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N-9 (n9-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 200,000
Max Cl/Cd: 68.1 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n9-il-200000.txt
Download as CSV file: xf-n9-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4812   0.09932   0.09575  -0.0191   1.0000   0.0490
 -10.000  -0.4864   0.09515   0.09163  -0.0248   1.0000   0.0494
  -9.750  -0.4896   0.09057   0.08711  -0.0305   1.0000   0.0496
  -9.500  -0.4904   0.08482   0.08140  -0.0298   1.0000   0.0504
  -9.250  -0.4803   0.08269   0.07929  -0.0255   1.0000   0.0516
  -9.000  -0.4733   0.07978   0.07639  -0.0257   1.0000   0.0529
  -8.750  -0.4682   0.07617   0.07280  -0.0280   1.0000   0.0545
  -8.500  -0.4636   0.07189   0.06853  -0.0317   1.0000   0.0565
  -8.250  -0.4618   0.06420   0.06045  -0.0446   1.0000   0.0611
  -8.000  -0.4603   0.05775   0.05396  -0.0455   1.0000   0.0622
  -7.750  -0.4488   0.05590   0.05227  -0.0429   1.0000   0.0638
  -7.500  -0.4375   0.05419   0.05059  -0.0413   1.0000   0.0667
  -7.250  -0.4255   0.05136   0.04694  -0.0441   1.0000   0.0741
  -7.000  -0.4194   0.04483   0.04062  -0.0436   1.0000   0.0760
  -6.750  -0.4068   0.03341   0.02823  -0.0432   1.0000   0.0485
  -6.500  -0.3915   0.02907   0.02353  -0.0424   1.0000   0.0464
  -6.250  -0.3721   0.02590   0.01984  -0.0413   1.0000   0.0473
  -6.000  -0.3504   0.02338   0.01683  -0.0402   1.0000   0.0484
  -5.750  -0.3273   0.02148   0.01449  -0.0393   1.0000   0.0493
  -5.500  -0.3034   0.01921   0.01197  -0.0389   1.0000   0.0520
  -5.250  -0.2805   0.01859   0.01130  -0.0382   1.0000   0.0556
  -5.000  -0.2559   0.01762   0.01012  -0.0376   1.0000   0.0585
  -4.750  -0.2290   0.01680   0.00910  -0.0374   0.9996   0.0622
  -4.500  -0.1874   0.01588   0.00821  -0.0404   0.9955   0.0681
  -4.250  -0.1454   0.01529   0.00748  -0.0432   0.9903   0.0746
  -4.000  -0.1037   0.01445   0.00673  -0.0461   0.9855   0.0838
  -3.750  -0.0625   0.01367   0.00600  -0.0489   0.9786   0.0978
  -3.500  -0.0181   0.01266   0.00511  -0.0524   0.9727   0.1304
  -3.250   0.0231   0.01191   0.00471  -0.0553   0.9633   0.1887
  -3.000   0.0656   0.01084   0.00438  -0.0588   0.9567   0.3618
  -2.750   0.0966   0.00933   0.00428  -0.0591   0.9480   0.7259
  -2.500   0.1566   0.00877   0.00411  -0.0641   0.9446   1.0000
  -2.250   0.1973   0.00860   0.00378  -0.0664   0.9320   1.0000
  -2.000   0.2339   0.00850   0.00355  -0.0679   0.9186   1.0000
  -1.750   0.2667   0.00847   0.00339  -0.0686   0.9042   1.0000
  -1.500   0.2958   0.00850   0.00330  -0.0685   0.8887   1.0000
  -1.250   0.3222   0.00856   0.00325  -0.0678   0.8723   1.0000
  -1.000   0.3473   0.00862   0.00322  -0.0670   0.8550   1.0000
  -0.750   0.3727   0.00866   0.00319  -0.0662   0.8379   1.0000
  -0.500   0.3983   0.00870   0.00315  -0.0654   0.8211   1.0000
  -0.250   0.4239   0.00873   0.00309  -0.0646   0.8033   1.0000
   0.000   0.4494   0.00875   0.00301  -0.0638   0.7837   1.0000
   0.250   0.4749   0.00882   0.00296  -0.0629   0.7624   1.0000
   0.500   0.5006   0.00894   0.00293  -0.0621   0.7423   1.0000
   0.750   0.5262   0.00909   0.00300  -0.0614   0.7222   1.0000
   1.000   0.5519   0.00928   0.00308  -0.0607   0.7022   1.0000
   1.250   0.5775   0.00948   0.00318  -0.0601   0.6821   1.0000
   1.500   0.6028   0.00964   0.00330  -0.0594   0.6589   1.0000
   1.750   0.6282   0.00982   0.00340  -0.0587   0.6355   1.0000
   2.000   0.6533   0.00999   0.00352  -0.0580   0.6087   1.0000
   2.250   0.6781   0.01017   0.00362  -0.0573   0.5770   1.0000
   2.500   0.7026   0.01038   0.00372  -0.0565   0.5375   1.0000
   2.750   0.7266   0.01067   0.00386  -0.0557   0.4952   1.0000
   3.000   0.7504   0.01104   0.00407  -0.0549   0.4582   1.0000
   3.250   0.7741   0.01146   0.00432  -0.0542   0.4235   1.0000
   3.500   0.7980   0.01189   0.00462  -0.0535   0.3940   1.0000
   3.750   0.8222   0.01231   0.00494  -0.0530   0.3683   1.0000
   4.000   0.8462   0.01273   0.00531  -0.0524   0.3413   1.0000
   4.250   0.8698   0.01318   0.00567  -0.0518   0.3043   1.0000
   4.500   0.8918   0.01381   0.00606  -0.0509   0.2394   1.0000
   4.750   0.9119   0.01477   0.00661  -0.0499   0.1749   1.0000
   5.000   0.9332   0.01560   0.00730  -0.0491   0.1547   1.0000
   5.250   0.9544   0.01645   0.00805  -0.0482   0.1432   1.0000
   5.500   0.9770   0.01713   0.00879  -0.0474   0.1353   1.0000
   5.750   0.9976   0.01811   0.00971  -0.0465   0.1281   1.0000
   6.000   1.0199   0.01883   0.01050  -0.0458   0.1200   1.0000
   6.250   1.0411   0.01974   0.01142  -0.0450   0.1115   1.0000
   6.500   1.0620   0.02065   0.01229  -0.0443   0.1029   1.0000
   6.750   1.0843   0.02131   0.01311  -0.0436   0.0956   1.0000
   7.000   1.1043   0.02240   0.01415  -0.0429   0.0877   1.0000
   7.250   1.1268   0.02255   0.01455  -0.0422   0.0788   1.0000
   7.500   1.1475   0.02308   0.01519  -0.0414   0.0678   1.0000
   7.750   1.1675   0.02366   0.01580  -0.0405   0.0548   1.0000
   8.000   1.1854   0.02463   0.01680  -0.0392   0.0454   1.0000
   8.250   1.1997   0.02609   0.01829  -0.0376   0.0400   1.0000
   8.500   1.2158   0.02737   0.01970  -0.0361   0.0364   1.0000
   8.750   1.2295   0.02883   0.02119  -0.0345   0.0338   1.0000
   9.000   1.2418   0.03090   0.02339  -0.0326   0.0317   1.0000
   9.250   1.2559   0.03231   0.02501  -0.0311   0.0297   1.0000
   9.500   1.2683   0.03390   0.02674  -0.0294   0.0281   1.0000
   9.750   1.2788   0.03566   0.02860  -0.0276   0.0270   1.0000
  10.000   1.2869   0.03789   0.03096  -0.0256   0.0261   1.0000
  10.250   1.2914   0.04158   0.03490  -0.0236   0.0253   1.0000
  10.500   1.2910   0.04440   0.03802  -0.0210   0.0250   1.0000
  10.750   1.2874   0.04705   0.04097  -0.0184   0.0248   1.0000
  11.000   1.2803   0.04998   0.04420  -0.0161   0.0245   1.0000
  11.250   1.2703   0.05330   0.04782  -0.0145   0.0243   1.0000
  11.500   1.2576   0.05710   0.05190  -0.0135   0.0241   1.0000
  11.750   1.2423   0.06150   0.05657  -0.0135   0.0239   1.0000
  12.000   1.2247   0.06659   0.06192  -0.0144   0.0238   1.0000
  12.250   1.2048   0.07246   0.06803  -0.0165   0.0239   1.0000
  12.500   1.1827   0.07918   0.07497  -0.0195   0.0240   1.0000
  12.750   1.1587   0.08680   0.08280  -0.0236   0.0242   1.0000
  13.000   1.1333   0.09537   0.09155  -0.0285   0.0245   1.0000
  13.250   1.1065   0.10495   0.10127  -0.0342   0.0249   1.0000
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