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AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AS5048 (18%) (as5048-il)
Reynolds number: 50,000
Max Cl/Cd: 23.64 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-as5048-il-50000-n5.txt
Download as CSV file: xf-as5048-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AS5048 (18%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6394   0.09275   0.08461  -0.0628   1.0000   0.0397
 -13.000  -0.6582   0.08764   0.07938  -0.0642   1.0000   0.0396
 -12.750  -0.6770   0.08295   0.07455  -0.0650   1.0000   0.0395
 -12.500  -0.6961   0.07864   0.07008  -0.0652   1.0000   0.0394
 -12.250  -0.7132   0.07480   0.06606  -0.0648   1.0000   0.0394
 -12.000  -0.7302   0.07130   0.06235  -0.0638   1.0000   0.0395
 -11.750  -0.7454   0.06817   0.05901  -0.0621   1.0000   0.0396
 -11.500  -0.7532   0.06533   0.05606  -0.0604   1.0000   0.0400
 -11.250  -0.7513   0.06284   0.05354  -0.0590   1.0000   0.0407
 -11.000  -0.7531   0.06052   0.05112  -0.0570   1.0000   0.0413
 -10.750  -0.7554   0.05832   0.04878  -0.0546   1.0000   0.0418
 -10.500  -0.7560   0.05621   0.04651  -0.0520   1.0000   0.0423
 -10.250  -0.7536   0.05415   0.04428  -0.0495   1.0000   0.0429
 -10.000  -0.7459   0.05211   0.04205  -0.0474   1.0000   0.0434
  -9.750  -0.7330   0.05019   0.03994  -0.0457   1.0000   0.0441
  -9.500  -0.7124   0.04838   0.03793  -0.0447   1.0000   0.0450
  -9.250  -0.6930   0.04701   0.03633  -0.0433   1.0000   0.0466
  -9.000  -0.6575   0.04568   0.03504  -0.0438   1.0000   0.0493
  -8.750  -0.6406   0.04511   0.03446  -0.0417   1.0000   0.0516
  -8.250  -0.5674   0.04357   0.03276  -0.0424   0.9916   0.0578
  -8.000  -0.5413   0.04236   0.03147  -0.0433   0.9799   0.0628
  -7.750  -0.5216   0.04103   0.03008  -0.0437   0.9673   0.0675
  -7.500  -0.5058   0.03962   0.02861  -0.0438   0.9557   0.0729
  -7.250  -0.4923   0.03806   0.02704  -0.0438   0.9456   0.0807
  -7.000  -0.4795   0.03625   0.02532  -0.0440   0.9375   0.0950
  -6.750  -0.4777   0.03429   0.02366  -0.0426   0.9273   0.1235
  -6.500  -0.4864   0.03167   0.02184  -0.0403   0.9178   0.2198
  -6.250  -0.4591   0.03376   0.02588  -0.0345   0.9140   0.5038
  -6.000  -0.4423   0.03547   0.02741  -0.0316   0.9080   0.5818
  -5.750  -0.4025   0.03976   0.03147  -0.0276   0.9040   0.6311
  -5.500  -0.3732   0.04011   0.03153  -0.0274   0.8990   0.6444
  -5.250  -0.3471   0.03989   0.03102  -0.0276   0.8943   0.6572
  -5.000  -0.3250   0.03946   0.03033  -0.0276   0.8900   0.6710
  -4.750  -0.2929   0.03974   0.03040  -0.0277   0.8856   0.6781
  -4.500  -0.2790   0.03935   0.02982  -0.0264   0.8799   0.6898
  -4.250  -0.2437   0.03924   0.02948  -0.0277   0.8766   0.6976
  -4.000  -0.2217   0.03882   0.02887  -0.0276   0.8726   0.7073
  -3.750  -0.2054   0.03879   0.02872  -0.0260   0.8669   0.7150
  -3.500  -0.1909   0.03843   0.02822  -0.0247   0.8618   0.7238
  -3.250  -0.1574   0.03824   0.02785  -0.0260   0.8586   0.7299
  -3.000  -0.1525   0.03787   0.02737  -0.0234   0.8530   0.7391
  -2.750  -0.1298   0.03789   0.02730  -0.0228   0.8481   0.7441
  -2.500  -0.1145   0.03759   0.02688  -0.0217   0.8433   0.7517
  -2.250  -0.0870   0.03728   0.02644  -0.0224   0.8399   0.7573
  -2.000  -0.0730   0.03734   0.02644  -0.0206   0.8344   0.7626
  -1.750  -0.0718   0.03713   0.02616  -0.0172   0.8280   0.7703
  -1.500  -0.0424   0.03697   0.02591  -0.0181   0.8242   0.7745
  -1.250  -0.0081   0.03680   0.02564  -0.0197   0.8213   0.7786
  -1.000  -0.0203   0.03695   0.02578  -0.0140   0.8126   0.7854
  -0.750  -0.0011   0.03677   0.02553  -0.0134   0.8078   0.7902
  -0.500   0.0342   0.03665   0.02534  -0.0152   0.8045   0.7934
  -0.250   0.0323   0.03690   0.02559  -0.0110   0.7964   0.7985
   0.000   0.0485   0.03678   0.02541  -0.0100   0.7908   0.8035
   0.250   0.0802   0.03659   0.02516  -0.0114   0.7871   0.8071
   0.500   0.0816   0.03696   0.02556  -0.0077   0.7782   0.8111
   0.750   0.1077   0.03694   0.02552  -0.0080   0.7728   0.8146
   1.250   0.1348   0.03712   0.02566  -0.0052   0.7583   0.8234
   1.500   0.1702   0.03707   0.02561  -0.0067   0.7537   0.8260
   1.750   0.1771   0.03743   0.02600  -0.0041   0.7444   0.8298
   2.000   0.2045   0.03742   0.02600  -0.0046   0.7381   0.8333
   2.250   0.2196   0.03761   0.02620  -0.0033   0.7300   0.8376
   2.500   0.2402   0.03772   0.02633  -0.0028   0.7219   0.8412
   2.750   0.2818   0.03752   0.02616  -0.0050   0.7177   0.8435
   3.000   0.2815   0.03809   0.02680  -0.0015   0.7052   0.8478
   3.250   0.3228   0.03783   0.02657  -0.0036   0.7008   0.8510
   3.500   0.3220   0.03838   0.02718  -0.0002   0.6877   0.8561
   3.750   0.3590   0.03819   0.02706  -0.0017   0.6819   0.8589
   4.000   0.3669   0.03862   0.02757   0.0008   0.6696   0.8629
   4.250   0.3787   0.03898   0.02800   0.0026   0.6580   0.8675
   4.500   0.4141   0.03864   0.02775   0.0015   0.6510   0.8714
   4.750   0.4221   0.03910   0.02830   0.0038   0.6375   0.8763
   5.250   0.4746   0.03870   0.02811   0.0044   0.6176   0.8847
   5.500   0.4871   0.03898   0.02849   0.0059   0.6033   0.8905
   5.750   0.5037   0.03914   0.02878   0.0072   0.5892   0.8959
   6.000   0.5233   0.03914   0.02890   0.0081   0.5756   0.9022
   6.500   0.5827   0.03785   0.02789   0.0087   0.5535   0.9143
   6.750   0.6031   0.03780   0.02799   0.0094   0.5386   0.9221
   7.000   0.6277   0.03762   0.02796   0.0096   0.5236   0.9299
   7.250   0.6547   0.03733   0.02781   0.0096   0.5085   0.9397
   7.500   0.6847   0.03690   0.02752   0.0093   0.4929   0.9521
   7.750   0.7168   0.03636   0.02708   0.0088   0.4763   0.9681
   8.000   0.7515   0.03574   0.02654   0.0080   0.4585   0.9855
   8.250   0.7788   0.03511   0.02592   0.0083   0.4399   1.0000
   8.500   0.8030   0.03493   0.02569   0.0087   0.4205   1.0000
   8.750   0.8217   0.03534   0.02606   0.0092   0.3999   1.0000
   9.000   0.8413   0.03580   0.02647   0.0096   0.3793   1.0000
   9.250   0.8604   0.03640   0.02699   0.0101   0.3598   1.0000
   9.500   0.8781   0.03716   0.02767   0.0106   0.3412   1.0000
   9.750   0.8942   0.03809   0.02854   0.0111   0.3236   1.0000
  10.000   0.9086   0.03918   0.02958   0.0117   0.3071   1.0000
  10.250   0.9219   0.04039   0.03078   0.0122   0.2916   1.0000
  10.500   0.9348   0.04168   0.03207   0.0128   0.2773   1.0000
  10.750   0.9474   0.04300   0.03341   0.0134   0.2639   1.0000
  11.000   0.9613   0.04425   0.03464   0.0139   0.2518   1.0000
  11.250   0.9758   0.04543   0.03577   0.0144   0.2400   1.0000
  11.500   0.9837   0.04721   0.03768   0.0150   0.2285   1.0000
  11.750   0.9944   0.04877   0.03929   0.0155   0.2180   1.0000
  12.000   1.0087   0.04997   0.04043   0.0161   0.2079   1.0000
  12.250   1.0124   0.05219   0.04285   0.0166   0.1983   1.0000
  12.500   1.0232   0.05376   0.04440   0.0171   0.1893   1.0000
  12.750   1.0278   0.05589   0.04667   0.0176   0.1806   1.0000
  13.000   1.0356   0.05783   0.04867   0.0181   0.1728   1.0000
  13.250   1.0387   0.06016   0.05114   0.0185   0.1651   1.0000
  13.500   1.0451   0.06225   0.05329   0.0188   0.1583   1.0000
  13.750   1.0427   0.06529   0.05653   0.0190   0.1520   1.0000
  14.000   1.0550   0.06672   0.05788   0.0194   0.1456   1.0000
  14.250   1.0411   0.07112   0.06261   0.0191   0.1407   1.0000
  14.500   1.0387   0.07427   0.06589   0.0190   0.1356   1.0000
  14.750   1.0462   0.07633   0.06794   0.0191   0.1306   1.0000
  15.000   1.0220   0.08246   0.07441   0.0178   0.1274   1.0000
  15.250   1.0003   0.08865   0.08084   0.0160   0.1241   1.0000
  15.500   1.0007   0.09177   0.08401   0.0153   0.1200   1.0000
  15.750   0.9949   0.09602   0.08835   0.0141   0.1168   1.0000
  16.000   0.9314   0.11067   0.10330   0.0071   0.1159   1.0000
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