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AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AS5045 (15%) (as5045-il)
Reynolds number: 200,000
Max Cl/Cd: 59.55 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-as5045-il-200000.txt
Download as CSV file: xf-as5045-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4649   0.09252   0.08951  -0.0415   1.0000   0.0663
 -11.250  -0.4963   0.08413   0.08107  -0.0465   1.0000   0.0663
 -11.000  -0.5253   0.07710   0.07398  -0.0500   1.0000   0.0662
 -10.750  -0.5521   0.07103   0.06784  -0.0525   1.0000   0.0662
  -7.750  -0.6004   0.03157   0.02412  -0.0511   0.8488   0.0364
  -7.500  -0.5747   0.02867   0.02101  -0.0506   0.8454   0.0338
  -7.250  -0.5476   0.02693   0.01879  -0.0497   0.8418   0.0313
  -7.000  -0.5208   0.02594   0.01764  -0.0494   0.8384   0.0309
  -6.750  -0.4940   0.02458   0.01620  -0.0490   0.8355   0.0308
  -6.500  -0.4681   0.02321   0.01482  -0.0484   0.8330   0.0310
  -6.250  -0.4443   0.02189   0.01355  -0.0476   0.8306   0.0315
  -6.000  -0.4214   0.02081   0.01255  -0.0471   0.8276   0.0324
  -5.750  -0.3984   0.01994   0.01170  -0.0469   0.8244   0.0337
  -5.500  -0.3745   0.01923   0.01098  -0.0468   0.8215   0.0361
  -5.250  -0.3511   0.01836   0.01008  -0.0469   0.8190   0.0393
  -5.000  -0.3263   0.01765   0.00932  -0.0472   0.8166   0.0435
  -4.750  -0.3007   0.01688   0.00848  -0.0475   0.8142   0.0527
  -4.500  -0.2862   0.01327   0.00764  -0.0489   0.8112   0.5589
  -4.250  -0.2578   0.01447   0.00880  -0.0479   0.8086   0.6187
  -4.000  -0.2328   0.01597   0.01035  -0.0454   0.8060   0.6422
  -3.750  -0.2112   0.01795   0.01240  -0.0412   0.8032   0.6666
  -3.500  -0.1870   0.01882   0.01324  -0.0389   0.8007   0.6762
  -3.250  -0.1597   0.01895   0.01325  -0.0388   0.7984   0.6829
  -3.000  -0.1336   0.01922   0.01350  -0.0380   0.7955   0.6876
  -2.750  -0.1038   0.01912   0.01329  -0.0392   0.7923   0.6968
  -2.500  -0.0790   0.01933   0.01348  -0.0379   0.7893   0.7000
  -2.250  -0.0525   0.01944   0.01352  -0.0375   0.7863   0.7047
  -2.000  -0.0216   0.01929   0.01322  -0.0391   0.7835   0.7123
  -1.750   0.0036   0.01936   0.01330  -0.0383   0.7801   0.7149
  -1.500   0.0299   0.01942   0.01336  -0.0380   0.7762   0.7184
  -1.250   0.0585   0.01937   0.01325  -0.0386   0.7725   0.7234
  -1.000   0.0887   0.01924   0.01302  -0.0397   0.7691   0.7285
  -0.750   0.1140   0.01930   0.01308  -0.0391   0.7655   0.7310
  -0.500   0.1407   0.01931   0.01311  -0.0391   0.7606   0.7341
  -0.250   0.1691   0.01927   0.01303  -0.0395   0.7562   0.7379
   0.000   0.2007   0.01918   0.01284  -0.0409   0.7524   0.7426
   0.250   0.2271   0.01916   0.01285  -0.0408   0.7472   0.7452
   0.500   0.2532   0.01914   0.01285  -0.0405   0.7417   0.7477
   0.750   0.2808   0.01908   0.01276  -0.0404   0.7372   0.7505
   1.000   0.3091   0.01908   0.01277  -0.0409   0.7315   0.7536
   1.250   0.3394   0.01897   0.01265  -0.0418   0.7253   0.7567
   1.500   0.3707   0.01883   0.01243  -0.0427   0.7206   0.7595
   1.750   0.3964   0.01878   0.01246  -0.0425   0.7134   0.7615
   2.000   0.4240   0.01862   0.01231  -0.0423   0.7073   0.7635
   2.250   0.4523   0.01850   0.01218  -0.0423   0.7014   0.7655
   2.500   0.4807   0.01834   0.01206  -0.0425   0.6932   0.7680
   2.750   0.5112   0.01809   0.01176  -0.0428   0.6880   0.7707
   3.000   0.5408   0.01794   0.01168  -0.0436   0.6784   0.7732
   3.250   0.5725   0.01760   0.01129  -0.0442   0.6725   0.7751
   3.500   0.5991   0.01738   0.01118  -0.0440   0.6627   0.7769
   3.750   0.6281   0.01700   0.01079  -0.0438   0.6563   0.7790
   4.000   0.6555   0.01674   0.01064  -0.0438   0.6453   0.7812
   4.250   0.6848   0.01638   0.01033  -0.0439   0.6358   0.7833
   4.500   0.7149   0.01593   0.00990  -0.0441   0.6255   0.7854
   4.750   0.7445   0.01554   0.00958  -0.0445   0.6112   0.7877
   5.000   0.7748   0.01516   0.00924  -0.0449   0.5948   0.7902
   5.250   0.8021   0.01485   0.00902  -0.0447   0.5723   0.7922
   5.500   0.8290   0.01460   0.00874  -0.0443   0.5458   0.7941
   5.750   0.8548   0.01454   0.00858  -0.0439   0.5093   0.7961
   6.000   0.8789   0.01476   0.00859  -0.0433   0.4664   0.7983
   6.250   0.9016   0.01523   0.00883  -0.0427   0.4220   0.8007
   6.500   0.9235   0.01583   0.00922  -0.0422   0.3781   0.8035
   6.750   0.9459   0.01648   0.00968  -0.0419   0.3371   0.8060
   7.000   0.9660   0.01712   0.01017  -0.0411   0.3017   0.8080
   7.250   0.9858   0.01777   0.01072  -0.0403   0.2707   0.8102
   7.500   1.0057   0.01845   0.01131  -0.0396   0.2433   0.8125
   7.750   1.0248   0.01921   0.01195  -0.0388   0.2195   0.8153
   8.000   1.0450   0.01991   0.01261  -0.0382   0.1976   0.8184
   8.250   1.0643   0.02072   0.01334  -0.0376   0.1786   0.8215
   8.500   1.0813   0.02152   0.01409  -0.0366   0.1623   0.8241
   8.750   1.0975   0.02233   0.01488  -0.0354   0.1478   0.8268
   9.000   1.1137   0.02316   0.01572  -0.0343   0.1349   0.8299
   9.250   1.1292   0.02406   0.01665  -0.0332   0.1236   0.8333
   9.500   1.1416   0.02510   0.01765  -0.0318   0.1143   0.8369
   9.750   1.1527   0.02603   0.01861  -0.0300   0.1063   0.8406
  10.000   1.1651   0.02711   0.01977  -0.0287   0.0990   0.8449
  10.250   1.1772   0.02831   0.02096  -0.0276   0.0927   0.8495
  10.500   1.1909   0.02957   0.02232  -0.0267   0.0873   0.8541
  10.750   1.2030   0.03072   0.02355  -0.0257   0.0825   0.8588
  11.000   1.2145   0.03223   0.02503  -0.0246   0.0781   0.8643
  11.250   1.2278   0.03344   0.02642  -0.0239   0.0743   0.8705
  11.500   1.2391   0.03470   0.02777  -0.0229   0.0710   0.8777
  11.750   1.2531   0.03627   0.02925  -0.0216   0.0673   0.8857
  12.000   1.2616   0.03755   0.03082  -0.0204   0.0650   0.8982
  12.250   1.2676   0.03879   0.03226  -0.0185   0.0626   0.9216
  12.500   1.2745   0.04006   0.03364  -0.0172   0.0603   1.0000
  12.750   1.2907   0.04178   0.03530  -0.0171   0.0577   1.0000
  13.000   1.3030   0.04385   0.03752  -0.0169   0.0556   1.0000
  13.250   1.3110   0.04590   0.03976  -0.0168   0.0536   1.0000
  13.500   1.3188   0.04797   0.04195  -0.0166   0.0517   1.0000
  13.750   1.3272   0.04992   0.04395  -0.0165   0.0500   1.0000
  14.000   1.3402   0.05212   0.04611  -0.0158   0.0479   1.0000
  14.250   1.3385   0.05499   0.04922  -0.0155   0.0468   1.0000
  14.500   1.3357   0.05794   0.05241  -0.0154   0.0456   1.0000
  14.750   1.3330   0.06099   0.05565  -0.0153   0.0444   1.0000
  15.000   1.3299   0.06409   0.05891  -0.0154   0.0432   1.0000
  15.250   1.3284   0.06699   0.06190  -0.0157   0.0420   1.0000
  15.500   1.3315   0.06947   0.06438  -0.0158   0.0408   1.0000
  15.750   1.3281   0.07348   0.06846  -0.0156   0.0395   1.0000
  16.000   1.3121   0.07818   0.07343  -0.0168   0.0391   1.0000
  16.250   1.2946   0.08350   0.07901  -0.0186   0.0387   1.0000
  16.500   1.2759   0.08950   0.08527  -0.0210   0.0383   1.0000
  16.750   1.2552   0.09626   0.09227  -0.0241   0.0380   1.0000
  17.000   1.2315   0.10401   0.10028  -0.0281   0.0378   1.0000
  17.250   1.2039   0.11310   0.10961  -0.0334   0.0378   1.0000
  17.500   1.1699   0.12414   0.12090  -0.0403   0.0381   1.0000
  17.750   1.1277   0.13794   0.13493  -0.0494   0.0388   1.0000
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