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AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AS5046 (16%) (as5046-il)
Reynolds number: 50,000
Max Cl/Cd: 28.05 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-as5046-il-50000-n5.txt
Download as CSV file: xf-as5046-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5615   0.10823   0.10086  -0.0358   1.0000   0.0414
 -12.250  -0.5782   0.10039   0.09299  -0.0405   1.0000   0.0408
 -12.000  -0.6006   0.09273   0.08526  -0.0451   1.0000   0.0402
 -11.750  -0.6250   0.08593   0.07835  -0.0488   1.0000   0.0396
 -11.500  -0.6488   0.08010   0.07239  -0.0514   1.0000   0.0392
 -11.250  -0.6702   0.07512   0.06724  -0.0528   1.0000   0.0388
 -11.000  -0.6884   0.07085   0.06278  -0.0533   1.0000   0.0386
 -10.750  -0.7043   0.06712   0.05885  -0.0530   1.0000   0.0384
 -10.500  -0.7175   0.06387   0.05540  -0.0519   1.0000   0.0382
 -10.250  -0.7275   0.06095   0.05228  -0.0501   1.0000   0.0381
 -10.000  -0.7312   0.05806   0.04914  -0.0485   1.0000   0.0381
  -9.750  -0.7303   0.05531   0.04614  -0.0469   1.0000   0.0382
  -9.500  -0.7255   0.05271   0.04331  -0.0453   1.0000   0.0384
  -9.250  -0.7174   0.05029   0.04066  -0.0437   1.0000   0.0387
  -9.000  -0.7070   0.04811   0.03829  -0.0421   1.0000   0.0393
  -8.750  -0.6958   0.04621   0.03619  -0.0404   1.0000   0.0404
  -8.500  -0.6848   0.04455   0.03432  -0.0385   1.0000   0.0416
  -8.250  -0.6759   0.04324   0.03277  -0.0360   1.0000   0.0428
  -8.000  -0.6665   0.04208   0.03158  -0.0334   1.0000   0.0440
  -7.750  -0.6322   0.04051   0.03000  -0.0341   0.9950   0.0460
  -7.500  -0.5907   0.03929   0.02866  -0.0348   0.9901   0.0483
  -7.250  -0.5536   0.03834   0.02750  -0.0353   0.9829   0.0519
  -7.000  -0.5262   0.03711   0.02632  -0.0358   0.9724   0.0564
  -6.750  -0.5005   0.03596   0.02498  -0.0363   0.9614   0.0611
  -6.500  -0.4804   0.03447   0.02351  -0.0369   0.9506   0.0671
  -6.250  -0.4605   0.03297   0.02198  -0.0376   0.9416   0.0764
  -6.000  -0.4414   0.03122   0.02033  -0.0384   0.9339   0.0936
  -5.750  -0.4354   0.02883   0.01861  -0.0380   0.9243   0.1562
  -5.500  -0.4247   0.02909   0.02139  -0.0316   0.9188   0.5027
  -5.250  -0.4058   0.03125   0.02332  -0.0283   0.9110   0.5975
  -5.000  -0.3764   0.03484   0.02671  -0.0231   0.9062   0.6532
  -4.750  -0.3410   0.03530   0.02683  -0.0232   0.9025   0.6665
  -4.500  -0.3106   0.03532   0.02656  -0.0232   0.8977   0.6765
  -4.250  -0.2906   0.03505   0.02606  -0.0226   0.8914   0.6886
  -4.000  -0.2606   0.03492   0.02569  -0.0230   0.8870   0.6980
  -3.500  -0.2174   0.03440   0.02477  -0.0222   0.8763   0.7175
  -3.250  -0.1889   0.03425   0.02445  -0.0224   0.8718   0.7241
  -3.000  -0.1635   0.03391   0.02392  -0.0228   0.8674   0.7328
  -2.750  -0.1432   0.03377   0.02365  -0.0220   0.8620   0.7394
  -2.500  -0.1221   0.03360   0.02336  -0.0214   0.8564   0.7462
  -2.250  -0.0993   0.03329   0.02290  -0.0215   0.8516   0.7534
  -2.000  -0.0730   0.03317   0.02267  -0.0216   0.8472   0.7585
  -1.750  -0.0594   0.03304   0.02246  -0.0202   0.8405   0.7655
  -1.500  -0.0341   0.03287   0.02218  -0.0204   0.8357   0.7707
  -1.250  -0.0041   0.03273   0.02194  -0.0212   0.8316   0.7753
  -1.000   0.0063   0.03273   0.02190  -0.0194   0.8242   0.7816
  -0.750   0.0307   0.03260   0.02169  -0.0195   0.8189   0.7863
  -0.500   0.0604   0.03251   0.02154  -0.0201   0.8145   0.7902
  -0.250   0.0727   0.03261   0.02162  -0.0184   0.8067   0.7951
   0.000   0.0974   0.03249   0.02143  -0.0189   0.8011   0.8001
   0.250   0.1193   0.03255   0.02147  -0.0184   0.7947   0.8036
   0.500   0.1403   0.03262   0.02154  -0.0178   0.7875   0.8072
   0.750   0.1716   0.03253   0.02140  -0.0187   0.7824   0.8109
   1.000   0.1837   0.03274   0.02162  -0.0173   0.7730   0.8156
   1.250   0.2136   0.03268   0.02155  -0.0180   0.7671   0.8188
   1.500   0.2301   0.03289   0.02180  -0.0167   0.7580   0.8222
   1.750   0.2590   0.03287   0.02178  -0.0171   0.7511   0.8256
   2.000   0.2766   0.03308   0.02203  -0.0162   0.7415   0.8297
   2.250   0.3066   0.03302   0.02198  -0.0169   0.7342   0.8331
   2.500   0.3238   0.03326   0.02229  -0.0158   0.7237   0.8364
   3.000   0.3719   0.03341   0.02255  -0.0150   0.7050   0.8434
   3.250   0.4028   0.03328   0.02247  -0.0155   0.6972   0.8468
   3.500   0.4238   0.03342   0.02269  -0.0150   0.6855   0.8504
   3.750   0.4429   0.03356   0.02293  -0.0139   0.6734   0.8539
   4.000   0.4778   0.03310   0.02256  -0.0142   0.6656   0.8572
   4.500   0.5158   0.03324   0.02290  -0.0123   0.6370   0.8654
   4.750   0.5367   0.03312   0.02290  -0.0113   0.6228   0.8691
   5.000   0.5586   0.03291   0.02283  -0.0102   0.6083   0.8733
   5.250   0.5816   0.03265   0.02269  -0.0093   0.5936   0.8780
   5.500   0.6054   0.03235   0.02251  -0.0086   0.5782   0.8827
   5.750   0.6281   0.03198   0.02230  -0.0075   0.5625   0.8871
   6.000   0.6519   0.03161   0.02206  -0.0066   0.5459   0.8919
   6.250   0.6770   0.03119   0.02176  -0.0058   0.5283   0.8974
   6.500   0.7034   0.03065   0.02135  -0.0049   0.5101   0.9030
   6.750   0.7332   0.02999   0.02075  -0.0042   0.4909   0.9091
   7.000   0.7565   0.02986   0.02070  -0.0034   0.4673   0.9162
   7.250   0.7845   0.02953   0.02034  -0.0027   0.4438   0.9232
   7.500   0.8074   0.02968   0.02047  -0.0020   0.4182   0.9317
   7.750   0.8320   0.02988   0.02060  -0.0016   0.3936   0.9416
   8.000   0.8522   0.03050   0.02122  -0.0012   0.3685   0.9564
   8.250   0.8736   0.03114   0.02179  -0.0012   0.3458   0.9809
   8.500   0.8896   0.03191   0.02251  -0.0006   0.3256   1.0000
   8.750   0.9066   0.03293   0.02353  -0.0004   0.3061   1.0000
   9.000   0.9241   0.03402   0.02460  -0.0004   0.2881   1.0000
   9.250   0.9417   0.03518   0.02574  -0.0004   0.2714   1.0000
   9.500   0.9589   0.03639   0.02697  -0.0004   0.2560   1.0000
   9.750   0.9760   0.03765   0.02824  -0.0004   0.2417   1.0000
  10.000   0.9924   0.03895   0.02953  -0.0003   0.2283   1.0000
  10.250   1.0092   0.04024   0.03078  -0.0002   0.2157   1.0000
  10.500   1.0219   0.04183   0.03249   0.0000   0.2032   1.0000
  10.750   1.0348   0.04345   0.03422   0.0002   0.1918   1.0000
  11.000   1.0486   0.04499   0.03577   0.0004   0.1815   1.0000
  11.250   1.0603   0.04666   0.03749   0.0007   0.1715   1.0000
  11.500   1.0698   0.04867   0.03966   0.0010   0.1623   1.0000
  11.750   1.0832   0.05021   0.04114   0.0013   0.1541   1.0000
  12.000   1.0872   0.05272   0.04393   0.0015   0.1463   1.0000
  12.250   1.0998   0.05437   0.04551   0.0019   0.1394   1.0000
  12.500   1.0994   0.05735   0.04881   0.0020   0.1329   1.0000
  12.750   1.1088   0.05928   0.05074   0.0023   0.1271   1.0000
  13.000   1.1076   0.06249   0.05418   0.0023   0.1221   1.0000
  13.250   1.1048   0.06581   0.05772   0.0022   0.1174   1.0000
  13.500   1.1158   0.06752   0.05938   0.0024   0.1127   1.0000
  13.750   1.1029   0.07222   0.06440   0.0017   0.1097   1.0000
  14.000   1.0867   0.07745   0.06992   0.0006   0.1069   1.0000
  14.250   1.0723   0.08259   0.07528  -0.0009   0.1043   1.0000
  14.500   1.0741   0.08554   0.07826  -0.0014   0.1010   1.0000
  14.750   1.0651   0.09022   0.08304  -0.0028   0.0987   1.0000
  15.000   1.0242   0.10032   0.09344  -0.0077   0.0982   1.0000
  15.250   0.9622   0.11629   0.10963  -0.0167   0.0983   1.0000
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