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AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AS5045 (15%) (as5045-il)
Reynolds number: 50,000
Max Cl/Cd: 29.23 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-as5045-il-50000-n5.txt
Download as CSV file: xf-as5045-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6456   0.08770   0.08035  -0.0408   1.0000   0.0376
 -11.250  -0.6588   0.08272   0.07528  -0.0431   1.0000   0.0375
 -11.000  -0.6730   0.07806   0.07051  -0.0450   1.0000   0.0373
 -10.750  -0.6869   0.07380   0.06612  -0.0463   1.0000   0.0372
 -10.500  -0.7003   0.06995   0.06211  -0.0470   1.0000   0.0371
 -10.250  -0.7129   0.06652   0.05851  -0.0469   1.0000   0.0371
 -10.000  -0.7214   0.06328   0.05503  -0.0465   1.0000   0.0372
  -9.750  -0.7255   0.06013   0.05158  -0.0459   1.0000   0.0374
  -9.250  -0.7162   0.05412   0.04516  -0.0447   1.0000   0.0384
  -9.000  -0.7054   0.05152   0.04244  -0.0441   1.0000   0.0391
  -8.750  -0.6946   0.04907   0.03979  -0.0433   1.0000   0.0396
  -8.500  -0.6833   0.04680   0.03732  -0.0421   1.0000   0.0400
  -8.250  -0.6733   0.04486   0.03519  -0.0404   1.0000   0.0403
  -8.000  -0.6655   0.04330   0.03347  -0.0381   0.9991   0.0407
  -7.750  -0.6329   0.04104   0.03091  -0.0393   0.9864   0.0416
  -7.500  -0.5979   0.03915   0.02880  -0.0401   0.9764   0.0428
  -7.250  -0.5603   0.03769   0.02711  -0.0406   0.9689   0.0447
  -7.000  -0.5248   0.03647   0.02585  -0.0409   0.9619   0.0480
  -6.750  -0.4938   0.03538   0.02466  -0.0413   0.9539   0.0520
  -6.500  -0.4646   0.03430   0.02336  -0.0417   0.9459   0.0556
  -6.250  -0.4426   0.03289   0.02198  -0.0422   0.9371   0.0603
  -6.000  -0.4190   0.03152   0.02051  -0.0431   0.9297   0.0687
  -5.750  -0.4007   0.03008   0.01907  -0.0434   0.9217   0.0811
  -5.500  -0.3862   0.02799   0.01742  -0.0439   0.9146   0.1200
  -5.250  -0.3897   0.02598   0.01799  -0.0395   0.9071   0.4358
  -5.000  -0.3657   0.02944   0.02151  -0.0341   0.9013   0.5981
  -4.750  -0.3336   0.03355   0.02540  -0.0273   0.8979   0.6552
  -4.500  -0.3091   0.03357   0.02511  -0.0267   0.8928   0.6689
  -4.250  -0.2872   0.03337   0.02464  -0.0262   0.8873   0.6818
  -4.000  -0.2585   0.03333   0.02433  -0.0261   0.8831   0.6914
  -3.750  -0.2323   0.03314   0.02390  -0.0260   0.8789   0.7012
  -3.500  -0.2150   0.03287   0.02344  -0.0253   0.8731   0.7124
  -3.250  -0.1875   0.03278   0.02317  -0.0250   0.8689   0.7191
  -3.000  -0.1643   0.03244   0.02262  -0.0252   0.8646   0.7287
  -2.750  -0.1408   0.03236   0.02240  -0.0246   0.8599   0.7348
  -2.500  -0.1230   0.03210   0.02200  -0.0242   0.8545   0.7438
  -2.250  -0.0957   0.03198   0.02173  -0.0241   0.8504   0.7490
  -2.000  -0.0722   0.03178   0.02141  -0.0242   0.8460   0.7560
  -1.750  -0.0543   0.03169   0.02123  -0.0233   0.8403   0.7621
  -1.500  -0.0295   0.03158   0.02102  -0.0233   0.8355   0.7674
  -1.250  -0.0035   0.03140   0.02071  -0.0240   0.8314   0.7738
  -1.000   0.0147   0.03142   0.02069  -0.0230   0.8252   0.7785
  -0.750   0.0384   0.03138   0.02058  -0.0229   0.8199   0.7834
  -0.500   0.0657   0.03127   0.02038  -0.0236   0.8155   0.7888
  -0.250   0.0829   0.03135   0.02044  -0.0227   0.8086   0.7932
   0.000   0.1079   0.03135   0.02040  -0.0227   0.8030   0.7971
   0.250   0.1356   0.03132   0.02033  -0.0232   0.7981   0.8014
   0.500   0.1527   0.03148   0.02047  -0.0228   0.7901   0.8062
   0.750   0.1810   0.03147   0.02044  -0.0231   0.7848   0.8093
   1.000   0.2000   0.03164   0.02064  -0.0223   0.7771   0.8131
   1.250   0.2258   0.03171   0.02070  -0.0225   0.7703   0.8169
   1.500   0.2496   0.03186   0.02086  -0.0227   0.7629   0.8208
   1.750   0.2738   0.03198   0.02101  -0.0226   0.7551   0.8241
   2.000   0.2978   0.03211   0.02118  -0.0223   0.7473   0.8274
   2.250   0.3224   0.03223   0.02135  -0.0222   0.7388   0.8309
   2.500   0.3457   0.03243   0.02160  -0.0221   0.7297   0.8345
   2.750   0.3751   0.03246   0.02167  -0.0227   0.7216   0.8380
   3.000   0.3946   0.03270   0.02200  -0.0218   0.7107   0.8412
   3.250   0.4266   0.03252   0.02189  -0.0220   0.7038   0.8444
   3.500   0.4462   0.03278   0.02226  -0.0214   0.6912   0.8481
   3.750   0.4695   0.03294   0.02251  -0.0212   0.6794   0.8518
   4.000   0.5011   0.03265   0.02231  -0.0212   0.6710   0.8550
   4.250   0.5220   0.03271   0.02251  -0.0203   0.6578   0.8587
   4.500   0.5436   0.03275   0.02268  -0.0196   0.6438   0.8627
   4.750   0.5670   0.03271   0.02277  -0.0192   0.6296   0.8666
   5.000   0.5908   0.03255   0.02278  -0.0186   0.6149   0.8704
   5.250   0.6136   0.03230   0.02268  -0.0176   0.5998   0.8745
   5.500   0.6379   0.03196   0.02250  -0.0168   0.5842   0.8791
   6.000   0.6893   0.03095   0.02182  -0.0152   0.5510   0.8880
   6.250   0.7138   0.03048   0.02150  -0.0142   0.5317   0.8929
   6.500   0.7383   0.03011   0.02128  -0.0134   0.5092   0.8985
   6.750   0.7675   0.02930   0.02054  -0.0123   0.4871   0.9040
   7.000   0.7927   0.02894   0.02021  -0.0112   0.4595   0.9104
   7.250   0.8175   0.02875   0.02000  -0.0102   0.4296   0.9172
   7.500   0.8391   0.02890   0.02007  -0.0091   0.3987   0.9249
   7.750   0.8584   0.02937   0.02047  -0.0081   0.3680   0.9341
   8.000   0.8762   0.03008   0.02111  -0.0074   0.3390   0.9466
   8.250   0.8942   0.03096   0.02191  -0.0071   0.3123   0.9670
   8.500   0.9094   0.03199   0.02292  -0.0068   0.2873   1.0000
   8.750   0.9254   0.03321   0.02404  -0.0067   0.2657   1.0000
   9.000   0.9410   0.03457   0.02541  -0.0067   0.2444   1.0000
   9.250   0.9570   0.03600   0.02682  -0.0069   0.2256   1.0000
   9.500   0.9724   0.03751   0.02829  -0.0070   0.2083   1.0000
   9.750   0.9881   0.03906   0.02984  -0.0072   0.1928   1.0000
  10.000   1.0032   0.04069   0.03148  -0.0074   0.1784   1.0000
  10.250   1.0187   0.04235   0.03320  -0.0075   0.1657   1.0000
  10.500   1.0340   0.04405   0.03496  -0.0075   0.1544   1.0000
  10.750   1.0501   0.04567   0.03652  -0.0075   0.1447   1.0000
  11.000   1.0638   0.04758   0.03862  -0.0074   0.1351   1.0000
  11.250   1.0778   0.04949   0.04060  -0.0073   0.1272   1.0000
  11.500   1.0909   0.05145   0.04266  -0.0072   0.1201   1.0000
  11.750   1.1028   0.05362   0.04498  -0.0070   0.1140   1.0000
  12.000   1.1107   0.05605   0.04761  -0.0069   0.1082   1.0000
  12.250   1.1254   0.05791   0.04938  -0.0066   0.1034   1.0000
  12.500   1.1249   0.06134   0.05321  -0.0066   0.0994   1.0000
  12.750   1.1259   0.06445   0.05654  -0.0067   0.0956   1.0000
  13.000   1.1348   0.06668   0.05877  -0.0066   0.0920   1.0000
  13.250   1.1318   0.07046   0.06277  -0.0069   0.0895   1.0000
  13.500   1.1172   0.07553   0.06820  -0.0079   0.0877   1.0000
  13.750   1.0992   0.08118   0.07415  -0.0095   0.0863   1.0000
  14.000   1.0765   0.08774   0.08097  -0.0119   0.0852   1.0000
  14.250   1.0449   0.09618   0.08967  -0.0158   0.0849   1.0000
  14.500   0.9910   0.10991   0.10366  -0.0237   0.0859   1.0000
  14.750   0.9134   0.13301   0.12681  -0.0380   0.0871   1.0000
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