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NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M15 AIRFOIL (m15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.75 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m15-il-1000000.txt
Download as CSV file: xf-m15-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3987   0.08713   0.08555  -0.0324   0.9780   0.0243
  -9.000  -0.3973   0.08336   0.08171  -0.0346   0.9346   0.0249
  -8.000  -0.5009   0.03326   0.03005  -0.0575   0.8334   0.0273
  -7.750  -0.4883   0.03046   0.02700  -0.0566   0.8182   0.0276
  -7.500  -0.4761   0.02668   0.02283  -0.0550   0.8038   0.0264
  -7.250  -0.4636   0.02309   0.01873  -0.0534   0.7895   0.0264
  -7.000  -0.4434   0.02133   0.01662  -0.0525   0.7749   0.0266
  -6.500  -0.4014   0.01767   0.01227  -0.0507   0.7474   0.0274
  -6.250  -0.3770   0.01653   0.01097  -0.0503   0.7355   0.0277
  -6.000  -0.3515   0.01572   0.01002  -0.0500   0.7246   0.0280
  -5.750  -0.3254   0.01505   0.00922  -0.0497   0.7140   0.0282
  -5.500  -0.2988   0.01442   0.00848  -0.0495   0.7048   0.0285
  -5.250  -0.2721   0.01385   0.00780  -0.0493   0.6965   0.0287
  -5.000  -0.2450   0.01331   0.00717  -0.0492   0.6897   0.0290
  -4.750  -0.2178   0.01282   0.00661  -0.0491   0.6830   0.0293
  -4.500  -0.1905   0.01237   0.00608  -0.0489   0.6770   0.0297
  -4.250  -0.1630   0.01194   0.00559  -0.0488   0.6711   0.0301
  -4.000  -0.1354   0.01161   0.00519  -0.0487   0.6656   0.0306
  -3.750  -0.1076   0.01133   0.00486  -0.0487   0.6608   0.0311
  -3.500  -0.0798   0.01102   0.00451  -0.0486   0.6559   0.0315
  -3.250  -0.0520   0.01076   0.00421  -0.0486   0.6507   0.0318
  -3.000  -0.0242   0.01055   0.00394  -0.0485   0.6458   0.0320
  -2.750   0.0024   0.00996   0.00333  -0.0483   0.6418   0.0327
  -2.500   0.0299   0.00965   0.00300  -0.0482   0.6373   0.0333
  -2.250   0.0576   0.00945   0.00277  -0.0481   0.6326   0.0341
  -2.000   0.0857   0.00929   0.00259  -0.0481   0.6281   0.0349
  -1.750   0.1139   0.00912   0.00242  -0.0482   0.6236   0.0358
  -1.500   0.1422   0.00899   0.00228  -0.0482   0.6191   0.0369
  -1.250   0.1704   0.00893   0.00217  -0.0482   0.6142   0.0378
  -1.000   0.1986   0.00872   0.00197  -0.0483   0.6099   0.0400
  -0.750   0.2269   0.00860   0.00186  -0.0483   0.6048   0.0423
  -0.500   0.2552   0.00853   0.00176  -0.0484   0.5998   0.0454
  -0.250   0.2833   0.00837   0.00168  -0.0484   0.5950   0.0624
   0.000   0.3111   0.00815   0.00164  -0.0485   0.5895   0.1111
   0.250   0.3389   0.00802   0.00161  -0.0485   0.5836   0.1526
   0.500   0.3664   0.00779   0.00161  -0.0486   0.5781   0.2319
   0.750   0.3866   0.00658   0.00156  -0.0476   0.5720   0.6331
   1.000   0.4017   0.00582   0.00168  -0.0445   0.5657   0.9159
   1.250   0.4285   0.00586   0.00177  -0.0439   0.5585   0.9516
   1.500   0.4573   0.00598   0.00185  -0.0438   0.5503   0.9707
   1.750   0.4947   0.00612   0.00196  -0.0457   0.5409   0.9809
   2.000   0.5431   0.00630   0.00207  -0.0502   0.5290   0.9854
   2.250   0.5883   0.00647   0.00216  -0.0540   0.5156   0.9890
   2.500   0.6265   0.00662   0.00223  -0.0563   0.5012   0.9925
   2.750   0.6872   0.00685   0.00236  -0.0636   0.4836   0.9976
   3.000   0.7281   0.00700   0.00242  -0.0666   0.4677   0.9999
   3.250   0.7551   0.00712   0.00247  -0.0666   0.4543   1.0000
   3.500   0.7808   0.00723   0.00253  -0.0664   0.4430   1.0000
   3.750   0.8065   0.00733   0.00258  -0.0661   0.4334   1.0000
   4.000   0.8319   0.00745   0.00266  -0.0657   0.4243   1.0000
   4.250   0.8574   0.00753   0.00272  -0.0654   0.4177   1.0000
   4.500   0.8822   0.00765   0.00281  -0.0649   0.4112   1.0000
   4.750   0.9071   0.00773   0.00290  -0.0644   0.4058   1.0000
   5.000   0.9317   0.00784   0.00300  -0.0639   0.3997   1.0000
   5.250   0.9557   0.00798   0.00312  -0.0633   0.3932   1.0000
   5.500   0.9805   0.00806   0.00321  -0.0628   0.3883   1.0000
   5.750   1.0046   0.00818   0.00333  -0.0621   0.3828   1.0000
   6.000   1.0283   0.00833   0.00347  -0.0615   0.3768   1.0000
   6.250   1.0521   0.00846   0.00358  -0.0608   0.3663   1.0000
   6.500   1.0753   0.00862   0.00371  -0.0600   0.3530   1.0000
   6.750   1.0983   0.00881   0.00386  -0.0592   0.3408   1.0000
   7.000   1.1209   0.00901   0.00403  -0.0584   0.3283   1.0000
   7.250   1.1432   0.00924   0.00421  -0.0575   0.3146   1.0000
   7.500   1.1650   0.00951   0.00442  -0.0565   0.2972   1.0000
   7.750   1.1857   0.00985   0.00467  -0.0553   0.2756   1.0000
   8.000   1.2052   0.01028   0.00498  -0.0540   0.2513   1.0000
   8.250   1.2231   0.01081   0.00536  -0.0525   0.2230   1.0000
   8.500   1.2398   0.01141   0.00582  -0.0507   0.1938   1.0000
   8.750   1.2562   0.01204   0.00630  -0.0490   0.1682   1.0000
   9.000   1.2728   0.01267   0.00680  -0.0473   0.1448   1.0000
   9.250   1.2873   0.01344   0.00740  -0.0454   0.1159   1.0000
   9.500   1.2959   0.01456   0.00826  -0.0426   0.0753   1.0000
   9.750   1.3064   0.01552   0.00907  -0.0402   0.0526   1.0000
  10.000   1.3185   0.01630   0.00978  -0.0380   0.0406   1.0000
  10.250   1.3291   0.01699   0.01045  -0.0354   0.0332   1.0000
  10.500   1.3390   0.01773   0.01119  -0.0329   0.0282   1.0000
  10.750   1.3506   0.01848   0.01194  -0.0308   0.0251   1.0000
  11.000   1.3624   0.01929   0.01277  -0.0290   0.0228   1.0000
  11.250   1.3745   0.02014   0.01365  -0.0274   0.0212   1.0000
  11.500   1.3830   0.02129   0.01483  -0.0255   0.0196   1.0000
  11.750   1.3959   0.02221   0.01581  -0.0243   0.0188   1.0000
  12.000   1.4073   0.02327   0.01693  -0.0231   0.0180   1.0000
  12.250   1.4173   0.02451   0.01821  -0.0220   0.0173   1.0000
  12.500   1.4242   0.02607   0.01981  -0.0208   0.0165   1.0000
  12.750   1.4289   0.02788   0.02170  -0.0196   0.0159   1.0000
  13.000   1.4389   0.02930   0.02320  -0.0189   0.0155   1.0000
  13.250   1.4473   0.03090   0.02485  -0.0182   0.0150   1.0000
  13.500   1.4543   0.03267   0.02669  -0.0175   0.0145   1.0000
  13.750   1.4601   0.03461   0.02870  -0.0170   0.0142   1.0000
  14.000   1.4633   0.03683   0.03098  -0.0164   0.0138   1.0000
  14.250   1.4631   0.03945   0.03367  -0.0158   0.0134   1.0000
  14.500   1.4578   0.04265   0.03696  -0.0153   0.0131   1.0000
  14.750   1.4542   0.04572   0.04013  -0.0149   0.0129   1.0000
  15.000   1.4564   0.04826   0.04275  -0.0148   0.0127   1.0000
  15.250   1.4574   0.05099   0.04557  -0.0147   0.0125   1.0000
  15.500   1.4571   0.05390   0.04856  -0.0147   0.0123   1.0000
  15.750   1.4555   0.05706   0.05180  -0.0148   0.0121   1.0000
  16.000   1.4534   0.06036   0.05518  -0.0151   0.0119   1.0000
  16.250   1.4509   0.06375   0.05866  -0.0154   0.0117   1.0000
  16.500   1.4475   0.06734   0.06233  -0.0159   0.0115   1.0000
  16.750   1.4433   0.07109   0.06617  -0.0165   0.0114   1.0000
  17.000   1.4391   0.07495   0.07010  -0.0172   0.0112   1.0000
  17.250   1.4339   0.07895   0.07418  -0.0180   0.0110   1.0000
  17.500   1.4273   0.08319   0.07851  -0.0189   0.0109   1.0000
  17.750   1.4187   0.08778   0.08318  -0.0200   0.0107   1.0000
  18.000   1.4082   0.09270   0.08818  -0.0212   0.0106   1.0000
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