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AVISTAR (avistar-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AVISTAR (avistar-il)
Reynolds number: 50,000
Max Cl/Cd: 31.06 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-avistar-il-50000-n5.txt
Download as CSV file: xf-avistar-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AVISTAR                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3093   0.12783   0.12065  -0.0384   1.0000   0.1680
 -11.250  -0.2989   0.12366   0.11652  -0.0384   1.0000   0.1689
 -10.750  -0.4420   0.11046   0.10263  -0.0434   1.0000   0.0824
 -10.500  -0.4340   0.10711   0.09930  -0.0435   1.0000   0.0817
 -10.250  -0.4313   0.10320   0.09541  -0.0446   1.0000   0.0809
 -10.000  -0.4321   0.09884   0.09111  -0.0463   1.0000   0.0799
  -9.750  -0.4366   0.09391   0.08623  -0.0486   1.0000   0.0786
  -9.250  -0.5374   0.07733   0.06954  -0.0583   1.0000   0.0719
  -9.000  -0.5524   0.07462   0.06685  -0.0559   1.0000   0.0716
  -8.750  -0.5690   0.07205   0.06427  -0.0529   1.0000   0.0714
  -8.500  -0.5857   0.06968   0.06187  -0.0495   1.0000   0.0711
  -8.250  -0.6023   0.06740   0.05951  -0.0456   1.0000   0.0708
  -8.000  -0.6164   0.06513   0.05713  -0.0418   1.0000   0.0705
  -7.750  -0.6280   0.06279   0.05466  -0.0381   1.0000   0.0701
  -7.500  -0.6369   0.06038   0.05207  -0.0346   1.0000   0.0698
  -7.250  -0.6428   0.05797   0.04943  -0.0313   1.0000   0.0694
  -7.000  -0.6457   0.05556   0.04678  -0.0282   1.0000   0.0691
  -6.750  -0.6419   0.05300   0.04391  -0.0261   0.9987   0.0689
  -6.500  -0.6195   0.04986   0.04029  -0.0273   0.9916   0.0690
  -6.250  -0.5947   0.04712   0.03704  -0.0286   0.9844   0.0700
  -6.000  -0.5693   0.04474   0.03414  -0.0294   0.9764   0.0711
  -5.750  -0.5397   0.04259   0.03149  -0.0306   0.9691   0.0718
  -5.500  -0.5086   0.04062   0.02915  -0.0318   0.9615   0.0722
  -5.250  -0.4759   0.03871   0.02703  -0.0333   0.9543   0.0728
  -5.000  -0.4422   0.03708   0.02528  -0.0349   0.9469   0.0742
  -4.750  -0.4069   0.03571   0.02380  -0.0367   0.9401   0.0765
  -4.500  -0.3738   0.03453   0.02246  -0.0379   0.9321   0.0788
  -4.250  -0.3319   0.03333   0.02106  -0.0405   0.9268   0.0806
  -4.000  -0.3018   0.03245   0.02005  -0.0408   0.9178   0.0819
  -3.750  -0.2628   0.03138   0.01901  -0.0429   0.9117   0.0846
  -3.500  -0.2298   0.03058   0.01819  -0.0440   0.9042   0.0885
  -3.250  -0.1983   0.02991   0.01742  -0.0447   0.8959   0.0922
  -3.000  -0.1602   0.02909   0.01652  -0.0467   0.8902   0.0958
  -2.750  -0.1388   0.02859   0.01599  -0.0457   0.8789   0.1003
  -2.500  -0.1029   0.02788   0.01523  -0.0473   0.8725   0.1090
  -2.250  -0.0810   0.02744   0.01480  -0.0465   0.8614   0.1189
  -2.000  -0.0488   0.02654   0.01413  -0.0474   0.8544   0.1480
  -1.750  -0.0420   0.02465   0.01407  -0.0443   0.8434   0.4682
  -1.500  -0.0166   0.02399   0.01438  -0.0417   0.8364   0.7019
  -1.250   0.0277   0.02406   0.01470  -0.0427   0.8291   0.8170
  -1.000   0.0913   0.02439   0.01496  -0.0476   0.8225   0.8950
  -0.750   0.2056   0.02479   0.01508  -0.0622   0.8204   0.9566
  -0.500   0.2587   0.02465   0.01473  -0.0672   0.8131   0.9724
  -0.250   0.3032   0.02466   0.01461  -0.0712   0.8023   0.9892
   0.000   0.3476   0.02446   0.01426  -0.0749   0.7945   1.0000
   0.250   0.3611   0.02454   0.01426  -0.0730   0.7816   1.0000
   0.500   0.3767   0.02461   0.01424  -0.0714   0.7705   1.0000
   0.750   0.3958   0.02460   0.01413  -0.0701   0.7607   1.0000
   1.000   0.4093   0.02483   0.01429  -0.0681   0.7490   1.0000
   1.250   0.4317   0.02480   0.01416  -0.0671   0.7410   1.0000
   1.500   0.4443   0.02517   0.01448  -0.0650   0.7292   1.0000
   1.750   0.4690   0.02514   0.01437  -0.0642   0.7222   1.0000
   2.000   0.4816   0.02562   0.01481  -0.0621   0.7105   1.0000
   2.250   0.5078   0.02559   0.01471  -0.0615   0.7039   1.0000
   2.500   0.5204   0.02615   0.01527  -0.0594   0.6925   1.0000
   2.750   0.5478   0.02610   0.01516  -0.0589   0.6861   1.0000
   3.000   0.5614   0.02661   0.01567  -0.0568   0.6740   1.0000
   3.250   0.5848   0.02665   0.01568  -0.0556   0.6645   1.0000
   3.500   0.6067   0.02673   0.01574  -0.0543   0.6536   1.0000
   3.750   0.6253   0.02699   0.01601  -0.0526   0.6421   1.0000
   4.000   0.6537   0.02683   0.01583  -0.0520   0.6337   1.0000
   4.250   0.6691   0.02735   0.01640  -0.0500   0.6220   1.0000
   4.500   0.6971   0.02728   0.01632  -0.0494   0.6141   1.0000
   4.750   0.7133   0.02781   0.01692  -0.0476   0.6028   1.0000
   5.000   0.7369   0.02801   0.01717  -0.0466   0.5936   1.0000
   5.250   0.7583   0.02832   0.01754  -0.0453   0.5835   1.0000
   5.500   0.7781   0.02873   0.01803  -0.0439   0.5731   1.0000
   5.750   0.8076   0.02850   0.01783  -0.0433   0.5623   1.0000
   6.000   0.8295   0.02828   0.01761  -0.0413   0.5441   1.0000
   6.250   0.8434   0.02831   0.01763  -0.0383   0.5212   1.0000
   6.500   0.8586   0.02832   0.01764  -0.0356   0.4982   1.0000
   6.750   0.8742   0.02843   0.01773  -0.0330   0.4765   1.0000
   7.000   0.8888   0.02862   0.01791  -0.0304   0.4548   1.0000
   7.250   0.8974   0.02914   0.01848  -0.0273   0.4313   1.0000
   7.500   0.9056   0.02967   0.01907  -0.0242   0.4060   1.0000
   7.750   0.9114   0.03034   0.01976  -0.0210   0.3771   1.0000
   8.000   0.9153   0.03105   0.02037  -0.0174   0.3410   1.0000
   8.250   0.9176   0.03194   0.02099  -0.0137   0.3017   1.0000
   8.500   0.9173   0.03327   0.02204  -0.0103   0.2615   1.0000
   8.750   0.9150   0.03506   0.02357  -0.0073   0.2143   1.0000
   9.250   0.8882   0.04123   0.02865  -0.0019   0.0948   1.0000
   9.500   0.8849   0.04391   0.03121  -0.0003   0.0850   1.0000
   9.750   0.8833   0.04654   0.03381   0.0010   0.0796   1.0000
  10.000   0.8836   0.04908   0.03641   0.0020   0.0756   1.0000
  10.250   0.8826   0.05183   0.03921   0.0028   0.0728   1.0000
  10.500   0.8821   0.05461   0.04202   0.0035   0.0708   1.0000
  10.750   0.8840   0.05719   0.04472   0.0041   0.0691   1.0000
  11.000   0.8858   0.05981   0.04746   0.0046   0.0676   1.0000
  11.250   0.8879   0.06241   0.05015   0.0051   0.0663   1.0000
  11.500   0.8904   0.06497   0.05277   0.0055   0.0649   1.0000
  11.750   0.8935   0.06745   0.05527   0.0061   0.0636   1.0000
  12.000   0.8990   0.06963   0.05747   0.0068   0.0622   1.0000
  12.250   0.9077   0.07153   0.05951   0.0075   0.0607   1.0000
  12.500   0.9174   0.07331   0.06139   0.0082   0.0592   1.0000
  12.750   0.9291   0.07485   0.06300   0.0092   0.0578   1.0000
  13.000   0.9445   0.07599   0.06419   0.0104   0.0567   1.0000
  13.250   0.9656   0.07657   0.06481   0.0121   0.0557   1.0000
  13.500   0.9992   0.07621   0.06442   0.0143   0.0547   1.0000
  13.750   1.0192   0.07755   0.06597   0.0154   0.0542   1.0000
  14.000   1.0333   0.07956   0.06822   0.0160   0.0535   1.0000
  14.250   1.0420   0.08213   0.07103   0.0163   0.0528   1.0000
  14.500   1.0465   0.08513   0.07427   0.0164   0.0522   1.0000
  14.750   1.0473   0.08853   0.07790   0.0161   0.0516   1.0000
  15.000   1.0453   0.09231   0.08190   0.0155   0.0511   1.0000
  15.250   1.0400   0.09653   0.08636   0.0146   0.0508   1.0000
  15.500   1.0313   0.10132   0.09139   0.0131   0.0506   1.0000
  15.750   1.0185   0.10686   0.09717   0.0110   0.0506   1.0000
  16.000   1.0012   0.11339   0.10396   0.0080   0.0507   1.0000
  16.250   0.9789   0.12125   0.11207   0.0038   0.0510   1.0000
  16.500   0.9513   0.13085   0.12192  -0.0018   0.0515   1.0000
  16.750   0.9207   0.14242   0.13371  -0.0089   0.0522   1.0000
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