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NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M13 AIRFOIL (m13-il)
Reynolds number: 100,000
Max Cl/Cd: 56.83 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m13-il-100000-n5.txt
Download as CSV file: xf-m13-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M13 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4637   0.11811   0.11333   0.0018   1.0000   0.0308
  -8.750  -0.4605   0.11528   0.11055  -0.0010   1.0000   0.0309
  -8.500  -0.4571   0.11226   0.10759  -0.0038   1.0000   0.0310
  -8.250  -0.4531   0.10902   0.10440  -0.0067   1.0000   0.0310
  -8.000  -0.4480   0.10560   0.10102  -0.0098   1.0000   0.0311
  -7.750  -0.4405   0.10094   0.09641  -0.0112   1.0000   0.0313
  -7.500  -0.4312   0.09587   0.09134  -0.0074   1.0000   0.0324
  -7.250  -0.4236   0.09233   0.08779  -0.0088   1.0000   0.0332
  -7.000  -0.4146   0.08879   0.08427  -0.0113   1.0000   0.0342
  -6.750  -0.4043   0.08517   0.08068  -0.0144   1.0000   0.0354
  -6.500  -0.3915   0.08151   0.07702  -0.0185   1.0000   0.0377
  -6.250  -0.3644   0.07801   0.07339  -0.0306   1.0000   0.0401
  -6.000  -0.3634   0.07384   0.06936  -0.0255   1.0000   0.0428
  -5.750  -0.3466   0.07048   0.06597  -0.0285   1.0000   0.0472
  -5.500  -0.3151   0.06650   0.06177  -0.0376   1.0000   0.0502
  -5.250  -0.3088   0.06267   0.05805  -0.0353   1.0000   0.0520
  -5.000  -0.2925   0.05959   0.05494  -0.0363   1.0000   0.0557
  -4.500  -0.2556   0.05305   0.04824  -0.0398   1.0000   0.0636
  -4.250  -0.2112   0.04681   0.04148  -0.0461   0.9897   0.0493
  -4.000  -0.1781   0.04209   0.03659  -0.0497   0.9765   0.0445
  -3.750  -0.1387   0.03811   0.03222  -0.0536   0.9622   0.0473
  -3.500  -0.1011   0.03411   0.02781  -0.0566   0.9480   0.0463
  -3.250  -0.0642   0.03056   0.02377  -0.0589   0.9338   0.0464
  -3.000  -0.0279   0.02745   0.01999  -0.0604   0.9192   0.0492
  -2.750   0.0041   0.02506   0.01713  -0.0612   0.9040   0.0489
  -2.500   0.0345   0.02306   0.01466  -0.0614   0.8886   0.0491
  -2.250   0.0635   0.02143   0.01259  -0.0613   0.8733   0.0495
  -2.000   0.0906   0.02049   0.01145  -0.0611   0.8581   0.0519
  -1.750   0.1174   0.01985   0.01061  -0.0607   0.8434   0.0549
  -1.500   0.1446   0.01882   0.00931  -0.0602   0.8295   0.0550
  -1.250   0.1716   0.01794   0.00820  -0.0596   0.8160   0.0549
  -1.000   0.1983   0.01720   0.00730  -0.0590   0.8029   0.0552
  -0.750   0.2248   0.01658   0.00654  -0.0585   0.7905   0.0557
  -0.500   0.2510   0.01606   0.00593  -0.0579   0.7785   0.0565
  -0.250   0.2770   0.01563   0.00541  -0.0573   0.7669   0.0580
   0.000   0.3035   0.01531   0.00497  -0.0567   0.7550   0.0602
   0.250   0.3302   0.01508   0.00469  -0.0563   0.7433   0.0642
   0.500   0.3572   0.01493   0.00440  -0.0559   0.7320   0.0731
   0.750   0.3841   0.01477   0.00418  -0.0556   0.7214   0.0888
   1.000   0.4110   0.01468   0.00407  -0.0553   0.7106   0.1071
   1.250   0.4378   0.01446   0.00411  -0.0552   0.6993   0.1919
   1.750   0.4978   0.01285   0.00412  -0.0558   0.6783   1.0000
   2.000   0.5242   0.01301   0.00418  -0.0555   0.6676   1.0000
   2.250   0.5507   0.01318   0.00428  -0.0552   0.6566   1.0000
   2.500   0.5772   0.01336   0.00442  -0.0549   0.6460   1.0000
   2.750   0.6036   0.01354   0.00454  -0.0545   0.6360   1.0000
   3.000   0.6301   0.01373   0.00472  -0.0542   0.6249   1.0000
   3.250   0.6566   0.01393   0.00493  -0.0540   0.6139   1.0000
   3.500   0.6831   0.01413   0.00517  -0.0537   0.6032   1.0000
   3.750   0.7094   0.01434   0.00539  -0.0533   0.5928   1.0000
   4.000   0.7358   0.01456   0.00566  -0.0530   0.5813   1.0000
   4.250   0.7622   0.01478   0.00601  -0.0528   0.5695   1.0000
   4.500   0.7885   0.01502   0.00633  -0.0525   0.5580   1.0000
   4.750   0.8148   0.01527   0.00668  -0.0521   0.5469   1.0000
   5.000   0.8410   0.01552   0.00704  -0.0518   0.5362   1.0000
   5.250   0.8673   0.01580   0.00754  -0.0515   0.5243   1.0000
   5.500   0.8919   0.01593   0.00777  -0.0507   0.4979   1.0000
   5.750   0.9133   0.01607   0.00773  -0.0492   0.4377   1.0000
   6.000   0.9322   0.01679   0.00800  -0.0477   0.3265   1.0000
   6.250   0.9362   0.02041   0.00977  -0.0458   0.0613   1.0000
   6.500   0.9542   0.02204   0.01136  -0.0446   0.0375   1.0000
   6.750   0.9728   0.02344   0.01290  -0.0435   0.0318   1.0000
   7.000   0.9913   0.02473   0.01442  -0.0422   0.0283   1.0000
   7.250   1.0068   0.02625   0.01606  -0.0408   0.0247   1.0000
   7.500   1.0203   0.02801   0.01793  -0.0391   0.0230   1.0000
   7.750   1.0359   0.02965   0.01971  -0.0374   0.0221   1.0000
   8.000   1.0531   0.03148   0.02166  -0.0358   0.0212   1.0000
   8.250   1.0723   0.03337   0.02377  -0.0344   0.0198   1.0000
   8.500   1.0918   0.03532   0.02591  -0.0333   0.0181   1.0000
   8.750   1.1115   0.03768   0.02849  -0.0321   0.0172   1.0000
   9.000   1.1303   0.04039   0.03149  -0.0309   0.0167   1.0000
   9.250   1.1462   0.04336   0.03479  -0.0295   0.0164   1.0000
   9.500   1.1585   0.04655   0.03836  -0.0279   0.0162   1.0000
   9.750   1.1666   0.04993   0.04214  -0.0261   0.0161   1.0000
  10.000   1.1701   0.05341   0.04602  -0.0241   0.0161   1.0000
  10.250   1.1694   0.05678   0.04973  -0.0221   0.0158   1.0000
  10.500   1.1641   0.06005   0.05330  -0.0200   0.0156   1.0000
  10.750   1.1534   0.06321   0.05671  -0.0177   0.0154   1.0000
  11.000   1.1406   0.06673   0.06047  -0.0164   0.0153   1.0000
  11.250   1.1264   0.07071   0.06468  -0.0161   0.0152   1.0000
  11.500   1.1108   0.07522   0.06942  -0.0168   0.0152   1.0000
  11.750   1.0938   0.08040   0.07482  -0.0184   0.0152   1.0000
  12.000   1.0734   0.08669   0.08134  -0.0213   0.0156   1.0000
  12.250   1.0502   0.09424   0.08911  -0.0257   0.0160   1.0000
  12.500   1.0262   0.10300   0.09806  -0.0313   0.0166   1.0000
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