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NACA M16 AIRFOIL (m16-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M16 AIRFOIL (m16-il)
Reynolds number: 200,000
Max Cl/Cd: 68.89 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m16-il-200000-n5.txt
Download as CSV file: xf-m16-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M16 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5290   0.13581   0.13262   0.0285   1.0000   0.0169
  -9.750  -0.5240   0.13248   0.12931   0.0264   1.0000   0.0169
  -9.500  -0.5191   0.12922   0.12608   0.0242   1.0000   0.0170
  -9.250  -0.5136   0.12585   0.12273   0.0221   1.0000   0.0170
  -9.000  -0.5076   0.12234   0.11925   0.0199   1.0000   0.0171
  -8.750  -0.5015   0.11866   0.11559   0.0179   1.0000   0.0171
  -8.500  -0.4954   0.11484   0.11181   0.0158   1.0000   0.0171
  -8.250  -0.4895   0.11097   0.10797   0.0135   1.0000   0.0171
  -7.750  -0.4756   0.10295   0.10000   0.0081   1.0000   0.0171
  -7.250  -0.4614   0.09289   0.08998   0.0059   1.0000   0.0165
  -7.000  -0.4548   0.08841   0.08553   0.0055   1.0000   0.0155
  -6.750  -0.4415   0.08411   0.08119   0.0015   0.9333   0.0148
  -6.500  -0.4303   0.08021   0.07717  -0.0013   0.8901   0.0144
  -6.250  -0.4179   0.07628   0.07313  -0.0040   0.8625   0.0141
  -6.000  -0.4022   0.07229   0.06902  -0.0071   0.8414   0.0145
  -5.750  -0.3822   0.06800   0.06458  -0.0109   0.8238   0.0156
  -5.500  -0.3601   0.06344   0.05985  -0.0146   0.8084   0.0160
  -5.250  -0.3382   0.05896   0.05519  -0.0174   0.7946   0.0160
  -5.000  -0.3132   0.05412   0.05012  -0.0204   0.7825   0.0163
  -4.750  -0.2855   0.04906   0.04480  -0.0229   0.7712   0.0169
  -4.500  -0.2657   0.04677   0.04239  -0.0237   0.7591   0.0187
  -4.250  -0.2433   0.04514   0.04062  -0.0243   0.7478   0.0208
  -4.000  -0.2159   0.04147   0.03669  -0.0257   0.7383   0.0217
  -3.750  -0.1874   0.03794   0.03283  -0.0267   0.7292   0.0234
  -3.500  -0.1552   0.03400   0.02847  -0.0275   0.7207   0.0267
  -3.250  -0.1251   0.02966   0.02360  -0.0278   0.7132   0.0291
  -3.000  -0.1021   0.02934   0.02327  -0.0283   0.7036   0.0323
  -2.750  -0.0740   0.02718   0.02077  -0.0284   0.6959   0.0351
  -2.500  -0.0448   0.02461   0.01777  -0.0284   0.6882   0.0361
  -2.250  -0.0154   0.02286   0.01557  -0.0282   0.6809   0.0388
  -2.000   0.0129   0.02095   0.01329  -0.0282   0.6735   0.0386
  -1.750   0.0414   0.01939   0.01136  -0.0281   0.6666   0.0387
  -1.500   0.0699   0.01821   0.00985  -0.0280   0.6592   0.0393
  -1.250   0.0983   0.01746   0.00881  -0.0279   0.6524   0.0400
  -1.000   0.1264   0.01629   0.00740  -0.0279   0.6453   0.0410
  -0.750   0.1542   0.01547   0.00641  -0.0279   0.6387   0.0418
  -0.500   0.1820   0.01496   0.00585  -0.0280   0.6315   0.0444
  -0.250   0.2097   0.01460   0.00540  -0.0280   0.6250   0.0464
   0.000   0.2376   0.01410   0.00483  -0.0279   0.6178   0.0460
   0.250   0.2652   0.01369   0.00435  -0.0278   0.6117   0.0456
   0.500   0.2930   0.01333   0.00396  -0.0278   0.6043   0.0453
   0.750   0.3205   0.01306   0.00363  -0.0277   0.5982   0.0451
   1.000   0.3484   0.01282   0.00340  -0.0277   0.5906   0.0451
   1.250   0.3760   0.01267   0.00320  -0.0277   0.5843   0.0453
   1.500   0.4041   0.01253   0.00306  -0.0278   0.5767   0.0458
   1.750   0.4319   0.01246   0.00294  -0.0278   0.5702   0.0466
   2.000   0.4600   0.01239   0.00288  -0.0279   0.5625   0.0481
   2.250   0.4878   0.01236   0.00282  -0.0279   0.5558   0.0508
   2.500   0.5159   0.01230   0.00284  -0.0280   0.5478   0.0632
   3.000   0.5764   0.01045   0.00303  -0.0291   0.5327   1.0000
   3.500   0.6310   0.01069   0.00324  -0.0290   0.5172   1.0000
   3.750   0.6582   0.01082   0.00339  -0.0290   0.5095   1.0000
   4.000   0.6856   0.01095   0.00356  -0.0290   0.5014   1.0000
   4.250   0.7129   0.01110   0.00375  -0.0290   0.4932   1.0000
   4.750   0.7670   0.01137   0.00408  -0.0289   0.4600   1.0000
   5.000   0.7938   0.01156   0.00425  -0.0288   0.4336   1.0000
   5.250   0.8198   0.01190   0.00444  -0.0287   0.3859   1.0000
   5.500   0.8432   0.01300   0.00494  -0.0288   0.2582   1.0000
   5.750   0.8596   0.01623   0.00684  -0.0293   0.0259   1.0000
   6.000   0.8846   0.01697   0.00773  -0.0291   0.0208   1.0000
   6.250   0.9090   0.01775   0.00868  -0.0289   0.0174   1.0000
   6.500   0.9320   0.01879   0.00991  -0.0286   0.0156   1.0000
   6.750   0.9513   0.02041   0.01171  -0.0280   0.0140   1.0000
   7.000   0.9706   0.02180   0.01324  -0.0273   0.0126   1.0000
   7.250   0.9901   0.02308   0.01463  -0.0265   0.0118   1.0000
   7.500   1.0082   0.02459   0.01623  -0.0255   0.0112   1.0000
   7.750   1.0263   0.02620   0.01794  -0.0243   0.0107   1.0000
   8.000   1.0450   0.02794   0.01978  -0.0231   0.0104   1.0000
   8.250   1.0645   0.02972   0.02168  -0.0220   0.0099   1.0000
   8.500   1.0833   0.03124   0.02330  -0.0213   0.0090   1.0000
   8.750   1.1001   0.03324   0.02543  -0.0205   0.0082   1.0000
   9.000   1.1165   0.03695   0.02936  -0.0194   0.0079   1.0000
   9.250   1.1316   0.03954   0.03225  -0.0182   0.0077   1.0000
   9.500   1.1440   0.04226   0.03530  -0.0169   0.0076   1.0000
   9.750   1.1529   0.04527   0.03864  -0.0155   0.0076   1.0000
  10.000   1.1577   0.04849   0.04219  -0.0139   0.0076   1.0000
  10.250   1.1582   0.05186   0.04587  -0.0123   0.0076   1.0000
  10.500   1.1530   0.05518   0.04946  -0.0104   0.0076   1.0000
  10.750   1.1431   0.05855   0.05305  -0.0087   0.0076   1.0000
  11.000   1.1318   0.06233   0.05705  -0.0081   0.0077   1.0000
  11.250   1.1192   0.06656   0.06148  -0.0082   0.0077   1.0000
  12.250   0.9451   0.07645   0.07210  -0.0011   0.0079   1.0000
  12.500   0.9266   0.08164   0.07744  -0.0026   0.0079   1.0000
  12.750   0.9078   0.08692   0.08286  -0.0044   0.0080   1.0000
  13.000   0.8881   0.09238   0.08846  -0.0065   0.0080   1.0000
  13.250   0.8684   0.09793   0.09416  -0.0091   0.0081   1.0000
  13.500   0.8455   0.10339   0.09975  -0.0117   0.0081   1.0000
  13.750   0.8223   0.10924   0.10574  -0.0149   0.0083   1.0000
  14.000   0.7987   0.11634   0.11297  -0.0191   0.0084   1.0000
  14.250   0.7673   0.12684   0.12361  -0.0252   0.0089   1.0000
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