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AVISTAR (avistar-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AVISTAR (avistar-il)
Reynolds number: 50,000
Max Cl/Cd: 30.51 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-avistar-il-50000.txt
Download as CSV file: xf-avistar-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3746   0.12139   0.11397  -0.0203   1.0000   0.3257
  -9.500  -0.3386   0.11538   0.10793  -0.0199   1.0000   0.3353
  -9.250  -0.3455   0.11328   0.10591  -0.0199   1.0000   0.3470
  -9.000  -0.3505   0.11186   0.10457  -0.0193   1.0000   0.3616
  -8.750  -0.3230   0.10682   0.09953  -0.0192   1.0000   0.3704
  -8.500  -0.3287   0.10474   0.09754  -0.0185   1.0000   0.3839
  -8.250  -0.3455   0.10413   0.09706  -0.0171   1.0000   0.3998
  -8.000  -0.3090   0.09898   0.09187  -0.0170   1.0000   0.4125
  -7.750  -0.3042   0.09619   0.08915  -0.0161   1.0000   0.4253
  -7.500  -0.3120   0.09438   0.08746  -0.0143   1.0000   0.4401
  -7.250  -0.3319   0.09397   0.08721  -0.0110   1.0000   0.4565
  -7.000  -0.3085   0.08947   0.08272  -0.0111   1.0000   0.4607
  -6.750  -0.3091   0.08717   0.08051  -0.0092   1.0000   0.4661
  -6.000  -0.5950   0.06721   0.06073  -0.0156   1.0000   0.2312
  -5.750  -0.6153   0.05934   0.05222  -0.0166   1.0000   0.1931
  -5.500  -0.6168   0.05455   0.04687  -0.0154   1.0000   0.1760
  -5.250  -0.6133   0.05089   0.04252  -0.0137   1.0000   0.1650
  -5.000  -0.6025   0.04812   0.03949  -0.0122   1.0000   0.1614
  -4.750  -0.5907   0.04547   0.03639  -0.0106   1.0000   0.1573
  -4.500  -0.5773   0.04370   0.03374  -0.0086   1.0000   0.1518
  -4.250  -0.5591   0.04170   0.03151  -0.0076   1.0000   0.1502
  -4.000  -0.5405   0.03991   0.02951  -0.0066   1.0000   0.1486
  -3.750  -0.5215   0.03841   0.02776  -0.0056   1.0000   0.1474
  -3.500  -0.5023   0.03721   0.02630  -0.0046   1.0000   0.1475
  -3.250  -0.4830   0.03626   0.02509  -0.0037   1.0000   0.1488
  -3.000  -0.4634   0.03549   0.02407  -0.0028   1.0000   0.1503
  -2.750  -0.4434   0.03483   0.02321  -0.0021   1.0000   0.1514
  -2.500  -0.4225   0.03400   0.02241  -0.0016   1.0000   0.1530
  -2.250  -0.3794   0.03347   0.02193  -0.0049   0.9935   0.1572
  -2.000  -0.3285   0.03335   0.02171  -0.0096   0.9833   0.1664
  -1.750  -0.2823   0.03305   0.02149  -0.0136   0.9729   0.1771
  -1.500  -0.2440   0.03281   0.02129  -0.0163   0.9621   0.1921
  -1.250  -0.2071   0.03229   0.02118  -0.0189   0.9520   0.2355
  -1.000  -0.0493   0.03178   0.02356  -0.0377   0.9489   1.0000
  -0.750  -0.0216   0.03220   0.02365  -0.0396   0.9364   1.0000
  -0.500   0.0161   0.03281   0.02392  -0.0430   0.9258   1.0000
  -0.250   0.0324   0.03330   0.02419  -0.0425   0.9133   1.0000
   0.000   0.0555   0.03395   0.02461  -0.0431   0.9023   1.0000
   0.250   0.0871   0.03465   0.02510  -0.0450   0.8924   1.0000
   0.500   0.0992   0.03539   0.02567  -0.0436   0.8821   1.0000
   0.750   0.1344   0.03618   0.02628  -0.0459   0.8731   1.0000
   1.000   0.1416   0.03701   0.02698  -0.0437   0.8632   1.0000
   1.250   0.1742   0.03786   0.02770  -0.0455   0.8548   1.0000
   1.500   0.1825   0.03880   0.02853  -0.0435   0.8456   1.0000
   1.750   0.2118   0.03968   0.02931  -0.0446   0.8367   1.0000
   2.000   0.2241   0.04070   0.03024  -0.0433   0.8279   1.0000
   2.250   0.2510   0.04160   0.03107  -0.0440   0.8182   1.0000
   2.500   0.2656   0.04262   0.03202  -0.0429   0.8082   1.0000
   2.750   0.3051   0.04339   0.03275  -0.0451   0.7972   1.0000
   3.000   0.3104   0.04444   0.03376  -0.0426   0.7852   1.0000
   3.250   0.3435   0.04525   0.03454  -0.0438   0.7735   1.0000
   3.500   0.3681   0.04608   0.03536  -0.0438   0.7613   1.0000
   3.750   0.3803   0.04719   0.03645  -0.0423   0.7488   1.0000
   4.000   0.4151   0.04791   0.03718  -0.0434   0.7370   1.0000
   4.250   0.4384   0.04878   0.03807  -0.0432   0.7243   1.0000
   4.500   0.4490   0.05001   0.03931  -0.0415   0.7108   1.0000
   4.750   0.4733   0.05093   0.04028  -0.0413   0.6978   1.0000
   5.000   0.5216   0.05106   0.04050  -0.0434   0.6861   1.0000
   5.250   0.5263   0.05254   0.04200  -0.0412   0.6710   1.0000
   5.500   0.5366   0.05400   0.04351  -0.0397   0.6566   1.0000
   5.750   0.5544   0.05523   0.04480  -0.0388   0.6426   1.0000
   6.000   0.5885   0.05576   0.04542  -0.0391   0.6303   1.0000
   6.250   0.6099   0.05684   0.04659  -0.0385   0.6171   1.0000
   6.500   0.6103   0.05911   0.04891  -0.0367   0.6027   1.0000
   6.750   0.6195   0.06110   0.05095  -0.0356   0.5901   1.0000
   7.000   0.6615   0.06122   0.05124  -0.0361   0.5806   1.0000
   7.250   0.6427   0.06507   0.05508  -0.0340   0.5676   1.0000
   7.500   0.6558   0.06669   0.05678  -0.0329   0.5543   1.0000
   7.750   0.9599   0.03484   0.02571  -0.0333   0.4966   1.0000
   8.000   0.9904   0.03275   0.02363  -0.0305   0.4698   1.0000
   8.250   0.9947   0.03262   0.02360  -0.0259   0.4430   1.0000
   8.500   0.9943   0.03259   0.02359  -0.0208   0.4110   1.0000
   8.750   0.9866   0.03303   0.02397  -0.0151   0.3711   1.0000
   9.000   0.9787   0.03389   0.02459  -0.0099   0.3210   1.0000
   9.250   0.9686   0.03559   0.02576  -0.0054   0.2597   1.0000
   9.500   0.9560   0.03825   0.02796  -0.0020   0.2061   1.0000
   9.750   0.9461   0.04116   0.03051   0.0006   0.1710   1.0000
  10.000   0.9401   0.04397   0.03305   0.0026   0.1536   1.0000
  10.250   0.9386   0.04652   0.03545   0.0043   0.1430   1.0000
  10.500   0.9397   0.04891   0.03770   0.0059   0.1358   1.0000
  10.750   0.9461   0.05089   0.03964   0.0074   0.1293   1.0000
  11.000   0.9553   0.05265   0.04127   0.0089   0.1240   1.0000
  11.250   0.9715   0.05396   0.04264   0.0105   0.1188   1.0000
  11.500   0.9988   0.05458   0.04312   0.0121   0.1141   1.0000
  11.750   1.0476   0.05464   0.04327   0.0133   0.1108   1.0000
  12.000   1.0964   0.05567   0.04449   0.0134   0.1085   1.0000
  12.250   1.1343   0.05767   0.04669   0.0134   0.1066   1.0000
  12.500   1.1621   0.06018   0.04938   0.0135   0.1049   1.0000
  12.750   1.1858   0.06307   0.05245   0.0136   0.1035   1.0000
  13.000   1.1985   0.06632   0.05594   0.0144   0.1029   1.0000
  13.250   1.1922   0.06974   0.05969   0.0162   0.1032   1.0000
  13.500   1.1715   0.07366   0.06399   0.0181   0.1040   1.0000
  13.750   1.1379   0.07859   0.06931   0.0193   0.1049   1.0000
  14.000   1.0982   0.08480   0.07589   0.0190   0.1061   1.0000
  14.250   1.0499   0.09294   0.08434   0.0167   0.1077   1.0000
  14.500   0.9980   0.10332   0.09496   0.0122   0.1100   1.0000
  14.750   0.9598   0.11369   0.10545   0.0073   0.1121   1.0000
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