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N-9 (n9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.64 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n9-il-1000000.txt
Download as CSV file: xf-n9-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-9                                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5141   0.12589   0.12417  -0.0003   1.0000   0.0120
 -12.250  -0.5105   0.12197   0.12026  -0.0019   1.0000   0.0126
 -11.250  -0.7952   0.02868   0.02600  -0.0577   1.0000   0.0089
 -11.000  -0.7848   0.02551   0.02248  -0.0569   1.0000   0.0091
 -10.750  -0.7698   0.02324   0.01994  -0.0559   1.0000   0.0094
 -10.500  -0.7526   0.02138   0.01782  -0.0549   1.0000   0.0096
 -10.250  -0.7336   0.01987   0.01610  -0.0539   1.0000   0.0099
 -10.000  -0.7131   0.01871   0.01475  -0.0528   1.0000   0.0101
  -9.750  -0.6914   0.01791   0.01381  -0.0518   1.0000   0.0103
  -9.500  -0.6748   0.01552   0.01106  -0.0505   1.0000   0.0109
  -9.250  -0.6531   0.01488   0.01036  -0.0494   1.0000   0.0114
  -9.000  -0.6270   0.01451   0.00995  -0.0492   0.9995   0.0119
  -8.750  -0.5937   0.01406   0.00943  -0.0504   0.9982   0.0125
  -8.500  -0.5604   0.01354   0.00883  -0.0516   0.9967   0.0132
  -8.250  -0.5271   0.01307   0.00825  -0.0528   0.9952   0.0136
  -8.000  -0.4957   0.01184   0.00688  -0.0538   0.9936   0.0147
  -7.750  -0.4635   0.01150   0.00652  -0.0547   0.9908   0.0156
  -7.500  -0.4306   0.01117   0.00616  -0.0558   0.9880   0.0166
  -7.250  -0.3970   0.01086   0.00580  -0.0569   0.9856   0.0176
  -7.000  -0.3651   0.01019   0.00507  -0.0579   0.9825   0.0191
  -6.750  -0.3343   0.00997   0.00486  -0.0584   0.9768   0.0205
  -6.250  -0.2688   0.00953   0.00437  -0.0603   0.9651   0.0232
  -6.000  -0.2348   0.00885   0.00363  -0.0616   0.9566   0.0258
  -5.750  -0.2001   0.00862   0.00338  -0.0630   0.9449   0.0280
  -5.250  -0.1404   0.00818   0.00278  -0.0634   0.9195   0.0312
  -5.000  -0.1132   0.00790   0.00244  -0.0631   0.9082   0.0345
  -4.750  -0.0858   0.00776   0.00226  -0.0628   0.8982   0.0368
  -4.500  -0.0585   0.00767   0.00208  -0.0625   0.8881   0.0387
  -4.250  -0.0311   0.00746   0.00185  -0.0622   0.8770   0.0427
  -4.000  -0.0038   0.00731   0.00168  -0.0619   0.8642   0.0482
  -3.750   0.0233   0.00711   0.00155  -0.0616   0.8483   0.0689
  -3.500   0.0505   0.00703   0.00146  -0.0612   0.8257   0.0865
  -3.250   0.0770   0.00700   0.00133  -0.0608   0.7878   0.0960
  -3.000   0.1034   0.00707   0.00123  -0.0603   0.7516   0.1019
  -2.750   0.1304   0.00705   0.00115  -0.0600   0.7294   0.1122
  -2.500   0.1579   0.00702   0.00108  -0.0599   0.7140   0.1258
  -2.250   0.1852   0.00682   0.00106  -0.0598   0.7002   0.2019
  -2.000   0.2127   0.00671   0.00104  -0.0597   0.6858   0.2450
  -1.750   0.2401   0.00651   0.00101  -0.0597   0.6732   0.3184
  -1.500   0.2669   0.00610   0.00102  -0.0597   0.6628   0.4701
  -1.250   0.2929   0.00565   0.00104  -0.0595   0.6495   0.6416
  -1.000   0.3167   0.00519   0.00108  -0.0586   0.6364   0.8133
  -0.750   0.3381   0.00492   0.00114  -0.0566   0.6251   0.9527
  -0.500   0.3772   0.00496   0.00113  -0.0589   0.6106   0.9906
  -0.250   0.4125   0.00503   0.00114  -0.0606   0.5956   1.0000
   0.000   0.4390   0.00513   0.00115  -0.0603   0.5774   1.0000
   0.250   0.4655   0.00525   0.00117  -0.0599   0.5515   1.0000
   0.500   0.4916   0.00543   0.00120  -0.0596   0.5161   1.0000
   0.750   0.5166   0.00576   0.00128  -0.0591   0.4562   1.0000
   1.000   0.5419   0.00611   0.00139  -0.0586   0.4061   1.0000
   1.250   0.5679   0.00638   0.00151  -0.0584   0.3735   1.0000
   1.500   0.5946   0.00658   0.00162  -0.0582   0.3512   1.0000
   1.750   0.6213   0.00679   0.00173  -0.0580   0.3315   1.0000
   2.000   0.6481   0.00698   0.00185  -0.0579   0.3151   1.0000
   2.250   0.6750   0.00716   0.00197  -0.0577   0.2996   1.0000
   2.500   0.7019   0.00734   0.00209  -0.0576   0.2837   1.0000
   2.750   0.7287   0.00754   0.00222  -0.0575   0.2633   1.0000
   3.000   0.7543   0.00789   0.00239  -0.0573   0.2240   1.0000
   3.250   0.7759   0.00880   0.00282  -0.0565   0.1276   1.0000
   3.500   0.8018   0.00913   0.00308  -0.0562   0.1137   1.0000
   3.750   0.8280   0.00940   0.00332  -0.0561   0.1066   1.0000
   4.000   0.8543   0.00967   0.00358  -0.0559   0.1009   1.0000
   4.250   0.8812   0.00985   0.00378  -0.0558   0.0978   1.0000
   4.500   0.9074   0.01010   0.00401  -0.0557   0.0924   1.0000
   4.750   0.9334   0.01039   0.00431  -0.0555   0.0871   1.0000
   5.000   0.9603   0.01054   0.00448  -0.0555   0.0844   1.0000
   5.250   0.9866   0.01076   0.00470  -0.0553   0.0804   1.0000
   5.500   1.0121   0.01109   0.00500  -0.0551   0.0745   1.0000
   5.750   1.0388   0.01124   0.00519  -0.0551   0.0720   1.0000
   6.000   1.0649   0.01147   0.00541  -0.0550   0.0673   1.0000
   6.250   1.0904   0.01176   0.00568  -0.0548   0.0617   1.0000
   6.500   1.1161   0.01201   0.00593  -0.0547   0.0559   1.0000
   6.750   1.1409   0.01238   0.00625  -0.0544   0.0463   1.0000
   7.000   1.1635   0.01300   0.00674  -0.0538   0.0298   1.0000
   7.250   1.1851   0.01375   0.00740  -0.0531   0.0189   1.0000
   7.500   1.2078   0.01434   0.00801  -0.0524   0.0160   1.0000
   7.750   1.2303   0.01494   0.00867  -0.0518   0.0142   1.0000
   8.000   1.2533   0.01546   0.00924  -0.0512   0.0132   1.0000
   8.250   1.2753   0.01605   0.00988  -0.0506   0.0122   1.0000
   8.500   1.2941   0.01702   0.01093  -0.0494   0.0109   1.0000
   8.750   1.3159   0.01759   0.01156  -0.0487   0.0105   1.0000
   9.000   1.3371   0.01819   0.01223  -0.0480   0.0101   1.0000
   9.250   1.3573   0.01886   0.01298  -0.0471   0.0096   1.0000
   9.500   1.3768   0.01957   0.01375  -0.0462   0.0091   1.0000
   9.750   1.3950   0.02036   0.01462  -0.0451   0.0087   1.0000
  10.000   1.4096   0.02146   0.01580  -0.0435   0.0083   1.0000
  10.250   1.4144   0.02334   0.01784  -0.0406   0.0079   1.0000
  10.500   1.4305   0.02410   0.01869  -0.0393   0.0077   1.0000
  10.750   1.4436   0.02496   0.01965  -0.0375   0.0076   1.0000
  11.000   1.4537   0.02586   0.02063  -0.0353   0.0074   1.0000
  11.250   1.4624   0.02688   0.02175  -0.0331   0.0072   1.0000
  11.500   1.4704   0.02799   0.02295  -0.0310   0.0069   1.0000
  11.750   1.4767   0.02929   0.02435  -0.0291   0.0068   1.0000
  12.000   1.4823   0.03074   0.02589  -0.0274   0.0066   1.0000
  12.250   1.4859   0.03246   0.02771  -0.0259   0.0064   1.0000
  12.500   1.4888   0.03435   0.02970  -0.0246   0.0063   1.0000
  12.750   1.4898   0.03656   0.03202  -0.0237   0.0062   1.0000
  13.000   1.4881   0.03923   0.03480  -0.0231   0.0061   1.0000
  13.250   1.4833   0.04252   0.03822  -0.0230   0.0059   1.0000
  13.500   1.4751   0.04648   0.04233  -0.0235   0.0059   1.0000
  13.750   1.4626   0.05125   0.04725  -0.0245   0.0058   1.0000
  14.000   1.4467   0.05671   0.05287  -0.0260   0.0057   1.0000
  14.250   1.4315   0.06234   0.05865  -0.0279   0.0057   1.0000
  14.500   1.4097   0.06919   0.06567  -0.0304   0.0056   1.0000
  14.750   1.3918   0.07588   0.07252  -0.0333   0.0056   1.0000
  15.000   1.3731   0.08298   0.07976  -0.0365   0.0056   1.0000
  15.250   1.3530   0.09061   0.08753  -0.0400   0.0056   1.0000
  15.500   1.3327   0.09843   0.09549  -0.0436   0.0056   1.0000
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