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NACA M16 AIRFOIL (m16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M16 AIRFOIL (m16-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.06 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m16-il-1000000.txt
Download as CSV file: xf-m16-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5169   0.10181   0.10047   0.0242   1.0000   0.0098
  -7.750  -0.5178   0.09886   0.09734   0.0233   0.8886   0.0098
  -7.500  -0.5144   0.09526   0.09360   0.0204   0.8511   0.0099
  -7.250  -0.5051   0.09102   0.08926   0.0164   0.8259   0.0099
  -7.000  -0.4933   0.08662   0.08476   0.0122   0.8050   0.0099
  -6.750  -0.4876   0.08137   0.07944   0.0099   0.7880   0.0103
  -6.500  -0.4731   0.07836   0.07634   0.0075   0.7712   0.0106
  -6.250  -0.4564   0.07510   0.07300   0.0046   0.7559   0.0110
  -6.000  -0.4380   0.07159   0.06941   0.0015   0.7422   0.0116
  -5.750  -0.4092   0.06751   0.06519  -0.0038   0.7300   0.0137
  -5.500  -0.3841   0.06323   0.06080  -0.0076   0.7187   0.0139
  -5.250  -0.3610   0.05880   0.05625  -0.0104   0.7086   0.0139
  -5.000  -0.3370   0.05405   0.05136  -0.0130   0.6997   0.0139
  -4.750  -0.3120   0.04902   0.04617  -0.0153   0.6910   0.0140
  -4.500  -0.2912   0.04350   0.04047  -0.0173   0.6835   0.0133
  -4.250  -0.2615   0.03782   0.03454  -0.0190   0.6763   0.0138
  -4.000  -0.2411   0.03958   0.03635  -0.0192   0.6672   0.0163
  -3.250  -0.1508   0.02242   0.01806  -0.0208   0.6497   0.0202
  -3.000  -0.1259   0.02451   0.02027  -0.0214   0.6422   0.0214
  -2.750  -0.0970   0.02678   0.02262  -0.0214   0.6348   0.0267
  -2.500  -0.0679   0.02436   0.01996  -0.0212   0.6292   0.0271
  -2.250  -0.0397   0.02164   0.01696  -0.0212   0.6235   0.0272
  -2.000  -0.0124   0.01579   0.01042  -0.0211   0.6189   0.0290
  -1.750   0.0152   0.01511   0.00967  -0.0213   0.6130   0.0303
  -1.500   0.0432   0.01455   0.00901  -0.0215   0.6069   0.0317
  -1.250   0.0715   0.01388   0.00820  -0.0216   0.6012   0.0334
  -1.000   0.1001   0.01308   0.00727  -0.0216   0.5954   0.0350
  -0.750   0.1290   0.01159   0.00553  -0.0215   0.5898   0.0334
  -0.500   0.1576   0.01080   0.00461  -0.0214   0.5842   0.0339
  -0.250   0.1860   0.01026   0.00399  -0.0215   0.5781   0.0342
   0.000   0.2144   0.00976   0.00342  -0.0215   0.5724   0.0339
   0.250   0.2426   0.00933   0.00295  -0.0215   0.5660   0.0336
   0.500   0.2708   0.00901   0.00258  -0.0216   0.5600   0.0336
   0.750   0.2991   0.00873   0.00228  -0.0216   0.5535   0.0339
   1.000   0.3274   0.00848   0.00198  -0.0217   0.5469   0.0335
   1.250   0.3558   0.00827   0.00176  -0.0218   0.5404   0.0336
   1.500   0.3843   0.00814   0.00159  -0.0220   0.5333   0.0344
   1.750   0.4128   0.00804   0.00148  -0.0221   0.5262   0.0362
   2.250   0.4698   0.00796   0.00138  -0.0225   0.5113   0.0392
   2.500   0.4984   0.00794   0.00133  -0.0227   0.5036   0.0422
   2.750   0.5269   0.00791   0.00133  -0.0229   0.4956   0.0502
   3.000   0.5431   0.00590   0.00151  -0.0208   0.4888   0.9536
   3.250   0.5818   0.00589   0.00151  -0.0233   0.4793   1.0000
   3.500   0.6095   0.00599   0.00157  -0.0233   0.4652   1.0000
   3.750   0.6373   0.00611   0.00163  -0.0234   0.4504   1.0000
   4.000   0.6652   0.00625   0.00171  -0.0236   0.4343   1.0000
   4.250   0.6931   0.00640   0.00180  -0.0237   0.4152   1.0000
   4.500   0.7209   0.00661   0.00194  -0.0239   0.3922   1.0000
   4.750   0.7485   0.00694   0.00211  -0.0242   0.3498   1.0000
   5.000   0.7715   0.00975   0.00340  -0.0255   0.0365   1.0000
   5.250   0.7987   0.01022   0.00381  -0.0256   0.0189   1.0000
   5.500   0.8259   0.01072   0.00441  -0.0257   0.0150   1.0000
   5.750   0.8532   0.01105   0.00478  -0.0258   0.0144   1.0000
   6.000   0.8801   0.01145   0.00522  -0.0259   0.0131   1.0000
   6.250   0.9069   0.01188   0.00568  -0.0260   0.0117   1.0000
   6.500   0.9328   0.01254   0.00641  -0.0260   0.0107   1.0000
   6.750   0.9555   0.01407   0.00812  -0.0258   0.0097   1.0000
   7.000   0.9806   0.01471   0.00882  -0.0257   0.0094   1.0000
   7.250   1.0055   0.01534   0.00949  -0.0256   0.0089   1.0000
   7.500   1.0288   0.01626   0.01049  -0.0252   0.0084   1.0000
   7.750   1.0514   0.01723   0.01152  -0.0248   0.0079   1.0000
   8.000   1.0748   0.01797   0.01229  -0.0246   0.0074   1.0000
   8.250   1.0969   0.01888   0.01327  -0.0242   0.0071   1.0000
   8.500   1.1178   0.02002   0.01448  -0.0236   0.0068   1.0000
   8.750   1.1377   0.02136   0.01587  -0.0229   0.0066   1.0000
   9.000   1.1559   0.02321   0.01780  -0.0219   0.0064   1.0000
   9.250   1.1716   0.02648   0.02124  -0.0206   0.0062   1.0000
   9.500   1.1887   0.02860   0.02363  -0.0195   0.0059   1.0000
   9.750   1.2067   0.03035   0.02559  -0.0185   0.0056   1.0000
  10.000   1.2186   0.03381   0.02937  -0.0170   0.0055   1.0000
  10.250   1.2159   0.04272   0.03897  -0.0131   0.0073   1.0000
  10.500   1.2199   0.04562   0.04208  -0.0117   0.0072   1.0000
  10.750   1.2200   0.04853   0.04519  -0.0101   0.0070   1.0000
  11.000   1.2155   0.05129   0.04812  -0.0083   0.0069   1.0000
  11.250   1.2038   0.05395   0.05091  -0.0063   0.0069   1.0000
  11.500   1.1914   0.05716   0.05427  -0.0057   0.0068   1.0000
  11.750   1.1783   0.06092   0.05817  -0.0060   0.0068   1.0000
  12.000   1.1641   0.06524   0.06262  -0.0072   0.0067   1.0000
  12.250   1.1482   0.07023   0.06775  -0.0091   0.0067   1.0000
  12.500   1.1304   0.07591   0.07358  -0.0118   0.0067   1.0000
  12.750   1.1115   0.08225   0.08006  -0.0151   0.0067   1.0000
  13.000   1.0893   0.08974   0.08770  -0.0192   0.0068   1.0000
  13.250   1.0652   0.09839   0.09649  -0.0244   0.0068   1.0000
  13.500   1.0366   0.10910   0.10735  -0.0311   0.0070   1.0000
  13.750   1.0045   0.12310   0.12148  -0.0399   0.0072   1.0000
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