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AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AS5046 (16%) (as5046-il)
Reynolds number: 50,000
Max Cl/Cd: 28.23 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-as5046-il-50000.txt
Download as CSV file: xf-as5046-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AS5046 (16%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5143   0.10928   0.10245  -0.0297   1.0000   0.1520
 -10.750  -0.5732   0.09302   0.08631  -0.0427   1.0000   0.1291
 -10.500  -0.6028   0.08505   0.07831  -0.0473   1.0000   0.1224
 -10.250  -0.6323   0.07866   0.07189  -0.0498   1.0000   0.1186
 -10.000  -0.6751   0.07356   0.06672  -0.0505   1.0000   0.1162
  -9.750  -0.7252   0.06975   0.06259  -0.0487   1.0000   0.1133
  -9.500  -0.7260   0.06587   0.05856  -0.0475   1.0000   0.1094
  -9.250  -0.7287   0.06199   0.05454  -0.0460   1.0000   0.1065
  -9.000  -0.7379   0.05846   0.05074  -0.0436   1.0000   0.1033
  -8.750  -0.7533   0.05560   0.04737  -0.0400   1.0000   0.0997
  -8.500  -0.7648   0.05442   0.04574  -0.0355   1.0000   0.0977
  -8.250  -0.7652   0.05208   0.04331  -0.0323   1.0000   0.0968
  -8.000  -0.7640   0.04988   0.04092  -0.0292   1.0000   0.0959
  -7.750  -0.7595   0.04773   0.03852  -0.0266   1.0000   0.0955
  -7.500  -0.7515   0.04569   0.03618  -0.0242   1.0000   0.0956
  -7.250  -0.7403   0.04379   0.03395  -0.0221   1.0000   0.0964
  -7.000  -0.7261   0.04205   0.03186  -0.0203   1.0000   0.0974
  -6.750  -0.7070   0.04006   0.02971  -0.0188   1.0000   0.0987
  -6.500  -0.6833   0.03823   0.02787  -0.0175   1.0000   0.1007
  -6.250  -0.6578   0.03695   0.02662  -0.0159   1.0000   0.1038
  -6.000  -0.6340   0.03610   0.02570  -0.0140   1.0000   0.1096
  -5.750  -0.6132   0.03522   0.02496  -0.0117   1.0000   0.1174
  -5.500  -0.5987   0.03446   0.02412  -0.0090   1.0000   0.1259
  -5.250  -0.5899   0.03329   0.02313  -0.0064   1.0000   0.1374
  -5.000  -0.5820   0.03186   0.02189  -0.0043   1.0000   0.1575
  -4.750  -0.5773   0.02884   0.01986  -0.0033   1.0000   0.2291
  -4.500  -0.4125   0.04964   0.04216   0.0224   1.0000   0.8051
  -4.250  -0.3819   0.04882   0.04103   0.0213   1.0000   0.8273
  -4.000  -0.3652   0.04798   0.03999   0.0218   1.0000   0.8467
  -3.750  -0.3472   0.04716   0.03897   0.0219   1.0000   0.8645
  -3.500  -0.3242   0.04633   0.03793   0.0210   1.0000   0.8809
  -3.250  -0.2969   0.04551   0.03692   0.0193   1.0000   0.8960
  -3.000  -0.2693   0.04474   0.03596   0.0173   1.0000   0.9095
  -2.750  -0.2476   0.04406   0.03512   0.0162   1.0000   0.9212
  -2.500  -0.2406   0.04356   0.03451   0.0175   1.0000   0.9311
  -2.250  -0.2081   0.04297   0.03376   0.0143   1.0000   0.9412
  -2.000  -0.1901   0.04252   0.03320   0.0136   1.0000   0.9496
  -1.750  -0.1699   0.04216   0.03272   0.0124   1.0000   0.9575
  -1.500  -0.1486   0.04185   0.03231   0.0110   1.0000   0.9646
  -1.250  -0.1302   0.04164   0.03202   0.0100   1.0000   0.9713
  -1.000  -0.1075   0.04148   0.03177   0.0083   1.0000   0.9774
  -0.750  -0.0880   0.04143   0.03164   0.0070   1.0000   0.9834
  -0.500  -0.0415   0.04146   0.03159   0.0006   0.9949   0.9888
  -0.250   0.0079   0.04158   0.03162  -0.0063   0.9869   0.9941
   0.000   0.0585   0.04169   0.03169  -0.0135   0.9782   0.9988
   0.250   0.0926   0.04187   0.03183  -0.0174   0.9692   1.0000
   0.500   0.1245   0.04211   0.03204  -0.0207   0.9598   1.0000
   0.750   0.1498   0.04236   0.03229  -0.0228   0.9496   1.0000
   1.000   0.1717   0.04268   0.03261  -0.0241   0.9389   1.0000
   1.250   0.1987   0.04307   0.03301  -0.0263   0.9276   1.0000
   1.500   0.2335   0.04350   0.03346  -0.0297   0.9158   1.0000
   1.750   0.2533   0.04395   0.03394  -0.0303   0.9030   1.0000
   2.000   0.2701   0.04449   0.03451  -0.0304   0.8896   1.0000
   2.250   0.2916   0.04506   0.03513  -0.0312   0.8757   1.0000
   2.500   0.3169   0.04566   0.03578  -0.0324   0.8611   1.0000
   2.750   0.3437   0.04625   0.03642  -0.0337   0.8457   1.0000
   3.000   0.3689   0.04685   0.03709  -0.0345   0.8295   1.0000
   3.250   0.3906   0.04746   0.03777  -0.0347   0.8126   1.0000
   3.500   0.4077   0.04808   0.03846  -0.0339   0.7948   1.0000
   3.750   0.4225   0.04870   0.03914  -0.0328   0.7763   1.0000
   4.000   0.4387   0.04925   0.03976  -0.0316   0.7573   1.0000
   4.250   0.4605   0.04966   0.04026  -0.0310   0.7380   1.0000
   4.500   0.4918   0.04982   0.04052  -0.0313   0.7187   1.0000
   4.750   0.5402   0.04952   0.04035  -0.0335   0.6997   1.0000
   5.000   0.5533   0.04972   0.04065  -0.0311   0.6808   1.0000
   5.250   0.5418   0.05033   0.04129  -0.0259   0.6621   1.0000
   5.500   0.5388   0.05067   0.04168  -0.0217   0.6436   1.0000
   5.750   0.5420   0.05079   0.04187  -0.0182   0.6255   1.0000
   6.000   0.5524   0.05067   0.04182  -0.0154   0.6077   1.0000
   6.250   0.5809   0.04995   0.04123  -0.0143   0.5897   1.0000
   6.500   0.6236   0.04848   0.03991  -0.0140   0.5723   1.0000
   6.750   0.6820   0.04580   0.03745  -0.0144   0.5552   1.0000
   7.000   0.7400   0.04259   0.03442  -0.0143   0.5386   1.0000
   7.250   0.7417   0.04304   0.03494  -0.0113   0.5173   1.0000
   7.500   0.8053   0.03939   0.03144  -0.0115   0.4972   1.0000
   7.750   0.8798   0.03548   0.02754  -0.0129   0.4716   1.0000
   8.000   0.9216   0.03430   0.02625  -0.0130   0.4441   1.0000
   8.250   0.9435   0.03476   0.02668  -0.0120   0.4189   1.0000
   8.500   0.9818   0.03478   0.02648  -0.0127   0.3924   1.0000
   8.750   0.9978   0.03614   0.02791  -0.0119   0.3701   1.0000
   9.000   1.0260   0.03714   0.02882  -0.0122   0.3474   1.0000
   9.250   1.0529   0.03840   0.02999  -0.0125   0.3261   1.0000
   9.500   1.0703   0.04015   0.03184  -0.0121   0.3073   1.0000
   9.750   1.0885   0.04191   0.03366  -0.0117   0.2891   1.0000
  10.000   1.1067   0.04380   0.03562  -0.0114   0.2724   1.0000
  10.250   1.1233   0.04583   0.03773  -0.0109   0.2571   1.0000
  10.500   1.1399   0.04798   0.03993  -0.0104   0.2432   1.0000
  10.750   1.1599   0.05011   0.04205  -0.0102   0.2297   1.0000
  11.000   1.1555   0.05314   0.04543  -0.0082   0.2211   1.0000
  11.250   1.1613   0.05602   0.04845  -0.0071   0.2121   1.0000
  11.500   1.1435   0.05978   0.05253  -0.0046   0.2073   1.0000
  11.750   1.1603   0.06238   0.05513  -0.0042   0.1983   1.0000
  12.000   1.1240   0.06714   0.06018  -0.0015   0.1975   1.0000
  12.250   1.0816   0.07345   0.06672  -0.0008   0.1979   1.0000
  12.500   1.0341   0.08169   0.07510  -0.0023   0.1991   1.0000
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