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MRC-20 (mrc-20-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MRC-20 (mrc-20-il)
Reynolds number: 200,000
Max Cl/Cd: 73.06 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mrc-20-il-200000.txt
Download as CSV file: xf-mrc-20-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MRC-20                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4346   0.08987   0.08659  -0.0585   0.9889   0.0431
  -8.750  -0.4538   0.08431   0.08091  -0.0650   0.9828   0.0433
  -8.500  -0.4773   0.08025   0.07655  -0.0679   0.9735   0.0437
  -8.250  -0.4942   0.07737   0.07330  -0.0673   0.9633   0.0439
  -8.000  -0.4723   0.07088   0.06700  -0.0698   0.9619   0.0447
  -7.750  -0.4599   0.06759   0.06373  -0.0703   0.9575   0.0454
  -7.500  -0.4520   0.06468   0.06075  -0.0702   0.9511   0.0464
  -7.250  -0.4348   0.06128   0.05719  -0.0721   0.9474   0.0482
  -7.000  -0.4413   0.06149   0.05661  -0.0679   0.9360   0.0521
  -6.750  -0.3763   0.04170   0.03745  -0.0722   0.9201   0.0545
  -6.500  -0.3957   0.05168   0.04688  -0.0724   0.9316   0.0549
  -6.250  -0.3916   0.04989   0.04500  -0.0694   0.9224   0.0567
  -6.000  -0.3705   0.04784   0.04230  -0.0691   0.9180   0.0631
  -5.750  -0.3406   0.04423   0.03878  -0.0716   0.9164   0.0655
  -5.500  -0.3341   0.04279   0.03724  -0.0684   0.9069   0.0683
  -5.250  -0.3081   0.04052   0.03457  -0.0689   0.9034   0.0764
  -4.750  -0.2671   0.03683   0.03066  -0.0680   0.8923   0.0919
  -4.500  -0.2387   0.03502   0.02864  -0.0688   0.8889   0.1060
  -4.250  -0.2056   0.03297   0.02646  -0.0706   0.8869   0.1224
  -4.000  -0.1645   0.03092   0.02360  -0.0685   0.8827   0.0724
  -3.750  -0.1313   0.02662   0.01872  -0.0664   0.8780   0.0418
  -3.500  -0.0953   0.02499   0.01696  -0.0675   0.8750   0.0407
  -3.250  -0.0562   0.02371   0.01558  -0.0693   0.8731   0.0414
  -3.000  -0.0151   0.02285   0.01458  -0.0715   0.8715   0.0438
  -2.750  -0.0011   0.02196   0.01375  -0.0688   0.8628   0.0448
  -2.500   0.0322   0.02089   0.01275  -0.0698   0.8595   0.0472
  -2.250   0.0696   0.01996   0.01180  -0.0715   0.8574   0.0513
  -2.000   0.1076   0.01894   0.01078  -0.0735   0.8559   0.0610
  -1.750   0.1211   0.01854   0.01036  -0.0707   0.8461   0.0731
  -1.500   0.1358   0.01573   0.00967  -0.0686   0.8428   0.6294
  -1.250   0.1684   0.01525   0.00938  -0.0684   0.8408   0.7027
  -1.000   0.1857   0.01523   0.00946  -0.0658   0.8320   0.7394
  -0.750   0.2145   0.01494   0.00926  -0.0649   0.8282   0.7819
  -0.500   0.2495   0.01455   0.00888  -0.0653   0.8257   0.8068
  -0.250   0.2730   0.01442   0.00873  -0.0644   0.8177   0.8207
   0.000   0.3060   0.01408   0.00836  -0.0650   0.8129   0.8339
   0.250   0.3443   0.01366   0.00791  -0.0666   0.8098   0.8472
   0.500   0.3670   0.01359   0.00785  -0.0653   0.8009   0.8634
   0.750   0.4023   0.01329   0.00753  -0.0664   0.7958   0.8791
   1.000   0.4352   0.01312   0.00733  -0.0670   0.7894   0.8953
   1.250   0.4678   0.01301   0.00720  -0.0677   0.7813   0.9115
   1.500   0.5082   0.01285   0.00698  -0.0699   0.7749   0.9258
   1.750   0.5440   0.01283   0.00693  -0.0714   0.7654   0.9406
   2.000   0.5903   0.01279   0.00684  -0.0751   0.7567   0.9492
   2.250   0.6349   0.01272   0.00671  -0.0786   0.7474   0.9588
   2.500   0.6800   0.01274   0.00670  -0.0823   0.7361   0.9671
   2.750   0.7272   0.01271   0.00661  -0.0865   0.7252   0.9742
   3.000   0.7738   0.01267   0.00649  -0.0906   0.7138   0.9817
   3.250   0.8191   0.01268   0.00648  -0.0946   0.6999   0.9890
   3.500   0.8643   0.01271   0.00647  -0.0986   0.6857   0.9964
   3.750   0.8956   0.01274   0.00646  -0.0999   0.6715   1.0000
   4.000   0.9107   0.01280   0.00646  -0.0977   0.6581   1.0000
   4.250   0.9265   0.01289   0.00648  -0.0956   0.6448   1.0000
   4.500   0.9432   0.01301   0.00652  -0.0936   0.6315   1.0000
   4.750   0.9588   0.01315   0.00662  -0.0914   0.6177   1.0000
   5.000   0.9723   0.01332   0.00675  -0.0887   0.6035   1.0000
   5.250   0.9867   0.01351   0.00690  -0.0862   0.5893   1.0000
   5.500   1.0017   0.01371   0.00706  -0.0838   0.5753   1.0000
   5.750   1.0172   0.01393   0.00724  -0.0815   0.5613   1.0000
   6.000   1.0329   0.01416   0.00742  -0.0792   0.5473   1.0000
   6.250   1.0487   0.01441   0.00761  -0.0770   0.5334   1.0000
   6.500   1.0649   0.01468   0.00782  -0.0748   0.5195   1.0000
   6.750   1.0793   0.01495   0.00809  -0.0724   0.5052   1.0000
   7.000   1.0938   0.01524   0.00836  -0.0700   0.4908   1.0000
   7.250   1.1086   0.01555   0.00865  -0.0676   0.4764   1.0000
   7.500   1.1231   0.01587   0.00897  -0.0653   0.4621   1.0000
   7.750   1.1366   0.01621   0.00929  -0.0628   0.4481   1.0000
   8.000   1.1499   0.01658   0.00963  -0.0603   0.4341   1.0000
   8.250   1.1632   0.01698   0.01000  -0.0578   0.4201   1.0000
   8.500   1.1763   0.01742   0.01041  -0.0554   0.4059   1.0000
   8.750   1.1888   0.01789   0.01086  -0.0530   0.3915   1.0000
   9.000   1.2006   0.01838   0.01136  -0.0505   0.3766   1.0000
   9.250   1.2121   0.01892   0.01191  -0.0481   0.3616   1.0000
   9.500   1.2231   0.01950   0.01249  -0.0456   0.3464   1.0000
   9.750   1.2335   0.02013   0.01312  -0.0432   0.3309   1.0000
  10.000   1.2434   0.02082   0.01381  -0.0408   0.3153   1.0000
  10.250   1.2526   0.02157   0.01457  -0.0384   0.2995   1.0000
  10.500   1.2613   0.02240   0.01539  -0.0360   0.2837   1.0000
  10.750   1.2692   0.02331   0.01629  -0.0336   0.2678   1.0000
  11.000   1.2765   0.02431   0.01728  -0.0313   0.2518   1.0000
  11.250   1.2829   0.02541   0.01836  -0.0290   0.2359   1.0000
  11.500   1.2890   0.02659   0.01954  -0.0268   0.2199   1.0000
  11.750   1.2945   0.02787   0.02082  -0.0247   0.2036   1.0000
  12.000   1.2991   0.02927   0.02221  -0.0226   0.1875   1.0000
  12.250   1.3025   0.03081   0.02375  -0.0206   0.1716   1.0000
  12.500   1.3047   0.03252   0.02543  -0.0186   0.1562   1.0000
  12.750   1.3057   0.03439   0.02729  -0.0167   0.1415   1.0000
  13.000   1.3056   0.03645   0.02932  -0.0149   0.1277   1.0000
  13.250   1.3045   0.03868   0.03155  -0.0132   0.1150   1.0000
  13.500   1.3025   0.04110   0.03395  -0.0116   0.1037   1.0000
  13.750   1.2990   0.04375   0.03659  -0.0102   0.0942   1.0000
  14.000   1.2940   0.04665   0.03945  -0.0090   0.0863   1.0000
  14.250   1.2934   0.04925   0.04213  -0.0080   0.0787   1.0000
  14.500   1.2883   0.05233   0.04522  -0.0070   0.0733   1.0000
  14.750   1.2873   0.05513   0.04809  -0.0064   0.0681   1.0000
  15.000   1.2820   0.05835   0.05130  -0.0057   0.0642   1.0000
  15.250   1.2825   0.06112   0.05420  -0.0053   0.0603   1.0000
  15.500   1.2800   0.06419   0.05728  -0.0050   0.0573   1.0000
  15.750   1.2787   0.06711   0.06024  -0.0045   0.0545   1.0000
  16.000   1.2794   0.06998   0.06323  -0.0044   0.0518   1.0000
  16.250   1.2795   0.07288   0.06618  -0.0043   0.0496   1.0000
  16.500   1.2821   0.07512   0.06836  -0.0035   0.0475   1.0000
  16.750   1.2827   0.07814   0.07157  -0.0036   0.0458   1.0000
  17.000   1.2839   0.08103   0.07458  -0.0037   0.0441   1.0000
  17.250   1.2859   0.08376   0.07736  -0.0039   0.0425   1.0000
  17.500   1.2935   0.08539   0.07891  -0.0030   0.0407   1.0000
  17.750   1.2939   0.08843   0.08212  -0.0032   0.0397   1.0000
  18.000   1.2936   0.09166   0.08554  -0.0036   0.0387   1.0000
  18.250   1.2929   0.09496   0.08899  -0.0041   0.0377   1.0000
  18.500   1.2930   0.09814   0.09230  -0.0047   0.0367   1.0000
  18.750   1.2946   0.10105   0.09527  -0.0053   0.0358   1.0000
  19.000   1.3038   0.10256   0.09674  -0.0048   0.0346   1.0000
  19.250   1.2995   0.10644   0.10080  -0.0056   0.0340   1.0000
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