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AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AS5045 (15%) (as5045-il)
Reynolds number: 50,000
Max Cl/Cd: 29.97 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-as5045-il-50000.txt
Download as CSV file: xf-as5045-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4600   0.11981   0.11326  -0.0016   1.0000   0.3107
 -10.000  -0.5796   0.08871   0.08237  -0.0349   1.0000   0.1401
  -9.750  -0.6195   0.07983   0.07348  -0.0416   1.0000   0.1309
  -9.500  -0.6578   0.07355   0.06715  -0.0447   1.0000   0.1257
  -9.250  -0.6941   0.06850   0.06174  -0.0462   1.0000   0.1192
  -9.000  -0.6931   0.06402   0.05717  -0.0462   1.0000   0.1156
  -8.750  -0.7053   0.05962   0.05240  -0.0457   1.0000   0.1108
  -8.500  -0.7190   0.05693   0.04904  -0.0436   1.0000   0.1061
  -8.250  -0.7165   0.05401   0.04607  -0.0414   1.0000   0.1047
  -8.000  -0.7200   0.05178   0.04369  -0.0382   1.0000   0.1033
  -7.750  -0.7207   0.04952   0.04120  -0.0353   1.0000   0.1017
  -7.500  -0.7167   0.04710   0.03844  -0.0328   1.0000   0.0996
  -7.250  -0.7083   0.04468   0.03561  -0.0307   1.0000   0.0976
  -7.000  -0.6957   0.04244   0.03293  -0.0288   1.0000   0.0960
  -6.750  -0.6796   0.04045   0.03056  -0.0272   1.0000   0.0953
  -6.500  -0.6606   0.03860   0.02850  -0.0256   1.0000   0.0955
  -6.250  -0.6398   0.03695   0.02674  -0.0240   1.0000   0.0966
  -6.000  -0.6186   0.03564   0.02539  -0.0223   1.0000   0.0999
  -5.750  -0.5969   0.03468   0.02432  -0.0203   1.0000   0.1047
  -5.500  -0.5757   0.03376   0.02349  -0.0177   1.0000   0.1104
  -5.250  -0.5592   0.03294   0.02269  -0.0152   1.0000   0.1171
  -5.000  -0.5461   0.03191   0.02172  -0.0129   1.0000   0.1259
  -4.750  -0.5336   0.03057   0.02052  -0.0114   1.0000   0.1432
  -4.250  -0.5307   0.03022   0.02345   0.0014   1.0000   0.6339
  -4.000  -0.4096   0.04476   0.03733   0.0255   1.0000   0.8291
  -3.750  -0.3863   0.04386   0.03615   0.0251   1.0000   0.8494
  -3.500  -0.3690   0.04297   0.03504   0.0254   1.0000   0.8674
  -3.250  -0.3479   0.04212   0.03395   0.0249   1.0000   0.8840
  -3.000  -0.3207   0.04129   0.03290   0.0233   1.0000   0.8994
  -2.750  -0.2892   0.04051   0.03189   0.0208   1.0000   0.9133
  -2.500  -0.2590   0.03979   0.03097   0.0182   1.0000   0.9255
  -2.250  -0.2358   0.03917   0.03019   0.0168   1.0000   0.9359
  -2.000  -0.2253   0.03869   0.02960   0.0175   1.0000   0.9452
  -1.750  -0.1906   0.03821   0.02894   0.0138   1.0000   0.9542
  -1.500  -0.1703   0.03784   0.02846   0.0127   1.0000   0.9619
  -1.250  -0.1460   0.03757   0.02808   0.0107   1.0000   0.9695
  -1.000  -0.1211   0.03736   0.02778   0.0086   1.0000   0.9762
  -0.750  -0.0989   0.03726   0.02758   0.0070   1.0000   0.9826
  -0.500  -0.0719   0.03723   0.02748   0.0044   1.0000   0.9886
  -0.250  -0.0267   0.03739   0.02755  -0.0017   0.9945   0.9941
   0.000   0.0257   0.03758   0.02767  -0.0092   0.9865   0.9991
   0.250   0.0572   0.03779   0.02783  -0.0126   0.9783   1.0000
   0.500   0.0874   0.03808   0.02808  -0.0157   0.9698   1.0000
   0.750   0.1128   0.03836   0.02836  -0.0178   0.9606   1.0000
   1.000   0.1345   0.03870   0.02870  -0.0192   0.9510   1.0000
   1.250   0.1628   0.03916   0.02915  -0.0217   0.9409   1.0000
   1.500   0.1920   0.03965   0.02966  -0.0242   0.9297   1.0000
   1.750   0.2069   0.04013   0.03016  -0.0242   0.9181   1.0000
   2.000   0.2283   0.04071   0.03077  -0.0252   0.9059   1.0000
   2.250   0.2552   0.04136   0.03146  -0.0269   0.8928   1.0000
   2.500   0.2858   0.04205   0.03220  -0.0291   0.8787   1.0000
   2.750   0.3120   0.04273   0.03294  -0.0305   0.8640   1.0000
   3.000   0.3281   0.04342   0.03369  -0.0301   0.8485   1.0000
   3.250   0.3502   0.04413   0.03448  -0.0304   0.8321   1.0000
   3.500   0.3787   0.04487   0.03529  -0.0315   0.8150   1.0000
   3.750   0.3869   0.04558   0.03606  -0.0296   0.7974   1.0000
   4.000   0.3926   0.04629   0.03684  -0.0272   0.7792   1.0000
   4.250   0.4016   0.04696   0.03758  -0.0252   0.7604   1.0000
   4.500   0.4186   0.04757   0.03827  -0.0241   0.7411   1.0000
   4.750   0.4531   0.04798   0.03880  -0.0249   0.7215   1.0000
   5.000   0.4751   0.04840   0.03932  -0.0240   0.7021   1.0000
   5.250   0.4741   0.04907   0.04006  -0.0208   0.6817   1.0000
   5.500   0.5016   0.04933   0.04044  -0.0207   0.6610   1.0000
   5.750   0.5497   0.04884   0.04014  -0.0219   0.6414   1.0000
   6.000   0.5620   0.04938   0.04078  -0.0206   0.6193   1.0000
   6.250   0.6017   0.04863   0.04021  -0.0208   0.5985   1.0000
   6.500   0.6622   0.04615   0.03799  -0.0210   0.5803   1.0000
   6.750   0.6796   0.04620   0.03817  -0.0198   0.5560   1.0000
   7.000   0.7381   0.04251   0.03474  -0.0185   0.5373   1.0000
   7.250   0.8066   0.03744   0.02986  -0.0171   0.5173   1.0000
   7.500   0.8642   0.03357   0.02605  -0.0159   0.4883   1.0000
   7.750   0.9018   0.03210   0.02448  -0.0148   0.4525   1.0000
   8.000   0.9335   0.03182   0.02402  -0.0140   0.4144   1.0000
   8.250   0.9653   0.03221   0.02409  -0.0138   0.3777   1.0000
   8.500   0.9903   0.03338   0.02507  -0.0136   0.3446   1.0000
   8.750   1.0146   0.03477   0.02632  -0.0135   0.3145   1.0000
   9.000   1.0339   0.03658   0.02820  -0.0134   0.2887   1.0000
   9.250   1.0606   0.03828   0.02972  -0.0137   0.2650   1.0000
   9.500   1.0795   0.04042   0.03201  -0.0137   0.2454   1.0000
   9.750   1.1002   0.04269   0.03438  -0.0138   0.2283   1.0000
  10.000   1.1195   0.04514   0.03694  -0.0138   0.2137   1.0000
  10.250   1.1388   0.04777   0.03966  -0.0138   0.2014   1.0000
  10.500   1.1641   0.05035   0.04217  -0.0143   0.1896   1.0000
  10.750   1.1574   0.05399   0.04641  -0.0127   0.1835   1.0000
  11.000   1.1835   0.05681   0.04914  -0.0132   0.1744   1.0000
  11.250   1.1657   0.06112   0.05400  -0.0112   0.1719   1.0000
  11.500   1.1434   0.06567   0.05893  -0.0095   0.1702   1.0000
  11.750   1.1126   0.07071   0.06425  -0.0082   0.1700   1.0000
  12.000   1.0740   0.07733   0.07108  -0.0089   0.1712   1.0000
  12.250   1.0318   0.08561   0.07950  -0.0116   0.1731   1.0000
  12.500   0.9931   0.09505   0.08902  -0.0154   0.1747   1.0000
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