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NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M15 AIRFOIL (m15-il)
Reynolds number: 500,000
Max Cl/Cd: 101.57 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m15-il-500000.txt
Download as CSV file: xf-m15-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M15 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3788   0.08442   0.08225  -0.0356   1.0000   0.0344
  -8.500  -0.3782   0.08046   0.07834  -0.0389   0.9966   0.0352
  -8.250  -0.3863   0.06748   0.06515  -0.0589   0.9458   0.0378
  -8.000  -0.3971   0.05984   0.05731  -0.0610   0.9195   0.0382
  -7.750  -0.3897   0.05772   0.05511  -0.0599   0.8984   0.0385
  -7.500  -0.3796   0.05569   0.05298  -0.0592   0.8791   0.0389
  -7.250  -0.3676   0.05361   0.05078  -0.0588   0.8614   0.0393
  -7.000  -0.3540   0.05145   0.04849  -0.0587   0.8450   0.0400
  -6.750  -0.3254   0.02907   0.02551  -0.0601   0.8015   0.0453
  -6.500  -0.3115   0.02637   0.02275  -0.0596   0.7894   0.0458
  -6.250  -0.2945   0.02459   0.02088  -0.0590   0.7775   0.0463
  -6.000  -0.2766   0.02290   0.01910  -0.0586   0.7662   0.0469
  -5.750  -0.2584   0.02114   0.01719  -0.0580   0.7563   0.0479
  -5.500  -0.2402   0.01899   0.01484  -0.0574   0.7472   0.0500
  -5.250  -0.2285   0.01481   0.01005  -0.0559   0.7405   0.0545
  -5.000  -0.2316   0.01896   0.01254  -0.0526   0.7485   0.0386
  -4.750  -0.2058   0.01787   0.01121  -0.0521   0.7404   0.0384
  -4.500  -0.1795   0.01678   0.00993  -0.0518   0.7325   0.0384
  -4.250  -0.1531   0.01572   0.00871  -0.0515   0.7256   0.0388
  -4.000  -0.1261   0.01496   0.00791  -0.0514   0.7185   0.0395
  -3.750  -0.0990   0.01437   0.00720  -0.0512   0.7123   0.0400
  -3.500  -0.0715   0.01377   0.00653  -0.0511   0.7060   0.0405
  -3.250  -0.0441   0.01325   0.00595  -0.0509   0.6998   0.0410
  -3.000  -0.0168   0.01283   0.00545  -0.0507   0.6944   0.0416
  -2.750   0.0107   0.01241   0.00500  -0.0506   0.6887   0.0423
  -2.500   0.0381   0.01205   0.00459  -0.0504   0.6831   0.0430
  -2.250   0.0654   0.01177   0.00424  -0.0502   0.6778   0.0438
  -2.000   0.0932   0.01153   0.00399  -0.0502   0.6721   0.0448
  -1.750   0.1197   0.01107   0.00352  -0.0499   0.6669   0.0467
  -1.500   0.1470   0.01087   0.00328  -0.0497   0.6620   0.0485
  -1.250   0.1748   0.01066   0.00309  -0.0497   0.6564   0.0507
  -1.000   0.2027   0.01052   0.00291  -0.0496   0.6507   0.0531
  -0.750   0.2300   0.01033   0.00272  -0.0494   0.6456   0.0592
  -0.500   0.2576   0.01008   0.00258  -0.0493   0.6400   0.0798
  -0.250   0.2843   0.00978   0.00251  -0.0492   0.6343   0.1466
   0.000   0.3107   0.00949   0.00248  -0.0491   0.6288   0.2363
   0.250   0.3215   0.00760   0.00242  -0.0461   0.6232   0.7801
   0.500   0.3492   0.00751   0.00268  -0.0450   0.6173   0.9410
   0.750   0.3873   0.00772   0.00283  -0.0468   0.6110   0.9699
   1.000   0.4593   0.00800   0.00304  -0.0560   0.6024   0.9859
   1.250   0.5272   0.00819   0.00313  -0.0646   0.5942   0.9969
   1.500   0.5675   0.00821   0.00310  -0.0674   0.5857   1.0000
   1.750   0.5936   0.00823   0.00307  -0.0671   0.5778   1.0000
   2.000   0.6197   0.00824   0.00304  -0.0669   0.5690   1.0000
   2.250   0.6457   0.00826   0.00302  -0.0666   0.5600   1.0000
   2.500   0.6715   0.00831   0.00300  -0.0662   0.5503   1.0000
   2.750   0.6973   0.00834   0.00301  -0.0659   0.5392   1.0000
   3.000   0.7229   0.00839   0.00303  -0.0656   0.5285   1.0000
   3.250   0.7480   0.00848   0.00305  -0.0651   0.5172   1.0000
   3.500   0.7729   0.00857   0.00310  -0.0646   0.5054   1.0000
   3.750   0.7977   0.00867   0.00316  -0.0641   0.4934   1.0000
   4.000   0.8220   0.00880   0.00324  -0.0635   0.4814   1.0000
   4.250   0.8461   0.00897   0.00334  -0.0629   0.4698   1.0000
   4.500   0.8701   0.00912   0.00345  -0.0623   0.4593   1.0000
   4.750   0.8943   0.00927   0.00358  -0.0616   0.4506   1.0000
   5.000   0.9179   0.00946   0.00373  -0.0609   0.4425   1.0000
   5.250   0.9420   0.00961   0.00388  -0.0603   0.4356   1.0000
   5.500   0.9656   0.00979   0.00405  -0.0596   0.4287   1.0000
   5.750   0.9891   0.00998   0.00424  -0.0589   0.4223   1.0000
   6.000   1.0128   0.01014   0.00441  -0.0582   0.4152   1.0000
   6.250   1.0356   0.01038   0.00462  -0.0573   0.4088   1.0000
   6.500   1.0596   0.01051   0.00481  -0.0567   0.4027   1.0000
   6.750   1.0820   0.01076   0.00502  -0.0558   0.3944   1.0000
   7.000   1.1050   0.01091   0.00520  -0.0550   0.3824   1.0000
   7.250   1.1274   0.01110   0.00539  -0.0541   0.3693   1.0000
   7.500   1.1496   0.01132   0.00560  -0.0532   0.3569   1.0000
   7.750   1.1715   0.01157   0.00583  -0.0522   0.3447   1.0000
   8.000   1.1931   0.01183   0.00607  -0.0512   0.3296   1.0000
   8.250   1.2144   0.01212   0.00634  -0.0502   0.3134   1.0000
   8.500   1.2352   0.01246   0.00665  -0.0492   0.2951   1.0000
   8.750   1.2538   0.01294   0.00703  -0.0478   0.2719   1.0000
   9.000   1.2707   0.01355   0.00751  -0.0462   0.2430   1.0000
   9.250   1.2850   0.01431   0.00811  -0.0443   0.2110   1.0000
   9.500   1.2975   0.01517   0.00881  -0.0422   0.1806   1.0000
   9.750   1.3083   0.01610   0.00958  -0.0398   0.1526   1.0000
  10.000   1.3142   0.01723   0.01051  -0.0368   0.1172   1.0000
  10.250   1.3081   0.01877   0.01177  -0.0320   0.0761   1.0000
  10.500   1.3065   0.02029   0.01315  -0.0284   0.0542   1.0000
  10.750   1.3099   0.02169   0.01450  -0.0257   0.0437   1.0000
  11.000   1.3157   0.02305   0.01589  -0.0237   0.0376   1.0000
  11.250   1.3202   0.02461   0.01748  -0.0218   0.0337   1.0000
  11.500   1.3282   0.02602   0.01895  -0.0205   0.0311   1.0000
  11.750   1.3308   0.02795   0.02091  -0.0190   0.0290   1.0000
  12.000   1.3371   0.02967   0.02271  -0.0179   0.0276   1.0000
  12.250   1.3437   0.03141   0.02454  -0.0170   0.0262   1.0000
  12.500   1.3479   0.03345   0.02663  -0.0162   0.0250   1.0000
  12.750   1.3458   0.03616   0.02941  -0.0154   0.0240   1.0000
  13.000   1.3464   0.03868   0.03202  -0.0147   0.0233   1.0000
  13.250   1.3495   0.04099   0.03443  -0.0142   0.0227   1.0000
  13.500   1.3511   0.04350   0.03703  -0.0138   0.0220   1.0000
  13.750   1.3515   0.04616   0.03977  -0.0135   0.0214   1.0000
  14.000   1.3506   0.04901   0.04270  -0.0132   0.0209   1.0000
  14.250   1.3481   0.05210   0.04587  -0.0131   0.0205   1.0000
  14.500   1.3425   0.05561   0.04944  -0.0130   0.0200   1.0000
  14.750   1.3331   0.05961   0.05352  -0.0129   0.0196   1.0000
  15.000   1.3324   0.06273   0.05673  -0.0131   0.0193   1.0000
  15.250   1.3331   0.06574   0.05984  -0.0133   0.0189   1.0000
  15.500   1.3332   0.06888   0.06307  -0.0136   0.0185   1.0000
  15.750   1.3325   0.07214   0.06642  -0.0140   0.0181   1.0000
  16.000   1.3318   0.07545   0.06982  -0.0145   0.0177   1.0000
  16.250   1.3307   0.07883   0.07326  -0.0150   0.0174   1.0000
  16.500   1.3296   0.08223   0.07673  -0.0156   0.0171   1.0000
  16.750   1.3284   0.08563   0.08019  -0.0162   0.0168   1.0000
  17.000   1.3268   0.08904   0.08364  -0.0167   0.0165   1.0000
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