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MRC-16 (mrc-16-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MRC-16 (mrc-16-il)
Reynolds number: 100,000
Max Cl/Cd: 52.53 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-16-il-100000-n5.txt
Download as CSV file: xf-mrc-16-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4262   0.08345   0.07850  -0.0593   1.0000   0.0319
 -10.000  -0.4421   0.07773   0.07285  -0.0614   1.0000   0.0317
  -9.750  -0.4651   0.07268   0.06786  -0.0630   1.0000   0.0314
  -9.500  -0.4938   0.06958   0.06481  -0.0618   1.0000   0.0312
  -9.250  -0.5256   0.06786   0.06313  -0.0579   1.0000   0.0309
  -9.000  -0.5395   0.06079   0.05576  -0.0629   0.9887   0.0308
  -8.750  -0.5447   0.05435   0.04891  -0.0661   0.9786   0.0309
  -8.500  -0.5408   0.04870   0.04273  -0.0682   0.9708   0.0310
  -8.250  -0.5355   0.04421   0.03769  -0.0682   0.9615   0.0312
  -8.000  -0.5190   0.03979   0.03258  -0.0692   0.9562   0.0317
  -7.750  -0.5039   0.03712   0.02953  -0.0686   0.9480   0.0323
  -7.500  -0.4760   0.03547   0.02775  -0.0700   0.9435   0.0337
  -7.250  -0.4502   0.03381   0.02582  -0.0707   0.9382   0.0355
  -7.000  -0.4276   0.03181   0.02342  -0.0704   0.9313   0.0372
  -6.750  -0.3975   0.02968   0.02080  -0.0712   0.9272   0.0386
  -6.500  -0.3728   0.02818   0.01919  -0.0711   0.9208   0.0400
  -6.250  -0.3453   0.02718   0.01810  -0.0715   0.9148   0.0425
  -6.000  -0.3126   0.02598   0.01666  -0.0726   0.9109   0.0458
  -5.750  -0.2892   0.02488   0.01545  -0.0719   0.9034   0.0481
  -5.250  -0.2281   0.02308   0.01348  -0.0732   0.8940   0.0567
  -5.000  -0.2085   0.02232   0.01278  -0.0718   0.8850   0.0607
  -4.750  -0.1785   0.02160   0.01195  -0.0723   0.8801   0.0680
  -4.500  -0.1567   0.02096   0.01134  -0.0713   0.8722   0.0754
  -4.250  -0.1300   0.02029   0.01066  -0.0711   0.8661   0.0869
  -4.000  -0.1046   0.01968   0.01007  -0.0707   0.8596   0.1034
  -3.750  -0.0810   0.01908   0.00957  -0.0700   0.8520   0.1294
  -3.500  -0.0529   0.01827   0.00902  -0.0702   0.8473   0.1861
  -3.250  -0.0347   0.01761   0.00878  -0.0688   0.8379   0.2774
  -3.000  -0.0104   0.01675   0.00845  -0.0682   0.8326   0.4114
  -2.750   0.0080   0.01625   0.00842  -0.0662   0.8238   0.5291
  -2.500   0.0334   0.01582   0.00835  -0.0650   0.8180   0.6398
  -2.250   0.0573   0.01570   0.00843  -0.0633   0.8103   0.7212
  -2.000   0.0858   0.01564   0.00843  -0.0624   0.8039   0.7848
  -1.750   0.1163   0.01568   0.00846  -0.0618   0.7974   0.8335
  -1.500   0.1480   0.01578   0.00848  -0.0617   0.7899   0.8707
  -1.250   0.1871   0.01579   0.00835  -0.0631   0.7847   0.8973
  -1.000   0.2214   0.01590   0.00836  -0.0641   0.7758   0.9186
  -0.750   0.2634   0.01585   0.00814  -0.0665   0.7700   0.9343
  -0.500   0.3029   0.01591   0.00810  -0.0688   0.7609   0.9481
  -0.250   0.3472   0.01581   0.00785  -0.0720   0.7545   0.9590
   0.000   0.3867   0.01583   0.00778  -0.0746   0.7450   0.9706
   0.250   0.4307   0.01571   0.00752  -0.0779   0.7378   0.9794
   0.500   0.4715   0.01568   0.00742  -0.0809   0.7279   0.9887
   0.750   0.5131   0.01560   0.00725  -0.0840   0.7193   0.9971
   1.000   0.5416   0.01557   0.00714  -0.0844   0.7100   1.0000
   1.250   0.5616   0.01562   0.00714  -0.0832   0.7001   1.0000
   1.500   0.5844   0.01560   0.00703  -0.0823   0.6918   1.0000
   1.750   0.6035   0.01571   0.00711  -0.0809   0.6811   1.0000
   2.000   0.6246   0.01577   0.00712  -0.0797   0.6717   1.0000
   2.250   0.6464   0.01583   0.00711  -0.0786   0.6625   1.0000
   2.500   0.6661   0.01597   0.00723  -0.0773   0.6521   1.0000
   2.750   0.6881   0.01605   0.00725  -0.0762   0.6429   1.0000
   3.000   0.7089   0.01618   0.00735  -0.0749   0.6327   1.0000
   3.250   0.7293   0.01633   0.00749  -0.0736   0.6224   1.0000
   3.500   0.7518   0.01645   0.00755  -0.0726   0.6130   1.0000
   3.750   0.7720   0.01662   0.00772  -0.0712   0.6022   1.0000
   4.000   0.7926   0.01680   0.00789  -0.0699   0.5916   1.0000
   4.250   0.8147   0.01696   0.00801  -0.0688   0.5816   1.0000
   4.500   0.8352   0.01716   0.00821  -0.0675   0.5706   1.0000
   4.750   0.8555   0.01738   0.00844  -0.0661   0.5594   1.0000
   5.000   0.8771   0.01758   0.00864  -0.0650   0.5488   1.0000
   5.250   0.8988   0.01779   0.00883  -0.0638   0.5380   1.0000
   5.500   0.9186   0.01806   0.00913  -0.0624   0.5261   1.0000
   5.750   0.9394   0.01832   0.00940  -0.0612   0.5146   1.0000
   6.000   0.9607   0.01858   0.00967  -0.0601   0.5033   1.0000
   6.250   0.9816   0.01885   0.00994  -0.0589   0.4916   1.0000
   6.500   1.0012   0.01917   0.01030  -0.0575   0.4790   1.0000
   6.750   1.0209   0.01949   0.01068  -0.0562   0.4666   1.0000
   7.000   1.0407   0.01983   0.01103  -0.0548   0.4541   1.0000
   7.250   1.0601   0.02018   0.01140  -0.0535   0.4414   1.0000
   7.500   1.0791   0.02056   0.01178  -0.0521   0.4287   1.0000
   7.750   1.0970   0.02096   0.01224  -0.0505   0.4152   1.0000
   8.000   1.1141   0.02140   0.01273  -0.0489   0.4014   1.0000
   8.250   1.1306   0.02187   0.01323  -0.0471   0.3875   1.0000
   8.500   1.1462   0.02236   0.01376  -0.0453   0.3735   1.0000
   8.750   1.1609   0.02289   0.01434  -0.0434   0.3594   1.0000
   9.000   1.1738   0.02345   0.01494  -0.0412   0.3452   1.0000
   9.250   1.1852   0.02407   0.01558  -0.0388   0.3310   1.0000
   9.500   1.1958   0.02475   0.01629  -0.0365   0.3166   1.0000
   9.750   1.2058   0.02550   0.01708  -0.0342   0.3020   1.0000
  10.000   1.2149   0.02635   0.01795  -0.0319   0.2873   1.0000
  10.250   1.2231   0.02728   0.01891  -0.0296   0.2725   1.0000
  10.500   1.2304   0.02831   0.01997  -0.0274   0.2576   1.0000
  10.750   1.2367   0.02946   0.02114  -0.0253   0.2427   1.0000
  11.000   1.2421   0.03073   0.02244  -0.0232   0.2279   1.0000
  11.250   1.2465   0.03214   0.02388  -0.0213   0.2132   1.0000
  11.500   1.2500   0.03369   0.02545  -0.0194   0.1988   1.0000
  11.750   1.2526   0.03539   0.02717  -0.0177   0.1846   1.0000
  12.000   1.2542   0.03724   0.02905  -0.0161   0.1708   1.0000
  12.250   1.2548   0.03928   0.03111  -0.0147   0.1577   1.0000
  12.500   1.2543   0.04150   0.03336  -0.0134   0.1451   1.0000
  12.750   1.2526   0.04393   0.03580  -0.0123   0.1334   1.0000
  13.000   1.2502   0.04654   0.03845  -0.0114   0.1222   1.0000
  13.250   1.2479   0.04923   0.04121  -0.0106   0.1115   1.0000
  13.500   1.2445   0.05215   0.04418  -0.0100   0.1020   1.0000
  13.750   1.2391   0.05540   0.04746  -0.0096   0.0939   1.0000
  14.000   1.2342   0.05874   0.05086  -0.0095   0.0862   1.0000
  14.250   1.2290   0.06223   0.05443  -0.0094   0.0794   1.0000
  14.500   1.2217   0.06610   0.05834  -0.0097   0.0737   1.0000
  14.750   1.2162   0.06985   0.06219  -0.0100   0.0684   1.0000
  15.000   1.2087   0.07397   0.06639  -0.0106   0.0639   1.0000
  15.250   1.2010   0.07821   0.07069  -0.0113   0.0601   1.0000
  15.500   1.1952   0.08233   0.07493  -0.0121   0.0560   1.0000
  15.750   1.1866   0.08690   0.07956  -0.0132   0.0531   1.0000
  16.000   1.1799   0.09123   0.08399  -0.0142   0.0504   1.0000
  16.250   1.1748   0.09548   0.08837  -0.0153   0.0474   1.0000
  16.500   1.1681   0.10001   0.09299  -0.0167   0.0451   1.0000
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