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AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AS5046 (16%) (as5046-il)
Reynolds number: 100,000
Max Cl/Cd: 42.24 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-as5046-il-100000.txt
Download as CSV file: xf-as5046-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4014   0.11307   0.10867  -0.0361   1.0000   0.1718
 -11.250  -0.4880   0.11685   0.11201  -0.0226   1.0000   0.1615
 -11.000  -0.5291   0.11061   0.10594  -0.0295   1.0000   0.1726
 -10.750  -0.4837   0.10959   0.10486  -0.0242   1.0000   0.1784
 -10.500  -0.5043   0.10441   0.09978  -0.0277   1.0000   0.1898
  -8.500  -0.7734   0.04857   0.04123  -0.0347   0.9897   0.0608
  -8.250  -0.7442   0.04366   0.03620  -0.0365   0.9854   0.0577
  -8.000  -0.7177   0.04034   0.03243  -0.0375   0.9791   0.0558
  -7.750  -0.6857   0.03760   0.02930  -0.0391   0.9742   0.0557
  -7.500  -0.6557   0.03529   0.02668  -0.0399   0.9686   0.0556
  -7.250  -0.6213   0.03309   0.02419  -0.0410   0.9644   0.0550
  -7.000  -0.5832   0.03115   0.02209  -0.0425   0.9616   0.0552
  -6.750  -0.5510   0.02968   0.02056  -0.0430   0.9574   0.0563
  -6.500  -0.5177   0.02836   0.01924  -0.0437   0.9534   0.0582
  -6.250  -0.4826   0.02711   0.01798  -0.0450   0.9500   0.0621
  -6.000  -0.4515   0.02571   0.01675  -0.0464   0.9467   0.0683
  -5.750  -0.4331   0.02480   0.01581  -0.0455   0.9405   0.0735
  -5.500  -0.4081   0.02355   0.01459  -0.0462   0.9362   0.0864
  -5.250  -0.3917   0.02071   0.01286  -0.0470   0.9321   0.2230
  -5.000  -0.3924   0.02210   0.01625  -0.0390   0.9247   0.6091
  -4.750  -0.3628   0.02560   0.01964  -0.0343   0.9211   0.6536
  -4.500  -0.3238   0.03023   0.02425  -0.0272   0.9196   0.6874
  -4.250  -0.2720   0.03253   0.02641  -0.0253   0.9187   0.7068
  -4.000  -0.2519   0.03238   0.02609  -0.0246   0.9138   0.7203
  -3.750  -0.2184   0.03263   0.02621  -0.0243   0.9100   0.7286
  -3.500  -0.1915   0.03242   0.02586  -0.0245   0.9058   0.7397
  -3.250  -0.1660   0.03202   0.02531  -0.0252   0.9018   0.7523
  -3.000  -0.1214   0.03197   0.02513  -0.0270   0.8994   0.7588
  -2.750  -0.1273   0.03184   0.02497  -0.0228   0.8916   0.7698
  -2.500  -0.0868   0.03168   0.02469  -0.0246   0.8883   0.7766
  -2.250  -0.0646   0.03125   0.02416  -0.0250   0.8842   0.7859
  -2.000  -0.0467   0.03131   0.02417  -0.0234   0.8784   0.7920
  -1.750  -0.0484   0.03111   0.02392  -0.0203   0.8714   0.8011
  -1.500  -0.0013   0.03081   0.02353  -0.0232   0.8684   0.8055
  -1.250   0.0073   0.03085   0.02354  -0.0209   0.8620   0.8119
  -1.000   0.0099   0.03072   0.02337  -0.0181   0.8546   0.8184
  -0.750   0.0541   0.03044   0.02302  -0.0209   0.8509   0.8224
  -0.500   0.0551   0.03060   0.02317  -0.0175   0.8428   0.8280
  -0.250   0.0693   0.03041   0.02294  -0.0167   0.8358   0.8335
   0.000   0.1167   0.03009   0.02256  -0.0196   0.8323   0.8367
   0.250   0.1128   0.03041   0.02290  -0.0154   0.8218   0.8413
   0.500   0.1502   0.03012   0.02257  -0.0173   0.8166   0.8453
   0.750   0.1486   0.03037   0.02282  -0.0143   0.8059   0.8499
   1.000   0.1886   0.03006   0.02249  -0.0160   0.8004   0.8526
   1.250   0.1989   0.03031   0.02276  -0.0139   0.7900   0.8561
   1.500   0.2363   0.03002   0.02246  -0.0155   0.7838   0.8589
   1.750   0.2471   0.03028   0.02274  -0.0138   0.7728   0.8628
   2.000   0.2857   0.02994   0.02238  -0.0156   0.7667   0.8655
   2.250   0.2995   0.03016   0.02264  -0.0141   0.7549   0.8681
   2.500   0.3409   0.02968   0.02216  -0.0155   0.7494   0.8706
   2.750   0.3557   0.02988   0.02241  -0.0140   0.7365   0.8739
   3.000   0.3809   0.02979   0.02236  -0.0138   0.7259   0.8766
   3.250   0.4178   0.02922   0.02180  -0.0146   0.7176   0.8791
   3.500   0.4404   0.02914   0.02176  -0.0142   0.7046   0.8824
   3.750   0.4829   0.02817   0.02080  -0.0149   0.6989   0.8846
   4.000   0.5028   0.02801   0.02072  -0.0137   0.6848   0.8873
   4.250   0.5265   0.02775   0.02053  -0.0130   0.6718   0.8900
   4.500   0.5674   0.02673   0.01952  -0.0138   0.6655   0.8928
   4.750   0.5906   0.02637   0.01925  -0.0132   0.6512   0.8964
   5.000   0.6166   0.02588   0.01884  -0.0127   0.6376   0.8995
   5.250   0.6445   0.02518   0.01823  -0.0121   0.6246   0.9022
   5.500   0.6755   0.02428   0.01741  -0.0119   0.6119   0.9052
   5.750   0.7061   0.02333   0.01652  -0.0116   0.5979   0.9089
   6.000   0.7341   0.02251   0.01579  -0.0111   0.5803   0.9130
   6.250   0.7627   0.02167   0.01499  -0.0106   0.5603   0.9165
   6.500   0.7928   0.02080   0.01409  -0.0101   0.5372   0.9200
   6.750   0.8192   0.02032   0.01354  -0.0094   0.5073   0.9241
   7.000   0.8428   0.02022   0.01328  -0.0085   0.4731   0.9289
   7.250   0.8632   0.02045   0.01333  -0.0073   0.4375   0.9341
   7.500   0.8829   0.02090   0.01360  -0.0061   0.4042   0.9400
   7.750   0.9029   0.02150   0.01401  -0.0053   0.3747   0.9462
   8.000   0.9234   0.02216   0.01456  -0.0047   0.3474   0.9526
   8.250   0.9449   0.02291   0.01521  -0.0045   0.3238   0.9604
   8.500   0.9682   0.02368   0.01593  -0.0047   0.3014   0.9694
   8.750   0.9943   0.02453   0.01669  -0.0055   0.2811   0.9802
   9.000   1.0206   0.02542   0.01751  -0.0066   0.2621   0.9969
   9.250   1.0401   0.02631   0.01838  -0.0066   0.2458   1.0000
   9.500   1.0620   0.02733   0.01938  -0.0071   0.2299   1.0000
   9.750   1.0845   0.02845   0.02046  -0.0077   0.2146   1.0000
  10.000   1.1083   0.02967   0.02161  -0.0085   0.1999   1.0000
  10.250   1.1280   0.03085   0.02287  -0.0088   0.1864   1.0000
  10.500   1.1473   0.03219   0.02429  -0.0091   0.1738   1.0000
  10.750   1.1661   0.03362   0.02579  -0.0091   0.1624   1.0000
  11.000   1.1876   0.03511   0.02721  -0.0095   0.1520   1.0000
  11.250   1.2034   0.03645   0.02860  -0.0091   0.1428   1.0000
  11.500   1.2180   0.03817   0.03045  -0.0086   0.1346   1.0000
  11.750   1.2421   0.03966   0.03177  -0.0092   0.1265   1.0000
  12.000   1.2473   0.04155   0.03399  -0.0076   0.1208   1.0000
  12.250   1.2619   0.04305   0.03549  -0.0070   0.1149   1.0000
  12.500   1.2754   0.04523   0.03778  -0.0065   0.1098   1.0000
  12.750   1.2768   0.04731   0.04012  -0.0049   0.1056   1.0000
  13.000   1.2948   0.04890   0.04163  -0.0047   0.1009   1.0000
  13.250   1.2984   0.05169   0.04463  -0.0036   0.0978   1.0000
  13.500   1.2900   0.05456   0.04784  -0.0020   0.0953   1.0000
  13.750   1.2861   0.05732   0.05083  -0.0010   0.0927   1.0000
  14.000   1.2898   0.05963   0.05322  -0.0005   0.0899   1.0000
  14.250   1.3028   0.06258   0.05615  -0.0002   0.0869   1.0000
  14.500   1.2802   0.06674   0.06066   0.0006   0.0862   1.0000
  14.750   1.2553   0.07154   0.06580   0.0008   0.0856   1.0000
  15.000   1.2270   0.07707   0.07164   0.0002   0.0853   1.0000
  15.250   1.1949   0.08350   0.07835  -0.0012   0.0852   1.0000
  15.500   1.1579   0.09113   0.08624  -0.0038   0.0855   1.0000
  15.750   1.1165   0.10029   0.09563  -0.0079   0.0861   1.0000
  16.000   1.0716   0.11139   0.10690  -0.0138   0.0869   1.0000
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