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AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AS5045 (15%) (as5045-il)
Reynolds number: 100,000
Max Cl/Cd: 43.54 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-as5045-il-100000-n5.txt
Download as CSV file: xf-as5045-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6103   0.09422   0.08918  -0.0301   1.0000   0.0239
 -11.750  -0.6313   0.08622   0.08110  -0.0355   1.0000   0.0236
 -11.500  -0.6529   0.07935   0.07410  -0.0398   1.0000   0.0233
 -11.250  -0.6733   0.07351   0.06812  -0.0430   1.0000   0.0231
 -11.000  -0.6920   0.06843   0.06287  -0.0451   1.0000   0.0229
 -10.750  -0.7086   0.06396   0.05822  -0.0464   1.0000   0.0227
 -10.500  -0.7232   0.05999   0.05405  -0.0470   1.0000   0.0225
 -10.250  -0.7357   0.05649   0.05034  -0.0468   1.0000   0.0223
 -10.000  -0.7436   0.05327   0.04688  -0.0461   1.0000   0.0221
  -9.500  -0.7268   0.04615   0.03893  -0.0481   0.9047   0.0218
  -9.250  -0.7105   0.04308   0.03539  -0.0487   0.8854   0.0218
  -9.000  -0.6933   0.04050   0.03238  -0.0487   0.8724   0.0218
  -8.750  -0.6740   0.03823   0.02974  -0.0485   0.8629   0.0219
  -8.500  -0.6529   0.03619   0.02740  -0.0482   0.8552   0.0221
  -8.250  -0.6301   0.03436   0.02531  -0.0478   0.8493   0.0224
  -8.000  -0.6059   0.03270   0.02344  -0.0475   0.8442   0.0228
  -7.750  -0.5812   0.03121   0.02178  -0.0471   0.8393   0.0233
  -7.500  -0.5565   0.02997   0.02036  -0.0466   0.8348   0.0242
  -7.250  -0.5325   0.02884   0.01910  -0.0461   0.8307   0.0255
  -7.000  -0.5100   0.02777   0.01807  -0.0457   0.8263   0.0269
  -6.750  -0.4875   0.02679   0.01705  -0.0452   0.8224   0.0282
  -6.500  -0.4658   0.02583   0.01602  -0.0447   0.8190   0.0293
  -6.250  -0.4444   0.02494   0.01502  -0.0442   0.8159   0.0305
  -6.000  -0.4239   0.02396   0.01401  -0.0439   0.8125   0.0321
  -5.750  -0.4020   0.02314   0.01311  -0.0437   0.8087   0.0344
  -5.500  -0.3791   0.02240   0.01228  -0.0436   0.8053   0.0388
  -5.250  -0.3558   0.02167   0.01151  -0.0435   0.8024   0.0467
  -5.000  -0.3337   0.02066   0.01064  -0.0433   0.7999   0.0707
  -4.750  -0.3257   0.01737   0.00952  -0.0438   0.7968   0.4182
  -4.500  -0.3041   0.01875   0.01159  -0.0402   0.7936   0.5774
  -4.250  -0.2785   0.02067   0.01344  -0.0375   0.7904   0.6304
  -4.000  -0.2523   0.02143   0.01406  -0.0361   0.7878   0.6462
  -3.750  -0.2253   0.02163   0.01410  -0.0355   0.7853   0.6527
  -3.500  -0.1981   0.02173   0.01401  -0.0353   0.7829   0.6605
  -3.250  -0.1708   0.02174   0.01390  -0.0354   0.7797   0.6672
  -3.000  -0.1441   0.02183   0.01389  -0.0351   0.7767   0.6723
  -2.750  -0.1151   0.02162   0.01351  -0.0363   0.7737   0.6804
  -2.500  -0.0888   0.02170   0.01350  -0.0357   0.7708   0.6836
  -2.250  -0.0618   0.02173   0.01343  -0.0355   0.7682   0.6878
  -2.000  -0.0334   0.02163   0.01323  -0.0363   0.7652   0.6936
  -1.750  -0.0056   0.02156   0.01309  -0.0368   0.7615   0.6979
  -1.500   0.0210   0.02158   0.01307  -0.0366   0.7580   0.7010
  -1.250   0.0485   0.02157   0.01299  -0.0368   0.7547   0.7048
  -1.000   0.0777   0.02149   0.01280  -0.0375   0.7518   0.7096
  -0.750   0.1055   0.02146   0.01275  -0.0381   0.7476   0.7133
  -0.500   0.1319   0.02149   0.01278  -0.0380   0.7432   0.7159
  -0.250   0.1593   0.02149   0.01274  -0.0381   0.7393   0.7190
   0.000   0.1879   0.02146   0.01265  -0.0384   0.7359   0.7223
   0.250   0.2167   0.02145   0.01263  -0.0394   0.7306   0.7260
   0.500   0.2447   0.02144   0.01261  -0.0398   0.7255   0.7287
   0.750   0.2720   0.02142   0.01258  -0.0397   0.7213   0.7309
   1.000   0.2990   0.02145   0.01264  -0.0398   0.7160   0.7332
   1.250   0.3263   0.02147   0.01269  -0.0400   0.7098   0.7359
   1.500   0.3553   0.02139   0.01259  -0.0403   0.7050   0.7388
   1.750   0.3836   0.02141   0.01265  -0.0410   0.6979   0.7416
   2.000   0.4124   0.02135   0.01260  -0.0414   0.6916   0.7440
   2.250   0.4395   0.02128   0.01256  -0.0412   0.6858   0.7460
   2.500   0.4657   0.02128   0.01265  -0.0411   0.6774   0.7483
   2.750   0.4947   0.02110   0.01248  -0.0410   0.6718   0.7505
   3.000   0.5212   0.02110   0.01259  -0.0412   0.6616   0.7528
   3.250   0.5504   0.02090   0.01240  -0.0414   0.6542   0.7555
   3.500   0.5787   0.02078   0.01238  -0.0417   0.6435   0.7583
   3.750   0.6053   0.02065   0.01236  -0.0416   0.6325   0.7605
   4.000   0.6324   0.02040   0.01220  -0.0413   0.6222   0.7625
   4.250   0.6595   0.02016   0.01207  -0.0410   0.6101   0.7645
   4.500   0.6861   0.01999   0.01202  -0.0408   0.5954   0.7669
   4.750   0.7132   0.01982   0.01194  -0.0407   0.5787   0.7696
   5.000   0.7406   0.01968   0.01190  -0.0407   0.5582   0.7725
   5.250   0.7688   0.01944   0.01167  -0.0407   0.5353   0.7751
   5.500   0.7944   0.01927   0.01148  -0.0399   0.5067   0.7769
   5.750   0.8191   0.01923   0.01133  -0.0391   0.4734   0.7791
   6.000   0.8422   0.01944   0.01139  -0.0383   0.4364   0.7816
   6.250   0.8642   0.01985   0.01165  -0.0375   0.3994   0.7846
   6.500   0.8857   0.02040   0.01206  -0.0369   0.3646   0.7876
   6.750   0.9072   0.02102   0.01255  -0.0364   0.3319   0.7905
   7.000   0.9265   0.02164   0.01311  -0.0355   0.3028   0.7928
   7.250   0.9455   0.02232   0.01371  -0.0346   0.2757   0.7953
   7.750   0.9829   0.02381   0.01509  -0.0330   0.2280   0.8014
   8.000   1.0010   0.02463   0.01586  -0.0323   0.2074   0.8051
   8.250   1.0175   0.02547   0.01666  -0.0313   0.1897   0.8083
   8.500   1.0334   0.02630   0.01751  -0.0302   0.1741   0.8117
   9.000   1.0642   0.02812   0.01938  -0.0282   0.1473   0.8192
   9.250   1.0776   0.02906   0.02038  -0.0269   0.1362   0.8231
   9.500   1.0883   0.03008   0.02146  -0.0253   0.1269   0.8271
   9.750   1.0994   0.03126   0.02267  -0.0241   0.1184   0.8320
  10.000   1.1127   0.03243   0.02395  -0.0233   0.1101   0.8376
  10.250   1.1209   0.03383   0.02535  -0.0221   0.1037   0.8433
  10.500   1.1332   0.03507   0.02677  -0.0213   0.0968   0.8501
  10.750   1.1412   0.03659   0.02833  -0.0203   0.0918   0.8575
  11.000   1.1513   0.03798   0.02990  -0.0193   0.0866   0.8664
  11.250   1.1591   0.03945   0.03150  -0.0182   0.0820   0.8776
  11.500   1.1634   0.04109   0.03316  -0.0169   0.0786   0.8945
  11.750   1.1679   0.04233   0.03467  -0.0149   0.0752   0.9463
  12.000   1.1770   0.04410   0.03655  -0.0147   0.0715   1.0000
  12.250   1.1854   0.04613   0.03860  -0.0148   0.0684   1.0000
  12.500   1.1945   0.04817   0.04074  -0.0146   0.0657   1.0000
  12.750   1.2032   0.05026   0.04300  -0.0144   0.0628   1.0000
  13.000   1.2099   0.05247   0.04532  -0.0144   0.0603   1.0000
  13.250   1.2149   0.05478   0.04767  -0.0143   0.0582   1.0000
  13.500   1.2200   0.05719   0.05013  -0.0141   0.0563   1.0000
  13.750   1.2234   0.05990   0.05309  -0.0141   0.0544   1.0000
  14.000   1.2251   0.06276   0.05614  -0.0141   0.0526   1.0000
  14.250   1.2256   0.06572   0.05925  -0.0144   0.0510   1.0000
  14.500   1.2254   0.06873   0.06234  -0.0147   0.0495   1.0000
  14.750   1.2260   0.07166   0.06533  -0.0151   0.0482   1.0000
  15.000   1.2227   0.07527   0.06909  -0.0156   0.0471   1.0000
  15.250   1.2139   0.07982   0.07392  -0.0168   0.0461   1.0000
  15.500   1.2033   0.08479   0.07915  -0.0184   0.0452   1.0000
  15.750   1.1911   0.09026   0.08485  -0.0206   0.0444   1.0000
  16.000   1.1772   0.09626   0.09108  -0.0233   0.0436   1.0000
  16.250   1.1614   0.10290   0.09793  -0.0267   0.0430   1.0000
  16.500   1.1423   0.11052   0.10576  -0.0309   0.0425   1.0000
  16.750   1.1154   0.12029   0.11577  -0.0368   0.0424   1.0000
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