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AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AS5045 (15%) (as5045-il)
Reynolds number: 100,000
Max Cl/Cd: 44.05 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-as5045-il-100000.txt
Download as CSV file: xf-as5045-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AS5045 (15%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5132   0.10171   0.09732  -0.0182   1.0000   0.1855
  -9.750  -0.5301   0.09682   0.09255  -0.0219   1.0000   0.1984
  -8.250  -0.7140   0.04930   0.04273  -0.0445   0.9850   0.0784
  -8.000  -0.6872   0.04348   0.03634  -0.0454   0.9787   0.0646
  -7.750  -0.6589   0.03913   0.03114  -0.0465   0.9730   0.0571
  -7.500  -0.6259   0.03698   0.02864  -0.0477   0.9677   0.0549
  -7.250  -0.5931   0.03403   0.02548  -0.0490   0.9631   0.0537
  -7.000  -0.5559   0.03161   0.02282  -0.0507   0.9598   0.0530
  -6.750  -0.5214   0.02987   0.02088  -0.0518   0.9558   0.0540
  -6.500  -0.4898   0.02874   0.01953  -0.0525   0.9511   0.0558
  -6.250  -0.4567   0.02668   0.01766  -0.0531   0.9482   0.0580
  -6.000  -0.4235   0.02534   0.01642  -0.0539   0.9450   0.0605
  -5.750  -0.3978   0.02436   0.01545  -0.0539   0.9401   0.0638
  -5.500  -0.3739   0.02336   0.01442  -0.0539   0.9349   0.0683
  -5.250  -0.3471   0.02222   0.01328  -0.0549   0.9309   0.0805
  -5.000  -0.3300   0.01992   0.01185  -0.0553   0.9265   0.1822
  -4.750  -0.3261   0.02181   0.01591  -0.0474   0.9205   0.6210
  -4.500  -0.3019   0.02577   0.01983  -0.0400   0.9170   0.6614
  -4.250  -0.2710   0.03013   0.02419  -0.0306   0.9153   0.6980
  -4.000  -0.2387   0.03050   0.02436  -0.0301   0.9127   0.7130
  -3.750  -0.2150   0.03074   0.02447  -0.0283   0.9083   0.7218
  -3.500  -0.1928   0.03066   0.02425  -0.0273   0.9039   0.7329
  -3.250  -0.1699   0.03042   0.02387  -0.0272   0.8998   0.7452
  -3.000  -0.1356   0.03033   0.02364  -0.0277   0.8970   0.7541
  -2.750  -0.1214   0.03023   0.02347  -0.0260   0.8918   0.7637
  -2.500  -0.1094   0.03005   0.02319  -0.0249   0.8863   0.7750
  -2.250  -0.0743   0.02985   0.02290  -0.0254   0.8830   0.7809
  -2.000  -0.0596   0.02967   0.02262  -0.0250   0.8783   0.7905
  -1.750  -0.0408   0.02962   0.02253  -0.0233   0.8728   0.7960
  -1.500  -0.0198   0.02946   0.02229  -0.0231   0.8678   0.8033
  -1.250   0.0105   0.02919   0.02194  -0.0240   0.8641   0.8092
  -1.000   0.0184   0.02931   0.02205  -0.0216   0.8572   0.8152
  -0.750   0.0363   0.02920   0.02187  -0.0215   0.8513   0.8216
  -0.500   0.0719   0.02897   0.02158  -0.0227   0.8475   0.8256
  -0.250   0.0769   0.02917   0.02179  -0.0201   0.8391   0.8307
   0.000   0.1043   0.02905   0.02162  -0.0209   0.8335   0.8355
   0.250   0.1198   0.02915   0.02170  -0.0199   0.8262   0.8399
   0.500   0.1441   0.02912   0.02166  -0.0197   0.8193   0.8437
   0.750   0.1744   0.02906   0.02158  -0.0204   0.8136   0.8477
   1.000   0.1891   0.02926   0.02178  -0.0197   0.8039   0.8518
   1.250   0.2263   0.02904   0.02153  -0.0211   0.7989   0.8548
   1.500   0.2378   0.02930   0.02184  -0.0194   0.7877   0.8582
   1.750   0.2671   0.02927   0.02181  -0.0197   0.7804   0.8611
   2.000   0.2906   0.02934   0.02190  -0.0197   0.7706   0.8645
   2.250   0.3143   0.02951   0.02210  -0.0199   0.7604   0.8676
   2.500   0.3486   0.02925   0.02185  -0.0206   0.7530   0.8699
   2.750   0.3674   0.02940   0.02206  -0.0196   0.7411   0.8728
   3.000   0.4042   0.02892   0.02158  -0.0198   0.7354   0.8755
   3.250   0.4254   0.02902   0.02175  -0.0193   0.7222   0.8783
   3.500   0.4503   0.02902   0.02181  -0.0192   0.7099   0.8811
   3.750   0.4887   0.02832   0.02111  -0.0197   0.7037   0.8838
   4.000   0.5113   0.02818   0.02107  -0.0189   0.6901   0.8867
   4.250   0.5357   0.02794   0.02091  -0.0182   0.6771   0.8894
   4.500   0.5646   0.02744   0.02048  -0.0178   0.6659   0.8920
   4.750   0.5989   0.02653   0.01962  -0.0176   0.6571   0.8949
   5.000   0.6266   0.02601   0.01920  -0.0173   0.6432   0.8983
   5.250   0.6546   0.02531   0.01860  -0.0168   0.6294   0.9014
   5.500   0.6827   0.02443   0.01783  -0.0160   0.6155   0.9042
   5.750   0.7127   0.02343   0.01692  -0.0155   0.6006   0.9074
   6.000   0.7436   0.02233   0.01590  -0.0150   0.5840   0.9111
   6.250   0.7763   0.02116   0.01479  -0.0148   0.5650   0.9150
   6.500   0.8022   0.02039   0.01407  -0.0138   0.5376   0.9188
   6.750   0.8296   0.01974   0.01335  -0.0130   0.5050   0.9226
   7.000   0.8543   0.01962   0.01306  -0.0122   0.4650   0.9268
   7.250   0.8765   0.01990   0.01306  -0.0113   0.4244   0.9316
   7.500   0.8946   0.02043   0.01343  -0.0100   0.3841   0.9373
   7.750   0.9132   0.02115   0.01394  -0.0091   0.3478   0.9436
   8.000   0.9314   0.02194   0.01454  -0.0082   0.3149   0.9501
   8.250   0.9501   0.02281   0.01529  -0.0077   0.2847   0.9579
   8.500   0.9701   0.02375   0.01614  -0.0075   0.2571   0.9672
   8.750   0.9925   0.02484   0.01710  -0.0080   0.2328   0.9809
   9.000   1.0141   0.02593   0.01816  -0.0084   0.2108   1.0000
   9.250   1.0368   0.02722   0.01933  -0.0091   0.1921   1.0000
   9.500   1.0609   0.02864   0.02061  -0.0100   0.1752   1.0000
   9.750   1.0855   0.03011   0.02203  -0.0110   0.1603   1.0000
  10.000   1.1081   0.03151   0.02349  -0.0117   0.1474   1.0000
  10.250   1.1316   0.03310   0.02520  -0.0124   0.1362   1.0000
  10.500   1.1565   0.03486   0.02698  -0.0133   0.1266   1.0000
  10.750   1.1849   0.03658   0.02858  -0.0146   0.1181   1.0000
  11.000   1.2034   0.03850   0.03083  -0.0147   0.1114   1.0000
  11.250   1.2311   0.04035   0.03254  -0.0158   0.1048   1.0000
  11.500   1.2468   0.04274   0.03528  -0.0156   0.1002   1.0000
  11.750   1.2607   0.04474   0.03750  -0.0152   0.0956   1.0000
  12.000   1.2895   0.04750   0.04012  -0.0165   0.0907   1.0000
  12.250   1.2874   0.04995   0.04304  -0.0144   0.0887   1.0000
  12.500   1.2840   0.05266   0.04610  -0.0126   0.0865   1.0000
  12.750   1.2834   0.05532   0.04900  -0.0113   0.0841   1.0000
  13.000   1.2895   0.05766   0.05142  -0.0106   0.0814   1.0000
  13.250   1.3052   0.06156   0.05529  -0.0109   0.0786   1.0000
  13.500   1.2848   0.06513   0.05921  -0.0093   0.0782   1.0000
  13.750   1.2621   0.06937   0.06379  -0.0086   0.0779   1.0000
  14.000   1.2369   0.07429   0.06900  -0.0087   0.0777   1.0000
  14.250   1.2092   0.07989   0.07488  -0.0096   0.0776   1.0000
  14.500   1.1794   0.08625   0.08149  -0.0113   0.0778   1.0000
  14.750   1.1476   0.09348   0.08893  -0.0139   0.0780   1.0000
  15.000   1.1147   0.10167   0.09729  -0.0175   0.0784   1.0000
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