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MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MILEY M06-13-128 (miley-il)
Reynolds number: 1,000,000
Max Cl/Cd: 157.64 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-miley-il-1000000-n5.txt
Download as CSV file: xf-miley-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MILEY M06-13-128                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2546   0.08641   0.08307  -0.0170   0.5166   0.0046
  -7.500  -0.2528   0.08303   0.07972  -0.0186   0.5165   0.0047
  -7.250  -0.2517   0.07989   0.07661  -0.0200   0.5164   0.0047
  -7.000  -0.2549   0.07685   0.07361  -0.0213   0.5162   0.0047
  -6.750  -0.2538   0.07339   0.07017  -0.0239   0.5161   0.0047
  -6.500  -0.2478   0.06945   0.06623  -0.0273   0.5159   0.0047
  -6.250  -0.2391   0.06549   0.06225  -0.0304   0.5157   0.0047
  -6.000  -0.2281   0.06140   0.05813  -0.0333   0.5155   0.0047
  -5.000  -0.1736   0.04194   0.03820  -0.0408   0.5147   0.0026
  -4.750  -0.1550   0.03753   0.03360  -0.0412   0.5143   0.0025
  -4.500  -0.1351   0.03326   0.02910  -0.0409   0.5140   0.0024
  -4.250  -0.1148   0.02871   0.02424  -0.0400   0.5136   0.0024
  -4.000  -0.0953   0.02304   0.01808  -0.0380   0.5133   0.0024
  -3.750  -0.0795   0.01476   0.00875  -0.0341   0.5131   0.0030
  -3.500  -0.0529   0.01394   0.00778  -0.0337   0.5127   0.0032
  -3.250  -0.0257   0.01346   0.00720  -0.0335   0.5124   0.0033
  -3.000   0.0013   0.01288   0.00652  -0.0332   0.5120   0.0036
  -2.750   0.0281   0.01225   0.00577  -0.0329   0.5116   0.0037
  -2.500   0.0550   0.01172   0.00514  -0.0325   0.5113   0.0039
  -2.250   0.0822   0.01134   0.00470  -0.0323   0.5109   0.0041
  -2.000   0.1094   0.01101   0.00430  -0.0320   0.5105   0.0044
  -1.750   0.1373   0.01083   0.00409  -0.0320   0.5101   0.0047
  -1.500   0.1642   0.01043   0.00362  -0.0316   0.5096   0.0050
  -1.250   0.1917   0.01016   0.00330  -0.0314   0.5091   0.0053
  -1.000   0.2195   0.00998   0.00310  -0.0313   0.5087   0.0059
  -0.750   0.2475   0.00984   0.00294  -0.0313   0.5083   0.0072
  -0.500   0.2756   0.00974   0.00285  -0.0313   0.5079   0.0102
  -0.250   0.3038   0.00967   0.00276  -0.0313   0.5075   0.0126
   0.000   0.3320   0.00959   0.00269  -0.0313   0.5070   0.0155
   0.250   0.3603   0.00953   0.00261  -0.0314   0.5065   0.0181
   0.500   0.3885   0.00946   0.00253  -0.0314   0.5060   0.0210
   0.750   0.4163   0.00934   0.00249  -0.0314   0.5055   0.0530
   1.000   0.4421   0.00892   0.00247  -0.0312   0.5048   0.2133
   1.250   0.4646   0.00824   0.00250  -0.0305   0.5039   0.4822
   1.500   0.4883   0.00692   0.00255  -0.0297   0.5032   0.9302
   2.000   0.6190   0.00688   0.00249  -0.0462   0.5007   1.0000
   2.250   0.6460   0.00683   0.00243  -0.0460   0.4986   1.0000
   2.500   0.6733   0.00675   0.00231  -0.0459   0.4961   1.0000
   2.750   0.7006   0.00668   0.00222  -0.0458   0.4939   1.0000
   3.000   0.7278   0.00667   0.00218  -0.0457   0.4926   1.0000
   3.250   0.7549   0.00669   0.00218  -0.0456   0.4915   1.0000
   3.500   0.7821   0.00673   0.00223  -0.0455   0.4903   1.0000
   3.750   0.8094   0.00676   0.00228  -0.0455   0.4887   1.0000
   4.000   0.8366   0.00680   0.00233  -0.0455   0.4872   1.0000
   4.250   0.8640   0.00683   0.00238  -0.0454   0.4855   1.0000
   4.500   0.8914   0.00685   0.00243  -0.0455   0.4835   1.0000
   4.750   0.9188   0.00685   0.00244  -0.0455   0.4813   1.0000
   5.000   0.9463   0.00684   0.00243  -0.0455   0.4790   1.0000
   5.250   0.9736   0.00689   0.00251  -0.0455   0.4764   1.0000
   5.500   1.0010   0.00693   0.00260  -0.0456   0.4730   1.0000
   5.750   1.0285   0.00695   0.00263  -0.0456   0.4691   1.0000
   6.000   1.0559   0.00696   0.00266  -0.0457   0.4643   1.0000
   6.250   1.0833   0.00699   0.00271  -0.0458   0.4563   1.0000
   6.500   1.1103   0.00706   0.00275  -0.0458   0.4450   1.0000
   6.750   1.1366   0.00721   0.00286  -0.0458   0.4302   1.0000
   7.000   1.1620   0.00750   0.00309  -0.0457   0.4107   1.0000
   7.250   1.1864   0.00794   0.00345  -0.0456   0.3881   1.0000
   7.500   1.2108   0.00837   0.00383  -0.0455   0.3687   1.0000
   7.750   1.2352   0.00881   0.00423  -0.0454   0.3513   1.0000
   8.000   1.2585   0.00937   0.00472  -0.0452   0.3312   1.0000
   8.250   1.2818   0.00992   0.00522  -0.0450   0.3109   1.0000
   8.500   1.3048   0.01048   0.00575  -0.0449   0.2935   1.0000
   8.750   1.3266   0.01117   0.00637  -0.0447   0.2737   1.0000
   9.000   1.3427   0.01246   0.00745  -0.0442   0.2338   1.0000
   9.250   1.3539   0.01421   0.00891  -0.0435   0.1856   1.0000
   9.500   1.3554   0.01694   0.01133  -0.0430   0.1302   1.0000
   9.750   1.3418   0.02297   0.01720  -0.0466   0.0875   1.0000
  10.000   1.3336   0.02570   0.01994  -0.0454   0.0807   1.0000
  10.250   1.3158   0.02931   0.02344  -0.0441   0.0590   1.0000
  10.500   1.3021   0.03259   0.02660  -0.0430   0.0378   1.0000
  10.750   1.2956   0.03530   0.02926  -0.0421   0.0231   1.0000
  11.000   1.2965   0.03739   0.03133  -0.0414   0.0159   1.0000
  11.250   1.2931   0.03989   0.03379  -0.0406   0.0075   1.0000
  11.500   1.2974   0.04179   0.03571  -0.0401   0.0046   1.0000
  11.750   1.3018   0.04377   0.03770  -0.0396   0.0025   1.0000
  12.000   1.3070   0.04575   0.03972  -0.0393   0.0015   1.0000
  12.250   1.3136   0.04763   0.04164  -0.0390   0.0010   1.0000
  12.500   1.3216   0.04936   0.04342  -0.0388   0.0009   1.0000
  12.750   1.3272   0.05138   0.04549  -0.0385   0.0007   1.0000
  13.000   1.3322   0.05352   0.04769  -0.0383   0.0005   1.0000
  13.250   1.3386   0.05551   0.04974  -0.0382   0.0005   1.0000
  13.500   1.3433   0.05770   0.05199  -0.0380   0.0003   1.0000
  13.750   1.3470   0.06007   0.05441  -0.0379   0.0003   1.0000
  14.000   1.3539   0.06209   0.05650  -0.0379   0.0004   1.0000
  14.250   1.3516   0.06518   0.05967  -0.0378   0.0002   1.0000
  14.500   1.3531   0.06790   0.06246  -0.0378   0.0002   1.0000
  14.750   1.3547   0.07066   0.06530  -0.0378   0.0002   1.0000
  15.000   1.3568   0.07338   0.06809  -0.0380   0.0002   1.0000
  15.250   1.3573   0.07631   0.07109  -0.0381   0.0002   1.0000
  15.500   1.3572   0.07940   0.07426  -0.0384   0.0002   1.0000
  15.750   1.3584   0.08234   0.07727  -0.0387   0.0002   1.0000
  16.000   1.3536   0.08616   0.08119  -0.0391   0.0001   1.0000
  16.250   1.3542   0.08923   0.08433  -0.0396   0.0001   1.0000
  16.500   1.3492   0.09316   0.08838  -0.0401   0.0001   1.0000
  16.750   1.3434   0.09730   0.09261  -0.0408   0.0001   1.0000
  17.000   1.3407   0.10100   0.09640  -0.0416   0.0001   1.0000
  17.250   1.3382   0.10469   0.10016  -0.0423   0.0001   1.0000
  17.500   1.3284   0.10955   0.10514  -0.0434   0.0001   1.0000
  17.750   1.3245   0.11361   0.10928  -0.0445   0.0001   1.0000
  18.000   1.3223   0.11740   0.11315  -0.0455   0.0001   1.0000
  18.250   1.3150   0.12203   0.11788  -0.0468   0.0001   1.0000
  18.500   1.3062   0.12698   0.12293  -0.0483   0.0001   1.0000
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