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N-9 (n9-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 100,000
Max Cl/Cd: 51.57 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n9-il-100000-n5.txt
Download as CSV file: xf-n9-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4632   0.09003   0.08507  -0.0218   1.0000   0.0308
  -9.500  -0.4652   0.08580   0.08091  -0.0240   1.0000   0.0305
  -9.250  -0.4692   0.08141   0.07660  -0.0266   1.0000   0.0301
  -9.000  -0.4702   0.07614   0.07138  -0.0310   1.0000   0.0296
  -8.750  -0.4699   0.07021   0.06547  -0.0360   1.0000   0.0291
  -8.500  -0.4686   0.06361   0.05881  -0.0409   1.0000   0.0286
  -8.250  -0.4656   0.05689   0.05196  -0.0446   1.0000   0.0284
  -8.000  -0.4604   0.05030   0.04514  -0.0471   1.0000   0.0284
  -7.750  -0.4515   0.04500   0.03954  -0.0482   1.0000   0.0289
  -7.500  -0.4392   0.04088   0.03510  -0.0485   1.0000   0.0306
  -7.250  -0.4257   0.03614   0.02982  -0.0486   1.0000   0.0324
  -7.000  -0.4095   0.03160   0.02457  -0.0482   1.0000   0.0338
  -6.750  -0.3900   0.02822   0.02043  -0.0474   1.0000   0.0353
  -6.500  -0.3709   0.02674   0.01889  -0.0467   1.0000   0.0381
  -6.250  -0.3498   0.02538   0.01728  -0.0458   1.0000   0.0413
  -6.000  -0.3270   0.02351   0.01497  -0.0450   1.0000   0.0442
  -5.750  -0.3044   0.02224   0.01347  -0.0442   1.0000   0.0483
  -5.500  -0.2819   0.02142   0.01255  -0.0435   1.0000   0.0520
  -5.250  -0.2525   0.02046   0.01130  -0.0438   0.9979   0.0572
  -5.000  -0.2160   0.01952   0.01031  -0.0458   0.9929   0.0626
  -4.750  -0.1792   0.01867   0.00934  -0.0477   0.9873   0.0680
  -4.500  -0.1436   0.01802   0.00863  -0.0494   0.9805   0.0760
  -4.250  -0.1073   0.01737   0.00785  -0.0511   0.9740   0.0847
  -4.000  -0.0716   0.01666   0.00716  -0.0529   0.9669   0.0966
  -3.750  -0.0368   0.01606   0.00653  -0.0544   0.9587   0.1133
  -3.500   0.0009   0.01541   0.00606  -0.0567   0.9527   0.1424
  -3.250   0.0351   0.01489   0.00584  -0.0582   0.9439   0.2062
  -3.000   0.0711   0.01410   0.00556  -0.0602   0.9371   0.3291
  -2.750   0.1035   0.01317   0.00543  -0.0611   0.9279   0.5504
  -2.500   0.1321   0.01232   0.00536  -0.0599   0.9178   0.7913
  -2.250   0.1914   0.01195   0.00499  -0.0654   0.9085   1.0000
  -2.000   0.2260   0.01191   0.00475  -0.0664   0.8918   1.0000
  -1.750   0.2572   0.01189   0.00455  -0.0667   0.8731   1.0000
  -1.500   0.2866   0.01190   0.00441  -0.0667   0.8553   1.0000
  -1.250   0.3144   0.01194   0.00433  -0.0664   0.8387   1.0000
  -1.000   0.3410   0.01200   0.00428  -0.0660   0.8212   1.0000
  -0.750   0.3681   0.01204   0.00423  -0.0656   0.8042   1.0000
  -0.500   0.3956   0.01209   0.00418  -0.0653   0.7877   1.0000
  -0.250   0.4234   0.01214   0.00413  -0.0650   0.7715   1.0000
   0.000   0.4511   0.01220   0.00410  -0.0646   0.7557   1.0000
   0.250   0.4786   0.01229   0.00409  -0.0643   0.7398   1.0000
   0.500   0.5058   0.01242   0.00413  -0.0639   0.7239   1.0000
   0.750   0.5325   0.01257   0.00421  -0.0634   0.7070   1.0000
   1.000   0.5585   0.01275   0.00431  -0.0628   0.6872   1.0000
   1.250   0.5842   0.01294   0.00442  -0.0621   0.6650   1.0000
   1.500   0.6093   0.01313   0.00455  -0.0614   0.6400   1.0000
   1.750   0.6343   0.01334   0.00469  -0.0606   0.6142   1.0000
   2.000   0.6593   0.01354   0.00485  -0.0599   0.5877   1.0000
   2.250   0.6840   0.01376   0.00502  -0.0592   0.5563   1.0000
   2.500   0.7084   0.01401   0.00518  -0.0584   0.5209   1.0000
   2.750   0.7327   0.01431   0.00539  -0.0576   0.4874   1.0000
   3.000   0.7565   0.01468   0.00562  -0.0568   0.4539   1.0000
   3.250   0.7798   0.01512   0.00591  -0.0560   0.4199   1.0000
   3.500   0.8032   0.01559   0.00628  -0.0553   0.3915   1.0000
   3.750   0.8264   0.01608   0.00668  -0.0546   0.3647   1.0000
   4.000   0.8500   0.01656   0.00712  -0.0539   0.3405   1.0000
   4.250   0.8734   0.01704   0.00759  -0.0533   0.3152   1.0000
   4.500   0.8962   0.01757   0.00811  -0.0526   0.2836   1.0000
   4.750   0.9185   0.01816   0.00862  -0.0518   0.2412   1.0000
   5.000   0.9391   0.01895   0.00920  -0.0509   0.1905   1.0000
   5.250   0.9592   0.01988   0.00991  -0.0500   0.1598   1.0000
   5.500   0.9796   0.02077   0.01076  -0.0491   0.1447   1.0000
   6.000   1.0205   0.02251   0.01257  -0.0472   0.1287   1.0000
   6.250   1.0397   0.02350   0.01359  -0.0461   0.1224   1.0000
   6.500   1.0597   0.02443   0.01463  -0.0451   0.1167   1.0000
   6.750   1.0798   0.02538   0.01574  -0.0442   0.1113   1.0000
   7.000   1.0980   0.02664   0.01696  -0.0431   0.1056   1.0000
   7.250   1.1179   0.02735   0.01792  -0.0423   0.0960   1.0000
   7.500   1.1361   0.02817   0.01889  -0.0414   0.0863   1.0000
   7.750   1.1534   0.02897   0.01977  -0.0404   0.0774   1.0000
   8.000   1.1730   0.02957   0.02065  -0.0396   0.0672   1.0000
   8.250   1.1908   0.03037   0.02164  -0.0385   0.0562   1.0000
   8.500   1.2060   0.03140   0.02279  -0.0373   0.0450   1.0000
   8.750   1.2172   0.03286   0.02429  -0.0355   0.0372   1.0000
   9.000   1.2248   0.03455   0.02599  -0.0334   0.0329   1.0000
   9.250   1.2314   0.03623   0.02787  -0.0311   0.0294   1.0000
   9.500   1.2356   0.03794   0.02968  -0.0289   0.0269   1.0000
   9.750   1.2373   0.04002   0.03187  -0.0266   0.0252   1.0000
  10.000   1.2398   0.04222   0.03430  -0.0246   0.0239   1.0000
  10.250   1.2407   0.04464   0.03694  -0.0229   0.0228   1.0000
  10.500   1.2403   0.04727   0.03978  -0.0214   0.0220   1.0000
  10.750   1.2384   0.05010   0.04281  -0.0203   0.0213   1.0000
  11.000   1.2349   0.05318   0.04608  -0.0197   0.0206   1.0000
  11.250   1.2294   0.05662   0.04968  -0.0195   0.0199   1.0000
  11.500   1.2220   0.06051   0.05374  -0.0198   0.0195   1.0000
  11.750   1.2120   0.06496   0.05836  -0.0206   0.0190   1.0000
  12.000   1.2005   0.06991   0.06350  -0.0219   0.0187   1.0000
  12.250   1.1883   0.07526   0.06910  -0.0237   0.0185   1.0000
  12.500   1.1740   0.08124   0.07533  -0.0263   0.0184   1.0000
  12.750   1.1580   0.08786   0.08217  -0.0295   0.0184   1.0000
  13.000   1.1401   0.09520   0.08972  -0.0333   0.0184   1.0000
  13.250   1.1212   0.10325   0.09795  -0.0378   0.0185   1.0000
  13.500   1.1015   0.11194   0.10680  -0.0427   0.0186   1.0000
  13.750   1.0809   0.12124   0.11624  -0.0479   0.0188   1.0000
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