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MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MILEY M06-13-128 (miley-il)
Reynolds number: 1,000,000
Max Cl/Cd: 167.96 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-miley-il-1000000.txt
Download as CSV file: xf-miley-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2645   0.08615   0.08301  -0.0167   0.5359   0.0069
  -7.500  -0.2626   0.08291   0.07980  -0.0182   0.5356   0.0069
  -7.250  -0.2624   0.07975   0.07666  -0.0196   0.5352   0.0072
  -7.000  -0.2666   0.07681   0.07375  -0.0208   0.5349   0.0071
  -6.750  -0.2659   0.07344   0.07040  -0.0236   0.5345   0.0075
  -6.500  -0.2603   0.06964   0.06659  -0.0269   0.5343   0.0076
  -6.250  -0.2520   0.06558   0.06250  -0.0303   0.5340   0.0078
  -6.000  -0.2407   0.06123   0.05810  -0.0335   0.5336   0.0080
  -5.750  -0.2249   0.05667   0.05345  -0.0366   0.5333   0.0083
  -5.500  -0.2073   0.05242   0.04909  -0.0385   0.5329   0.0084
  -5.250  -0.1896   0.04867   0.04523  -0.0396   0.5325   0.0085
  -5.000  -0.1709   0.04503   0.04146  -0.0403   0.5319   0.0085
  -4.750  -0.1514   0.04133   0.03759  -0.0405   0.5315   0.0086
  -4.500  -0.1312   0.03784   0.03392  -0.0404   0.5314   0.0086
  -4.250  -0.1105   0.03454   0.03040  -0.0400   0.5312   0.0086
  -4.000  -0.0969   0.02951   0.02510  -0.0395   0.5309   0.0091
  -3.750  -0.0744   0.02769   0.02314  -0.0392   0.5305   0.0093
  -3.500  -0.0509   0.02591   0.02120  -0.0387   0.5301   0.0097
  -3.250  -0.0266   0.02406   0.01916  -0.0381   0.5297   0.0101
  -3.000  -0.0014   0.02226   0.01714  -0.0373   0.5293   0.0108
  -2.750   0.0277   0.02179   0.01645  -0.0365   0.5289   0.0123
  -2.500   0.0492   0.01630   0.01034  -0.0340   0.5285   0.0079
  -2.250   0.0755   0.01454   0.00832  -0.0330   0.5281   0.0077
  -2.000   0.1031   0.01393   0.00758  -0.0326   0.5275   0.0084
  -1.750   0.1288   0.01296   0.00653  -0.0320   0.5269   0.0093
  -1.500   0.1559   0.01260   0.00616  -0.0318   0.5263   0.0098
  -1.250   0.1833   0.01236   0.00590  -0.0316   0.5257   0.0107
  -1.000   0.2109   0.01218   0.00570  -0.0315   0.5251   0.0117
  -0.750   0.2385   0.01197   0.00545  -0.0313   0.5245   0.0124
  -0.500   0.2644   0.01143   0.00485  -0.0308   0.5239   0.0150
  -0.250   0.2924   0.01131   0.00472  -0.0307   0.5232   0.0177
   0.000   0.3198   0.01109   0.00446  -0.0305   0.5226   0.0236
   0.250   0.3477   0.01099   0.00434  -0.0304   0.5219   0.0315
   0.500   0.3712   0.01024   0.00427  -0.0299   0.5212   0.2731
   0.750   0.3878   0.00910   0.00427  -0.0280   0.5206   0.6678
   1.000   0.4779   0.00839   0.00433  -0.0414   0.5197   0.9928
   1.250   0.5291   0.00857   0.00443  -0.0466   0.5185   1.0000
   1.500   0.5551   0.00871   0.00455  -0.0463   0.5174   1.0000
   1.750   0.5817   0.00867   0.00449  -0.0460   0.5166   1.0000
   2.000   0.6084   0.00861   0.00442  -0.0458   0.5154   1.0000
   2.250   0.6353   0.00852   0.00431  -0.0455   0.5136   1.0000
   2.500   0.6623   0.00838   0.00413  -0.0453   0.5115   1.0000
   2.750   0.6894   0.00825   0.00398  -0.0451   0.5097   1.0000
   3.000   0.7165   0.00820   0.00390  -0.0450   0.5085   1.0000
   3.250   0.7436   0.00820   0.00387  -0.0448   0.5075   1.0000
   3.500   0.7707   0.00819   0.00383  -0.0447   0.5065   1.0000
   3.750   0.7978   0.00823   0.00384  -0.0446   0.5054   1.0000
   4.000   0.8246   0.00838   0.00399  -0.0445   0.5040   1.0000
   4.250   0.8517   0.00836   0.00399  -0.0445   0.5032   1.0000
   4.500   0.8789   0.00835   0.00402  -0.0444   0.5020   1.0000
   4.750   0.9061   0.00834   0.00404  -0.0444   0.5005   1.0000
   5.000   0.9335   0.00830   0.00404  -0.0444   0.4988   1.0000
   5.250   0.9609   0.00824   0.00400  -0.0444   0.4970   1.0000
   5.500   0.9885   0.00818   0.00395  -0.0444   0.4955   1.0000
   5.750   1.0161   0.00812   0.00390  -0.0444   0.4940   1.0000
   6.000   1.0438   0.00804   0.00383  -0.0445   0.4924   1.0000
   6.250   1.0712   0.00802   0.00382  -0.0445   0.4904   1.0000
   6.500   1.0986   0.00799   0.00387  -0.0446   0.4879   1.0000
   6.750   1.1262   0.00794   0.00389  -0.0447   0.4851   1.0000
   7.000   1.1539   0.00787   0.00386  -0.0448   0.4822   1.0000
   7.250   1.1817   0.00777   0.00379  -0.0449   0.4792   1.0000
   7.500   1.2093   0.00776   0.00386  -0.0450   0.4747   1.0000
   7.750   1.2370   0.00772   0.00387  -0.0452   0.4685   1.0000
   8.000   1.2646   0.00769   0.00389  -0.0453   0.4609   1.0000
   8.250   1.2916   0.00769   0.00387  -0.0454   0.4433   1.0000
   8.500   1.3148   0.00816   0.00416  -0.0451   0.4031   1.0000
   8.750   1.3341   0.00918   0.00495  -0.0446   0.3563   1.0000
   9.000   1.3519   0.01039   0.00594  -0.0441   0.3080   1.0000
   9.250   1.3678   0.01176   0.00706  -0.0435   0.2627   1.0000
   9.500   1.3842   0.01300   0.00812  -0.0431   0.2283   1.0000
   9.750   1.3985   0.01437   0.00934  -0.0426   0.1961   1.0000
  10.000   1.4076   0.01628   0.01107  -0.0422   0.1599   1.0000
  10.250   1.4061   0.02086   0.01551  -0.0452   0.1212   1.0000
  10.500   1.3864   0.02522   0.01983  -0.0449   0.1040   1.0000
  10.750   1.3667   0.02901   0.02352  -0.0436   0.0843   1.0000
  11.250   1.3409   0.03545   0.02976  -0.0415   0.0466   1.0000
  11.500   1.3224   0.03916   0.03331  -0.0402   0.0221   1.0000
  11.750   1.3132   0.04221   0.03628  -0.0393   0.0087   1.0000
  12.000   1.3086   0.04508   0.03915  -0.0387   0.0038   1.0000
  12.250   1.3134   0.04714   0.04126  -0.0383   0.0033   1.0000
  12.500   1.3203   0.04899   0.04317  -0.0380   0.0031   1.0000
  12.750   1.3250   0.05112   0.04535  -0.0377   0.0027   1.0000
  13.000   1.3276   0.05352   0.04781  -0.0375   0.0024   1.0000
  13.250   1.3237   0.05663   0.05102  -0.0371   0.0019   1.0000
  13.500   1.3254   0.05923   0.05370  -0.0370   0.0019   1.0000
  13.750   1.3279   0.06178   0.05632  -0.0369   0.0018   1.0000
  14.000   1.3288   0.06454   0.05918  -0.0369   0.0018   1.0000
  14.250   1.3281   0.06755   0.06226  -0.0369   0.0017   1.0000
  14.500   1.3266   0.07073   0.06553  -0.0370   0.0016   1.0000
  14.750   1.3246   0.07402   0.06890  -0.0371   0.0016   1.0000
  15.000   1.3235   0.07723   0.07220  -0.0373   0.0016   1.0000
  15.250   1.3214   0.08063   0.07568  -0.0377   0.0016   1.0000
  15.500   1.3170   0.08442   0.07956  -0.0381   0.0016   1.0000
  15.750   1.3099   0.08861   0.08384  -0.0386   0.0015   1.0000
  16.000   1.3059   0.09242   0.08774  -0.0391   0.0015   1.0000
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