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MRC-16 (mrc-16-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MRC-16 (mrc-16-il)
Reynolds number: 500,000
Max Cl/Cd: 94.37 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-16-il-500000-n5.txt
Download as CSV file: xf-mrc-16-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7506   0.05649   0.05356  -0.0724   1.0000   0.0101
 -13.250  -0.7835   0.04635   0.04315  -0.0815   1.0000   0.0100
 -13.000  -0.8035   0.04099   0.03756  -0.0846   1.0000   0.0100
 -12.750  -0.8196   0.03752   0.03391  -0.0845   1.0000   0.0101
 -12.500  -0.8373   0.03534   0.03159  -0.0813   0.9998   0.0101
 -12.250  -0.8306   0.03251   0.02849  -0.0826   0.9916   0.0103
 -12.000  -0.8190   0.03019   0.02590  -0.0832   0.9836   0.0105
 -11.750  -0.8048   0.02826   0.02373  -0.0832   0.9754   0.0107
 -11.500  -0.7861   0.02658   0.02181  -0.0836   0.9694   0.0109
 -11.250  -0.7682   0.02527   0.02030  -0.0832   0.9614   0.0110
 -11.000  -0.7498   0.02387   0.01875  -0.0830   0.9546   0.0113
 -10.750  -0.7307   0.02296   0.01774  -0.0823   0.9464   0.0116
 -10.500  -0.7093   0.02219   0.01689  -0.0819   0.9398   0.0118
 -10.250  -0.6890   0.02147   0.01607  -0.0811   0.9318   0.0121
 -10.000  -0.6678   0.02072   0.01519  -0.0804   0.9252   0.0124
  -9.750  -0.6472   0.01994   0.01429  -0.0796   0.9174   0.0128
  -9.500  -0.6259   0.01917   0.01337  -0.0788   0.9107   0.0131
  -9.250  -0.6042   0.01844   0.01252  -0.0781   0.9035   0.0134
  -9.000  -0.5818   0.01778   0.01171  -0.0773   0.8966   0.0138
  -8.750  -0.5590   0.01715   0.01097  -0.0767   0.8900   0.0140
  -8.500  -0.5369   0.01644   0.01018  -0.0760   0.8828   0.0145
  -8.250  -0.5132   0.01593   0.00960  -0.0755   0.8766   0.0149
  -8.000  -0.4891   0.01548   0.00908  -0.0750   0.8694   0.0154
  -7.500  -0.4398   0.01464   0.00808  -0.0741   0.8559   0.0168
  -7.250  -0.4148   0.01427   0.00760  -0.0737   0.8491   0.0174
  -7.000  -0.3906   0.01376   0.00706  -0.0732   0.8423   0.0182
  -6.750  -0.3654   0.01340   0.00665  -0.0728   0.8352   0.0190
  -6.500  -0.3400   0.01306   0.00625  -0.0724   0.8285   0.0200
  -6.250  -0.3144   0.01274   0.00585  -0.0721   0.8212   0.0209
  -6.000  -0.2890   0.01240   0.00545  -0.0717   0.8144   0.0221
  -5.750  -0.2632   0.01211   0.00513  -0.0714   0.8067   0.0237
  -5.500  -0.2371   0.01187   0.00482  -0.0711   0.7998   0.0254
  -5.250  -0.2112   0.01159   0.00450  -0.0708   0.7921   0.0272
  -5.000  -0.1852   0.01135   0.00422  -0.0705   0.7850   0.0296
  -4.750  -0.1587   0.01115   0.00398  -0.0702   0.7771   0.0321
  -4.250  -0.1061   0.01072   0.00350  -0.0697   0.7617   0.0405
  -3.750  -0.0534   0.01035   0.00310  -0.0692   0.7460   0.0545
  -3.500  -0.0271   0.01018   0.00292  -0.0690   0.7383   0.0651
  -3.250  -0.0006   0.00999   0.00277  -0.0688   0.7300   0.0796
  -3.000   0.0253   0.00980   0.00261  -0.0685   0.7222   0.1008
  -2.750   0.0512   0.00956   0.00247  -0.0682   0.7137   0.1328
  -2.500   0.0766   0.00931   0.00234  -0.0679   0.7059   0.1771
  -2.250   0.1018   0.00902   0.00221  -0.0675   0.6973   0.2358
  -2.000   0.1264   0.00870   0.00211  -0.0671   0.6893   0.3075
  -1.750   0.1509   0.00840   0.00202  -0.0666   0.6806   0.3822
  -1.500   0.1753   0.00813   0.00196  -0.0661   0.6725   0.4569
  -1.250   0.1994   0.00787   0.00191  -0.0654   0.6637   0.5290
  -1.000   0.2236   0.00766   0.00189  -0.0647   0.6555   0.5981
  -0.750   0.2476   0.00749   0.00189  -0.0639   0.6468   0.6628
  -0.500   0.2719   0.00735   0.00191  -0.0631   0.6382   0.7201
  -0.250   0.2967   0.00730   0.00194  -0.0624   0.6296   0.7639
   0.000   0.3225   0.00727   0.00198  -0.0618   0.6205   0.7972
   0.250   0.3483   0.00728   0.00202  -0.0613   0.6118   0.8241
   0.500   0.3745   0.00731   0.00206  -0.0608   0.6026   0.8466
   0.750   0.4009   0.00736   0.00211  -0.0604   0.5937   0.8665
   1.000   0.4273   0.00743   0.00216  -0.0600   0.5844   0.8839
   1.250   0.4543   0.00750   0.00222  -0.0598   0.5749   0.8993
   1.500   0.4814   0.00759   0.00229  -0.0596   0.5657   0.9132
   1.750   0.5090   0.00769   0.00235  -0.0595   0.5556   0.9257
   2.000   0.5374   0.00780   0.00243  -0.0596   0.5459   0.9370
   2.250   0.5674   0.00793   0.00251  -0.0601   0.5357   0.9460
   2.500   0.5965   0.00806   0.00259  -0.0604   0.5250   0.9555
   2.750   0.6294   0.00819   0.00269  -0.0616   0.5144   0.9622
   3.000   0.6592   0.00834   0.00279  -0.0622   0.5038   0.9702
   3.250   0.6932   0.00850   0.00290  -0.0637   0.4924   0.9748
   3.500   0.7250   0.00864   0.00301  -0.0647   0.4814   0.9804
   3.750   0.7581   0.00881   0.00313  -0.0661   0.4699   0.9844
   4.000   0.7921   0.00899   0.00326  -0.0677   0.4582   0.9878
   4.250   0.8246   0.00917   0.00340  -0.0690   0.4460   0.9918
   4.500   0.8574   0.00935   0.00355  -0.0703   0.4336   0.9951
   4.750   0.8907   0.00954   0.00371  -0.0718   0.4210   0.9981
   5.000   0.9184   0.00974   0.00387  -0.0721   0.4085   1.0000
   5.250   0.9371   0.00994   0.00402  -0.0705   0.3972   1.0000
   5.500   0.9560   0.01013   0.00418  -0.0689   0.3852   1.0000
   5.750   0.9752   0.01034   0.00436  -0.0673   0.3733   1.0000
   6.000   0.9942   0.01056   0.00455  -0.0657   0.3613   1.0000
   6.250   1.0129   0.01081   0.00476  -0.0641   0.3487   1.0000
   6.500   1.0318   0.01107   0.00499  -0.0626   0.3359   1.0000
   6.750   1.0508   0.01136   0.00523  -0.0611   0.3223   1.0000
   7.000   1.0702   0.01166   0.00549  -0.0597   0.3084   1.0000
   7.250   1.0896   0.01198   0.00577  -0.0583   0.2942   1.0000
   7.500   1.1086   0.01233   0.00608  -0.0569   0.2794   1.0000
   7.750   1.1272   0.01271   0.00641  -0.0555   0.2643   1.0000
   8.000   1.1450   0.01313   0.00677  -0.0540   0.2488   1.0000
   8.500   1.1772   0.01402   0.00756  -0.0504   0.2177   1.0000
   8.750   1.1928   0.01454   0.00802  -0.0486   0.2015   1.0000
   9.000   1.2079   0.01510   0.00852  -0.0468   0.1851   1.0000
   9.250   1.2224   0.01572   0.00908  -0.0450   0.1686   1.0000
   9.500   1.2363   0.01639   0.00969  -0.0432   0.1526   1.0000
   9.750   1.2496   0.01713   0.01036  -0.0414   0.1371   1.0000
  10.000   1.2622   0.01792   0.01109  -0.0396   0.1225   1.0000
  10.500   1.2858   0.01967   0.01274  -0.0361   0.0958   1.0000
  10.750   1.2968   0.02064   0.01368  -0.0344   0.0838   1.0000
  11.000   1.3074   0.02166   0.01467  -0.0327   0.0731   1.0000
  11.250   1.3177   0.02273   0.01573  -0.0311   0.0637   1.0000
  11.500   1.3276   0.02387   0.01685  -0.0296   0.0556   1.0000
  11.750   1.3368   0.02508   0.01806  -0.0281   0.0486   1.0000
  12.000   1.3450   0.02641   0.01940  -0.0267   0.0424   1.0000
  12.250   1.3534   0.02776   0.02077  -0.0253   0.0371   1.0000
  12.500   1.3614   0.02918   0.02221  -0.0241   0.0329   1.0000
  12.750   1.3679   0.03076   0.02382  -0.0228   0.0292   1.0000
  13.000   1.3758   0.03228   0.02538  -0.0218   0.0264   1.0000
  13.250   1.3809   0.03406   0.02720  -0.0207   0.0238   1.0000
  13.500   1.3874   0.03577   0.02899  -0.0198   0.0217   1.0000
  13.750   1.3919   0.03771   0.03098  -0.0189   0.0198   1.0000
  14.000   1.3961   0.03973   0.03306  -0.0181   0.0183   1.0000
  14.250   1.4003   0.04182   0.03522  -0.0174   0.0170   1.0000
  14.500   1.4028   0.04414   0.03760  -0.0169   0.0158   1.0000
  14.750   1.4048   0.04658   0.04012  -0.0164   0.0150   1.0000
  15.000   1.4074   0.04902   0.04265  -0.0161   0.0142   1.0000
  15.250   1.4086   0.05167   0.04539  -0.0158   0.0135   1.0000
  15.500   1.4085   0.05455   0.04835  -0.0157   0.0128   1.0000
  15.750   1.4067   0.05768   0.05157  -0.0157   0.0123   1.0000
  16.000   1.4050   0.06088   0.05487  -0.0159   0.0119   1.0000
  16.250   1.4036   0.06411   0.05821  -0.0161   0.0115   1.0000
  16.500   1.4012   0.06754   0.06174  -0.0165   0.0111   1.0000
  16.750   1.3979   0.07115   0.06545  -0.0170   0.0107   1.0000
  17.000   1.3932   0.07497   0.06937  -0.0177   0.0103   1.0000
  17.250   1.3875   0.07904   0.07353  -0.0185   0.0100   1.0000
  17.500   1.3803   0.08338   0.07797  -0.0194   0.0098   1.0000
  17.750   1.3714   0.08804   0.08273  -0.0206   0.0095   1.0000
  18.000   1.3639   0.09254   0.08733  -0.0218   0.0093   1.0000
  18.250   1.3571   0.09702   0.09193  -0.0231   0.0091   1.0000
  18.500   1.3496   0.10167   0.09669  -0.0245   0.0089   1.0000
  18.750   1.3416   0.10645   0.10159  -0.0261   0.0087   1.0000
  19.000   1.3333   0.11131   0.10656  -0.0278   0.0085   1.0000
  19.250   1.3247   0.11629   0.11164  -0.0296   0.0084   1.0000
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