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NACA M17 AIRFOIL (m17-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M17 AIRFOIL (m17-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.84 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m17-il-1000000-n5.txt
Download as CSV file: xf-m17-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M17 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5279   0.08939   0.08716   0.0072   0.7182   0.0067
  -8.250  -0.5333   0.08299   0.08072   0.0014   0.7099   0.0072
  -8.000  -0.5368   0.07380   0.07147  -0.0067   0.7028   0.0079
  -7.750  -0.5230   0.07032   0.06792  -0.0096   0.6935   0.0081
  -7.250  -0.5652   0.01902   0.01460  -0.0244   0.6929   0.0146
  -7.000  -0.5329   0.02110   0.01688  -0.0248   0.6823   0.0147
  -6.750  -0.4630   0.04943   0.04652  -0.0225   0.6624   0.0109
  -6.250  -0.4364   0.03003   0.02627  -0.0258   0.6520   0.0147
  -6.000  -0.4112   0.02902   0.02513  -0.0258   0.6440   0.0150
  -5.750  -0.3855   0.02835   0.02439  -0.0259   0.6371   0.0154
  -5.500  -0.3736   0.01805   0.01310  -0.0243   0.6327   0.0187
  -5.250  -0.3472   0.01731   0.01217  -0.0241   0.6259   0.0193
  -5.000  -0.3198   0.01702   0.01179  -0.0241   0.6191   0.0196
  -4.750  -0.2923   0.01676   0.01142  -0.0240   0.6127   0.0198
  -4.500  -0.2681   0.01479   0.00914  -0.0237   0.6072   0.0208
  -4.250  -0.2407   0.01443   0.00870  -0.0237   0.6008   0.0212
  -4.000  -0.2132   0.01403   0.00821  -0.0237   0.5952   0.0216
  -3.750  -0.1856   0.01366   0.00776  -0.0237   0.5897   0.0220
  -3.500  -0.1579   0.01337   0.00738  -0.0237   0.5839   0.0225
  -3.250  -0.1303   0.01290   0.00680  -0.0237   0.5786   0.0230
  -3.000  -0.1025   0.01241   0.00621  -0.0236   0.5728   0.0234
  -2.500  -0.0469   0.01148   0.00508  -0.0236   0.5627   0.0241
  -2.250  -0.0191   0.01105   0.00457  -0.0236   0.5570   0.0243
  -2.000   0.0088   0.01066   0.00410  -0.0235   0.5518   0.0245
  -1.750   0.0366   0.01028   0.00367  -0.0235   0.5467   0.0246
  -1.500   0.0645   0.00996   0.00327  -0.0235   0.5416   0.0248
  -1.250   0.0924   0.00971   0.00299  -0.0235   0.5367   0.0252
  -1.000   0.1203   0.00945   0.00268  -0.0235   0.5314   0.0254
  -0.750   0.1481   0.00920   0.00238  -0.0234   0.5259   0.0255
  -0.500   0.1760   0.00899   0.00213  -0.0234   0.5213   0.0257
  -0.250   0.2040   0.00881   0.00193  -0.0235   0.5164   0.0260
   0.000   0.2320   0.00868   0.00176  -0.0235   0.5111   0.0264
   0.250   0.2602   0.00858   0.00164  -0.0236   0.5061   0.0269
   0.500   0.2885   0.00851   0.00157  -0.0237   0.5008   0.0273
   0.750   0.3167   0.00847   0.00151  -0.0238   0.4959   0.0277
   1.000   0.3449   0.00837   0.00140  -0.0239   0.4913   0.0285
   1.250   0.3731   0.00829   0.00130  -0.0240   0.4859   0.0296
   1.500   0.4014   0.00826   0.00124  -0.0241   0.4807   0.0305
   1.750   0.4298   0.00822   0.00121  -0.0242   0.4762   0.0313
   2.000   0.4581   0.00821   0.00120  -0.0244   0.4706   0.0321
   2.250   0.4864   0.00823   0.00120  -0.0245   0.4644   0.0332
   2.500   0.5147   0.00822   0.00121  -0.0247   0.4573   0.0351
   2.750   0.5429   0.00826   0.00124  -0.0248   0.4493   0.0381
   3.000   0.5709   0.00821   0.00130  -0.0250   0.4399   0.0888
   3.250   0.5986   0.00811   0.00140  -0.0251   0.4307   0.1895
   3.500   0.6114   0.00634   0.00155  -0.0222   0.4238   0.9491
   3.750   0.6483   0.00644   0.00168  -0.0242   0.4173   0.9832
   4.000   0.6925   0.00660   0.00182  -0.0280   0.4088   0.9937
   4.250   0.7361   0.00672   0.00194  -0.0317   0.4020   0.9972
   4.500   0.7787   0.00689   0.00208  -0.0353   0.3915   1.0000
   4.750   0.8046   0.00704   0.00218  -0.0350   0.3743   1.0000
   5.000   0.8303   0.00723   0.00231  -0.0348   0.3540   1.0000
   5.250   0.8557   0.00748   0.00246  -0.0345   0.3293   1.0000
   5.500   0.8796   0.00806   0.00277  -0.0342   0.2719   1.0000
   5.750   0.9020   0.00893   0.00326  -0.0339   0.1972   1.0000
   6.000   0.9248   0.00958   0.00368  -0.0334   0.1516   1.0000
   6.250   0.9439   0.01087   0.00447  -0.0327   0.0561   1.0000
   6.500   0.9658   0.01155   0.00499  -0.0320   0.0237   1.0000
   6.750   0.9893   0.01192   0.00533  -0.0315   0.0165   1.0000
   7.000   1.0128   0.01229   0.00570  -0.0309   0.0128   1.0000
   7.250   1.0366   0.01259   0.00603  -0.0304   0.0117   1.0000
   7.500   1.0602   0.01293   0.00639  -0.0299   0.0106   1.0000
   7.750   1.0832   0.01333   0.00680  -0.0294   0.0094   1.0000
   8.000   1.1056   0.01379   0.00731  -0.0287   0.0084   1.0000
   8.250   1.1287   0.01416   0.00770  -0.0282   0.0078   1.0000
   8.500   1.1515   0.01456   0.00813  -0.0276   0.0072   1.0000
   8.750   1.1739   0.01501   0.00861  -0.0271   0.0067   1.0000
   9.000   1.1955   0.01553   0.00915  -0.0265   0.0062   1.0000
   9.250   1.2157   0.01621   0.00989  -0.0257   0.0057   1.0000
   9.500   1.2370   0.01674   0.01048  -0.0250   0.0055   1.0000
   9.750   1.2575   0.01732   0.01112  -0.0243   0.0053   1.0000
  10.000   1.2773   0.01794   0.01180  -0.0236   0.0050   1.0000
  10.250   1.2967   0.01857   0.01248  -0.0228   0.0048   1.0000
  10.500   1.3154   0.01921   0.01316  -0.0220   0.0045   1.0000
  10.750   1.3331   0.01990   0.01388  -0.0210   0.0043   1.0000
  11.000   1.3483   0.02074   0.01479  -0.0199   0.0041   1.0000
  11.250   1.3570   0.02191   0.01605  -0.0179   0.0039   1.0000
  11.500   1.3633   0.02305   0.01728  -0.0158   0.0038   1.0000
  11.750   1.3716   0.02432   0.01863  -0.0146   0.0037   1.0000
  12.000   1.3798   0.02579   0.02019  -0.0137   0.0036   1.0000
  12.250   1.3875   0.02744   0.02193  -0.0131   0.0035   1.0000
  12.500   1.3943   0.02928   0.02387  -0.0127   0.0035   1.0000
  12.750   1.4003   0.03127   0.02595  -0.0124   0.0034   1.0000
  13.000   1.4052   0.03343   0.02821  -0.0122   0.0033   1.0000
  13.250   1.4092   0.03572   0.03059  -0.0120   0.0032   1.0000
  13.500   1.4124   0.03814   0.03310  -0.0119   0.0032   1.0000
  13.750   1.4148   0.04065   0.03573  -0.0119   0.0031   1.0000
  14.000   1.4160   0.04334   0.03851  -0.0119   0.0030   1.0000
  14.250   1.4165   0.04612   0.04139  -0.0120   0.0030   1.0000
  14.500   1.4160   0.04905   0.04440  -0.0122   0.0029   1.0000
  14.750   1.4145   0.05214   0.04759  -0.0124   0.0029   1.0000
  15.000   1.4125   0.05531   0.05086  -0.0128   0.0028   1.0000
  15.250   1.4096   0.05868   0.05432  -0.0132   0.0028   1.0000
  15.500   1.4065   0.06224   0.05798  -0.0139   0.0028   1.0000
  15.750   1.4030   0.06593   0.06177  -0.0147   0.0027   1.0000
  16.000   1.3984   0.06986   0.06579  -0.0156   0.0027   1.0000
  16.250   1.3930   0.07401   0.07004  -0.0167   0.0027   1.0000
  16.500   1.3868   0.07836   0.07450  -0.0179   0.0026   1.0000
  16.750   1.3790   0.08301   0.07926  -0.0193   0.0026   1.0000
  17.000   1.3703   0.08795   0.08430  -0.0208   0.0026   1.0000
  17.250   1.3607   0.09311   0.08958  -0.0226   0.0025   1.0000
  17.500   1.3497   0.09858   0.09516  -0.0245   0.0025   1.0000
  17.750   1.3378   0.10433   0.10102  -0.0266   0.0025   1.0000
  18.000   1.3253   0.11032   0.10714  -0.0290   0.0025   1.0000
  18.250   1.3118   0.11660   0.11354  -0.0315   0.0024   1.0000
  18.500   1.2975   0.12320   0.12026  -0.0344   0.0024   1.0000
  18.750   1.2827   0.13008   0.12726  -0.0375   0.0024   1.0000
  19.000   1.2680   0.13717   0.13449  -0.0410   0.0024   1.0000
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