   0.8486
  15.750   1.3237   0.09579   0.09001  -0.0698   0.0084   0.8551
  16.250   1.3126   0.10416   0.09873  -0.0715   0.0074   0.8736
  16.500   1.3059   0.10840   0.10313  -0.0723   0.0071   0.8885
  16.750   1.2967   0.11235   0.10725  -0.0725   0.0069   0.9235
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