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MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MA409 (smoothed) (ma409sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.24 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ma409sm-il-1000000-n5.txt
Download as CSV file: xf-ma409sm-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MA409 (smoothed)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4612   0.09213   0.09048  -0.0259   1.0000   0.0048
  -9.000  -0.4682   0.08743   0.08581  -0.0269   1.0000   0.0048
  -8.750  -0.5546   0.03089   0.02883  -0.0858   0.9902   0.0045
  -8.500  -0.5307   0.01974   0.01656  -0.0959   0.9868   0.0049
  -8.250  -0.5014   0.01807   0.01466  -0.0976   0.9856   0.0051
  -8.000  -0.4711   0.01692   0.01333  -0.0991   0.9846   0.0053
  -7.750  -0.4401   0.01590   0.01215  -0.1005   0.9838   0.0055
  -7.500  -0.4089   0.01487   0.01096  -0.1019   0.9831   0.0058
  -7.250  -0.3810   0.01397   0.00987  -0.1024   0.9811   0.0060
  -7.000  -0.3536   0.01312   0.00887  -0.1028   0.9787   0.0062
  -6.750  -0.3242   0.01229   0.00789  -0.1035   0.9769   0.0063
  -6.500  -0.2940   0.01155   0.00701  -0.1043   0.9752   0.0065
  -6.250  -0.2636   0.01087   0.00619  -0.1050   0.9737   0.0067
  -6.000  -0.2327   0.01029   0.00551  -0.1059   0.9722   0.0069
  -5.750  -0.2017   0.00983   0.00495  -0.1067   0.9708   0.0072
  -5.500  -0.1720   0.00944   0.00448  -0.1072   0.9685   0.0074
  -5.250  -0.1448   0.00902   0.00399  -0.1070   0.9645   0.0076
  -5.000  -0.1157   0.00851   0.00337  -0.1073   0.9612   0.0080
  -4.750  -0.0854   0.00808   0.00287  -0.1079   0.9585   0.0091
  -4.500  -0.0553   0.00780   0.00255  -0.1084   0.9556   0.0104
  -4.250  -0.0280   0.00758   0.00230  -0.1082   0.9499   0.0116
  -4.000   0.0019   0.00733   0.00202  -0.1086   0.9443   0.0145
  -3.750   0.0300   0.00712   0.00181  -0.1086   0.9363   0.0183
  -3.500   0.0591   0.00692   0.00160  -0.1087   0.9286   0.0241
  -3.250   0.0870   0.00675   0.00142  -0.1087   0.9200   0.0316
  -3.000   0.1152   0.00657   0.00126  -0.1087   0.9119   0.0435
  -2.750   0.1433   0.00640   0.00112  -0.1087   0.9028   0.0616
  -2.500   0.1710   0.00625   0.00100  -0.1087   0.8928   0.0811
  -2.250   0.1987   0.00613   0.00091  -0.1086   0.8820   0.0990
  -2.000   0.2263   0.00605   0.00081  -0.1084   0.8699   0.1148
  -1.750   0.2537   0.00597   0.00074  -0.1083   0.8564   0.1347
  -1.500   0.2809   0.00591   0.00069  -0.1081   0.8415   0.1542
  -1.250   0.3080   0.00587   0.00065  -0.1078   0.8250   0.1775
  -1.000   0.3348   0.00585   0.00061  -0.1075   0.8070   0.2003
  -0.750   0.3616   0.00583   0.00059  -0.1073   0.7874   0.2251
  -0.500   0.3881   0.00585   0.00059  -0.1069   0.7658   0.2490
  -0.250   0.4146   0.00587   0.00060  -0.1066   0.7423   0.2790
   0.000   0.4410   0.00591   0.00062  -0.1062   0.7174   0.3071
   0.250   0.4672   0.00597   0.00066  -0.1059   0.6902   0.3390
   0.500   0.4933   0.00606   0.00071  -0.1055   0.6604   0.3694
   0.750   0.5193   0.00615   0.00077  -0.1051   0.6287   0.4017
   1.000   0.5454   0.00626   0.00085  -0.1048   0.5967   0.4356
   1.250   0.5714   0.00635   0.00093  -0.1044   0.5641   0.4806
   1.500   0.5974   0.00640   0.00103  -0.1042   0.5321   0.5475
   1.750   0.6182   0.00578   0.00122  -0.1027   0.5044   0.8788
   2.000   0.6451   0.00582   0.00129  -0.1024   0.4759   1.0000
   2.250   0.6716   0.00602   0.00139  -0.1021   0.4501   1.0000
   2.500   0.6981   0.00622   0.00150  -0.1018   0.4253   1.0000
   2.750   0.7234   0.00655   0.00165  -0.1014   0.3820   1.0000
   3.000   0.7468   0.00713   0.00188  -0.1007   0.3031   1.0000
   3.250   0.7710   0.00763   0.00211  -0.1001   0.2430   1.0000
   3.500   0.7940   0.00830   0.00241  -0.0994   0.1651   1.0000
   3.750   0.8176   0.00891   0.00272  -0.0987   0.1044   1.0000
   4.000   0.8419   0.00943   0.00304  -0.0982   0.0599   1.0000
   4.250   0.8671   0.00983   0.00334  -0.0977   0.0364   1.0000
   4.500   0.8927   0.01015   0.00361  -0.0973   0.0248   1.0000
   4.750   0.9185   0.01045   0.00388  -0.0970   0.0180   1.0000
   5.000   0.9440   0.01078   0.00418  -0.0965   0.0131   1.0000
   5.250   0.9699   0.01105   0.00448  -0.0962   0.0117   1.0000
   5.500   0.9953   0.01138   0.00482  -0.0957   0.0103   1.0000
   5.750   1.0202   0.01179   0.00525  -0.0952   0.0086   1.0000
   6.000   1.0449   0.01221   0.00573  -0.0946   0.0081   1.0000
   6.250   1.0699   0.01258   0.00613  -0.0941   0.0078   1.0000
   6.500   1.0946   0.01298   0.00658  -0.0935   0.0075   1.0000
   6.750   1.1191   0.01338   0.00703  -0.0930   0.0071   1.0000
   7.000   1.1436   0.01376   0.00746  -0.0924   0.0066   1.0000
   7.250   1.1679   0.01415   0.00788  -0.0919   0.0061   1.0000
   7.500   1.1916   0.01462   0.00837  -0.0912   0.0057   1.0000
   7.750   1.2140   0.01525   0.00907  -0.0903   0.0052   1.0000
   8.000   1.2345   0.01614   0.01006  -0.0891   0.0048   1.0000
   8.250   1.2576   0.01663   0.01061  -0.0884   0.0047   1.0000
   8.500   1.2801   0.01717   0.01122  -0.0876   0.0045   1.0000
   8.750   1.3019   0.01779   0.01191  -0.0866   0.0042   1.0000
   9.000   1.3231   0.01846   0.01268  -0.0856   0.0040   1.0000
   9.250   1.3443   0.01909   0.01339  -0.0846   0.0037   1.0000
   9.500   1.3655   0.01969   0.01405  -0.0837   0.0035   1.0000
   9.750   1.3869   0.02023   0.01463  -0.0828   0.0032   1.0000
  10.000   1.4078   0.02079   0.01524  -0.0818   0.0030   1.0000
  10.250   1.4271   0.02153   0.01604  -0.0807   0.0028   1.0000
  10.500   1.4404   0.02297   0.01766  -0.0785   0.0025   1.0000
  10.750   1.4556   0.02411   0.01892  -0.0767   0.0025   1.0000
  11.000   1.4708   0.02515   0.02009  -0.0750   0.0024   1.0000
  11.250   1.4846   0.02628   0.02137  -0.0730   0.0024   1.0000
  11.500   1.4965   0.02751   0.02275  -0.0709   0.0023   1.0000
  11.750   1.5049   0.02882   0.02421  -0.0682   0.0023   1.0000
  12.000   1.5099   0.03024   0.02579  -0.0650   0.0022   1.0000
  12.250   1.5132   0.03175   0.02746  -0.0618   0.0022   1.0000
  12.500   1.5139   0.03350   0.02938  -0.0586   0.0022   1.0000
  12.750   1.5131   0.03543   0.03148  -0.0555   0.0021   1.0000
  13.000   1.5099   0.03765   0.03389  -0.0527   0.0021   1.0000
  13.250   1.5045   0.04023   0.03665  -0.0501   0.0021   1.0000
  13.500   1.4988   0.04300   0.03959  -0.0481   0.0020   1.0000
  13.750   1.4886   0.04648   0.04327  -0.0465   0.0020   1.0000
  14.000   1.4777   0.05037   0.04734  -0.0457   0.0020   1.0000
  14.250   1.4636   0.05506   0.05223  -0.0459   0.0020   1.0000
  14.500   1.4467   0.06068   0.05804  -0.0472   0.0020   1.0000
  14.750   1.4260   0.06756   0.06513  -0.0499   0.0020   1.0000
  15.000   1.4038   0.07550   0.07325  -0.0538   0.0020   1.0000
  15.250   1.3770   0.08511   0.08305  -0.0592   0.0020   1.0000
  15.500   1.3481   0.09591   0.09402  -0.0655   0.0020   1.0000
  15.750   1.3084   0.10978   0.10807  -0.0733   0.0020   1.0000
  16.000   1.2694   0.12421   0.12264  -0.0811   0.0021   1.0000
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