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NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M15 AIRFOIL (m15-il)
Reynolds number: 100,000
Max Cl/Cd: 53.08 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m15-il-100000-n5.txt
Download as CSV file: xf-m15-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3768   0.09778   0.09291  -0.0396   1.0000   0.0781
  -8.750  -0.3919   0.09417   0.08939  -0.0442   1.0000   0.0784
  -8.500  -0.4047   0.09102   0.08629  -0.0459   1.0000   0.0786
  -8.000  -0.3994   0.07608   0.07125  -0.0511   0.9860   0.0559
  -7.750  -0.3787   0.07282   0.06799  -0.0526   0.9750   0.0548
  -7.500  -0.3620   0.06824   0.06332  -0.0565   0.9610   0.0536
  -7.250  -0.3470   0.06316   0.05808  -0.0608   0.9461   0.0527
  -7.000  -0.3327   0.05828   0.05298  -0.0641   0.9313   0.0529
  -6.750  -0.3186   0.05375   0.04819  -0.0661   0.9171   0.0529
  -6.500  -0.3041   0.04946   0.04362  -0.0671   0.9039   0.0521
  -6.250  -0.2894   0.04521   0.03901  -0.0675   0.8917   0.0513
  -6.000  -0.2741   0.04120   0.03456  -0.0672   0.8802   0.0507
  -5.750  -0.2578   0.03783   0.03076  -0.0664   0.8682   0.0504
  -5.500  -0.2391   0.03498   0.02749  -0.0656   0.8580   0.0505
  -5.250  -0.2181   0.03290   0.02505  -0.0649   0.8486   0.0515
  -5.000  -0.1967   0.03095   0.02272  -0.0641   0.8384   0.0527
  -4.750  -0.1733   0.02903   0.02035  -0.0633   0.8306   0.0534
  -4.500  -0.1495   0.02735   0.01831  -0.0626   0.8208   0.0537
  -4.250  -0.1242   0.02586   0.01646  -0.0620   0.8130   0.0541
  -4.000  -0.0988   0.02461   0.01490  -0.0613   0.8029   0.0547
  -3.750  -0.0729   0.02351   0.01351  -0.0607   0.7932   0.0554
  -3.500  -0.0466   0.02255   0.01232  -0.0601   0.7838   0.0563
  -3.250  -0.0209   0.02180   0.01156  -0.0597   0.7742   0.0582
  -3.000   0.0055   0.02122   0.01088  -0.0593   0.7667   0.0605
  -2.750   0.0320   0.02062   0.01020  -0.0590   0.7583   0.0627
  -2.500   0.0586   0.01999   0.00946  -0.0585   0.7513   0.0645
  -2.250   0.0849   0.01947   0.00884  -0.0580   0.7435   0.0665
  -2.000   0.1105   0.01892   0.00832  -0.0575   0.7363   0.0693
  -1.750   0.1364   0.01854   0.00791  -0.0570   0.7292   0.0733
  -1.500   0.1623   0.01820   0.00754  -0.0565   0.7217   0.0803
  -1.250   0.1884   0.01788   0.00720  -0.0560   0.7152   0.0914
  -1.000   0.2141   0.01753   0.00693  -0.0556   0.7074   0.1097
  -0.750   0.2404   0.01715   0.00665  -0.0551   0.7013   0.1474
  -0.500   0.2661   0.01674   0.00658  -0.0549   0.6932   0.2291
  -0.250   0.3870   0.01498   0.00684  -0.0722   0.6860   1.0000
   0.000   0.4114   0.01505   0.00677  -0.0716   0.6778   1.0000
   0.250   0.4359   0.01510   0.00666  -0.0709   0.6705   1.0000
   0.500   0.4602   0.01519   0.00663  -0.0703   0.6626   1.0000
   0.750   0.4846   0.01527   0.00657  -0.0696   0.6550   1.0000
   1.000   0.5087   0.01537   0.00658  -0.0689   0.6470   1.0000
   1.250   0.5330   0.01546   0.00657  -0.0682   0.6391   1.0000
   1.500   0.5570   0.01558   0.00661  -0.0675   0.6311   1.0000
   1.750   0.5811   0.01569   0.00664  -0.0668   0.6229   1.0000
   2.000   0.6050   0.01583   0.00672  -0.0661   0.6146   1.0000
   2.250   0.6290   0.01596   0.00678  -0.0653   0.6063   1.0000
   2.500   0.6527   0.01611   0.00690  -0.0646   0.5978   1.0000
   2.750   0.6766   0.01625   0.00698  -0.0638   0.5895   1.0000
   3.000   0.7001   0.01642   0.00715  -0.0630   0.5805   1.0000
   3.250   0.7240   0.01656   0.00723  -0.0623   0.5725   1.0000
   3.500   0.7472   0.01676   0.00746  -0.0615   0.5632   1.0000
   3.750   0.7712   0.01691   0.00755  -0.0607   0.5557   1.0000
   4.000   0.7940   0.01714   0.00781  -0.0599   0.5461   1.0000
   4.250   0.8179   0.01730   0.00794  -0.0591   0.5386   1.0000
   4.500   0.8406   0.01755   0.00823  -0.0582   0.5293   1.0000
   4.750   0.8641   0.01775   0.00841  -0.0574   0.5216   1.0000
   5.000   0.8869   0.01799   0.00870  -0.0566   0.5129   1.0000
   5.250   0.9100   0.01822   0.00894  -0.0557   0.5050   1.0000
   5.500   0.9329   0.01848   0.00922  -0.0549   0.4968   1.0000
   5.750   0.9556   0.01874   0.00951  -0.0540   0.4883   1.0000
   6.000   0.9784   0.01895   0.00971  -0.0531   0.4791   1.0000
   6.250   1.0000   0.01924   0.01005  -0.0521   0.4684   1.0000
   6.500   1.0224   0.01951   0.01032  -0.0511   0.4592   1.0000
   6.750   1.0446   0.01984   0.01071  -0.0502   0.4504   1.0000
   7.000   1.0668   0.02020   0.01111  -0.0493   0.4422   1.0000
   7.250   1.0890   0.02055   0.01152  -0.0484   0.4340   1.0000
   7.500   1.1107   0.02095   0.01201  -0.0475   0.4258   1.0000
   7.750   1.1327   0.02134   0.01245  -0.0466   0.4177   1.0000
   8.000   1.1535   0.02178   0.01301  -0.0456   0.4090   1.0000
   8.250   1.1753   0.02219   0.01345  -0.0447   0.4007   1.0000
   8.500   1.1946   0.02268   0.01412  -0.0435   0.3910   1.0000
   8.750   1.2137   0.02310   0.01461  -0.0422   0.3800   1.0000
   9.000   1.2300   0.02353   0.01510  -0.0405   0.3656   1.0000
   9.250   1.2432   0.02400   0.01566  -0.0384   0.3478   1.0000
   9.500   1.2545   0.02454   0.01628  -0.0360   0.3285   1.0000
   9.750   1.2642   0.02517   0.01693  -0.0335   0.3089   1.0000
  10.000   1.2719   0.02592   0.01770  -0.0309   0.2887   1.0000
  10.250   1.2752   0.02681   0.01859  -0.0277   0.2671   1.0000
  10.500   1.2754   0.02796   0.01968  -0.0244   0.2451   1.0000
  10.750   1.2748   0.02941   0.02106  -0.0215   0.2215   1.0000
  11.000   1.2724   0.03118   0.02276  -0.0190   0.1990   1.0000
  11.250   1.2684   0.03329   0.02481  -0.0168   0.1775   1.0000
  11.500   1.2635   0.03571   0.02717  -0.0150   0.1570   1.0000
  11.750   1.2579   0.03839   0.02981  -0.0136   0.1356   1.0000
  12.000   1.2503   0.04145   0.03282  -0.0124   0.1137   1.0000
  12.250   1.2402   0.04492   0.03620  -0.0116   0.0949   1.0000
  12.500   1.2297   0.04861   0.03983  -0.0110   0.0819   1.0000
  12.750   1.2203   0.05232   0.04354  -0.0106   0.0726   1.0000
  13.000   1.2115   0.05609   0.04735  -0.0104   0.0662   1.0000
  13.250   1.2020   0.06004   0.05134  -0.0104   0.0613   1.0000
  13.500   1.1937   0.06399   0.05536  -0.0105   0.0573   1.0000
  13.750   1.1867   0.06791   0.05938  -0.0108   0.0536   1.0000
  14.000   1.1778   0.07220   0.06374  -0.0113   0.0509   1.0000
  14.250   1.1718   0.07619   0.06781  -0.0118   0.0482   1.0000
  14.500   1.1678   0.07998   0.07172  -0.0124   0.0457   1.0000
  14.750   1.1634   0.08387   0.07570  -0.0130   0.0437   1.0000
  15.000   1.1585   0.08783   0.07970  -0.0137   0.0420   1.0000
  15.250   1.1575   0.09120   0.08316  -0.0141   0.0402   1.0000
  15.500   1.1577   0.09449   0.08657  -0.0146   0.0383   1.0000
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