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MRC-16 (mrc-16-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MRC-16 (mrc-16-il)
Reynolds number: 200,000
Max Cl/Cd: 73.07 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mrc-16-il-200000.txt
Download as CSV file: xf-mrc-16-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MRC-16                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4010   0.09037   0.08716  -0.0446   1.0000   0.0636
  -9.000  -0.4242   0.08834   0.08522  -0.0421   1.0000   0.0642
  -8.750  -0.4449   0.08464   0.08159  -0.0434   0.9986   0.0653
  -8.500  -0.4870   0.07125   0.06766  -0.0666   0.9810   0.0682
  -8.250  -0.4808   0.06364   0.06003  -0.0695   0.9753   0.0695
  -8.000  -0.4533   0.06040   0.05687  -0.0715   0.9726   0.0710
  -7.750  -0.4335   0.05714   0.05354  -0.0737   0.9676   0.0732
  -7.500  -0.4553   0.04000   0.03490  -0.0748   0.9568   0.0449
  -7.250  -0.4437   0.03598   0.03045  -0.0737   0.9483   0.0435
  -7.000  -0.4175   0.03235   0.02631  -0.0747   0.9441   0.0437
  -6.750  -0.3846   0.02888   0.02230  -0.0764   0.9417   0.0435
  -6.500  -0.3638   0.02686   0.01992  -0.0753   0.9338   0.0440
  -6.250  -0.3302   0.02493   0.01762  -0.0764   0.9300   0.0453
  -6.000  -0.2937   0.02330   0.01567  -0.0781   0.9272   0.0479
  -5.750  -0.2657   0.02195   0.01432  -0.0784   0.9215   0.0504
  -5.500  -0.2361   0.02094   0.01322  -0.0787   0.9155   0.0531
  -5.250  -0.2008   0.02011   0.01222  -0.0798   0.9120   0.0568
  -5.000  -0.1753   0.01891   0.01111  -0.0795   0.9056   0.0619
  -4.750  -0.1477   0.01823   0.01036  -0.0793   0.8992   0.0672
  -4.500  -0.1174   0.01724   0.00943  -0.0797   0.8952   0.0758
  -4.250  -0.0972   0.01664   0.00883  -0.0782   0.8863   0.0850
  -4.000  -0.0698   0.01590   0.00815  -0.0780   0.8809   0.1017
  -3.750  -0.0479   0.01525   0.00763  -0.0769   0.8733   0.1301
  -3.500  -0.0266   0.01424   0.00709  -0.0758   0.8665   0.2210
  -3.250  -0.0090   0.01320   0.00679  -0.0742   0.8596   0.3949
  -3.000   0.0089   0.01252   0.00665  -0.0721   0.8517   0.5349
  -2.750   0.0319   0.01201   0.00652  -0.0704   0.8465   0.6477
  -2.500   0.0521   0.01185   0.00659  -0.0683   0.8375   0.7235
  -2.250   0.0792   0.01167   0.00649  -0.0671   0.8324   0.7822
  -2.000   0.1016   0.01172   0.00658  -0.0653   0.8234   0.8249
  -1.750   0.1299   0.01171   0.00653  -0.0643   0.8177   0.8599
  -1.500   0.1560   0.01184   0.00663  -0.0631   0.8094   0.8890
  -1.250   0.1902   0.01195   0.00664  -0.0633   0.8031   0.9125
  -1.000   0.2289   0.01213   0.00673  -0.0646   0.7958   0.9315
  -0.750   0.2738   0.01221   0.00668  -0.0675   0.7887   0.9451
  -0.500   0.3198   0.01225   0.00660  -0.0709   0.7815   0.9565
  -0.250   0.3686   0.01222   0.00646  -0.0751   0.7733   0.9654
   0.000   0.4144   0.01217   0.00631  -0.0788   0.7652   0.9742
   0.250   0.4580   0.01209   0.00612  -0.0821   0.7566   0.9835
   0.500   0.5046   0.01199   0.00596  -0.0862   0.7472   0.9912
   0.750   0.5506   0.01184   0.00568  -0.0902   0.7390   0.9981
   1.000   0.5787   0.01180   0.00560  -0.0907   0.7282   1.0000
   1.250   0.6016   0.01177   0.00551  -0.0901   0.7189   1.0000
   1.500   0.6247   0.01175   0.00541  -0.0894   0.7093   1.0000
   1.750   0.6469   0.01177   0.00540  -0.0886   0.6988   1.0000
   2.000   0.6702   0.01179   0.00534  -0.0879   0.6896   1.0000
   2.250   0.6924   0.01182   0.00534  -0.0870   0.6792   1.0000
   2.500   0.7142   0.01189   0.00538  -0.0860   0.6688   1.0000
   2.750   0.7372   0.01195   0.00536  -0.0852   0.6594   1.0000
   3.000   0.7586   0.01204   0.00543  -0.0841   0.6485   1.0000
   3.250   0.7800   0.01214   0.00551  -0.0830   0.6378   1.0000
   3.500   0.8026   0.01225   0.00555  -0.0820   0.6280   1.0000
   3.750   0.8237   0.01236   0.00564  -0.0808   0.6170   1.0000
   4.000   0.8445   0.01250   0.00578  -0.0795   0.6060   1.0000
   4.250   0.8664   0.01265   0.00588  -0.0784   0.5956   1.0000
   4.500   0.8880   0.01279   0.00598  -0.0772   0.5848   1.0000
   4.750   0.9081   0.01296   0.00617  -0.0758   0.5731   1.0000
   5.000   0.9290   0.01314   0.00633  -0.0745   0.5619   1.0000
   5.250   0.9508   0.01333   0.00646  -0.0734   0.5511   1.0000
   5.500   0.9709   0.01351   0.00665  -0.0720   0.5392   1.0000
   5.750   0.9907   0.01372   0.00688  -0.0705   0.5270   1.0000
   6.000   1.0109   0.01394   0.00709  -0.0691   0.5150   1.0000
   6.250   1.0315   0.01417   0.00729  -0.0677   0.5031   1.0000
   6.500   1.0522   0.01442   0.00751  -0.0664   0.4909   1.0000
   6.750   1.0712   0.01466   0.00778  -0.0649   0.4776   1.0000
   7.000   1.0906   0.01493   0.00807  -0.0634   0.4643   1.0000
   7.250   1.1098   0.01522   0.00836  -0.0619   0.4508   1.0000
   7.500   1.1289   0.01552   0.00868  -0.0604   0.4370   1.0000
   7.750   1.1475   0.01585   0.00900  -0.0588   0.4230   1.0000
   8.000   1.1655   0.01619   0.00934  -0.0572   0.4086   1.0000
   8.250   1.1828   0.01656   0.00972  -0.0555   0.3938   1.0000
   8.500   1.1993   0.01696   0.01012  -0.0536   0.3787   1.0000
   8.750   1.2148   0.01739   0.01055  -0.0517   0.3632   1.0000
   9.000   1.2293   0.01785   0.01101  -0.0496   0.3475   1.0000
   9.250   1.2421   0.01834   0.01150  -0.0473   0.3316   1.0000
   9.500   1.2528   0.01887   0.01204  -0.0446   0.3158   1.0000
   9.750   1.2628   0.01948   0.01264  -0.0420   0.2998   1.0000
  10.000   1.2723   0.02017   0.01332  -0.0394   0.2836   1.0000
  10.250   1.2812   0.02095   0.01408  -0.0369   0.2673   1.0000
  10.500   1.2893   0.02182   0.01494  -0.0345   0.2510   1.0000
  10.750   1.2965   0.02281   0.01592  -0.0322   0.2349   1.0000
  11.000   1.3028   0.02392   0.01700  -0.0299   0.2189   1.0000
  11.250   1.3095   0.02509   0.01818  -0.0279   0.2024   1.0000
  11.500   1.3151   0.02639   0.01948  -0.0259   0.1859   1.0000
  11.750   1.3195   0.02786   0.02094  -0.0240   0.1696   1.0000
  12.000   1.3225   0.02950   0.02256  -0.0221   0.1537   1.0000
  12.250   1.3239   0.03135   0.02440  -0.0204   0.1383   1.0000
  12.500   1.3237   0.03342   0.02643  -0.0187   0.1237   1.0000
  12.750   1.3222   0.03570   0.02868  -0.0171   0.1100   1.0000
  13.000   1.3195   0.03818   0.03114  -0.0157   0.0975   1.0000
  13.250   1.3162   0.04082   0.03377  -0.0145   0.0863   1.0000
  13.500   1.3122   0.04364   0.03661  -0.0134   0.0769   1.0000
  13.750   1.3062   0.04676   0.03974  -0.0125   0.0694   1.0000
  14.000   1.3003   0.05001   0.04299  -0.0119   0.0632   1.0000
  14.250   1.2961   0.05318   0.04624  -0.0113   0.0577   1.0000
  14.500   1.2902   0.05663   0.04971  -0.0110   0.0535   1.0000
  14.750   1.2848   0.06008   0.05323  -0.0107   0.0499   1.0000
  15.000   1.2823   0.06334   0.05659  -0.0107   0.0465   1.0000
  15.250   1.2758   0.06701   0.06025  -0.0106   0.0439   1.0000
  15.500   1.2734   0.07029   0.06364  -0.0106   0.0414   1.0000
  15.750   1.2719   0.07360   0.06705  -0.0108   0.0391   1.0000
  16.000   1.2695   0.07700   0.07049  -0.0111   0.0372   1.0000
  16.250   1.2681   0.07982   0.07325  -0.0105   0.0354   1.0000
  16.500   1.2679   0.08310   0.07672  -0.0108   0.0341   1.0000
  16.750   1.2675   0.08636   0.08010  -0.0112   0.0327   1.0000
  17.000   1.2673   0.08961   0.08343  -0.0117   0.0313   1.0000
  17.250   1.2682   0.09258   0.08642  -0.0120   0.0301   1.0000
  17.500   1.2714   0.09482   0.08867  -0.0112   0.0288   1.0000
  17.750   1.2682   0.09879   0.09283  -0.0123   0.0281   1.0000
  18.000   1.2658   0.10259   0.09680  -0.0133   0.0273   1.0000
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