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MRC-16 (mrc-16-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MRC-16 (mrc-16-il)
Reynolds number: 500,000
Max Cl/Cd: 102.09 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mrc-16-il-500000.txt
Download as CSV file: xf-mrc-16-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3817   0.09945   0.09716  -0.0500   1.0000   0.0272
 -10.750  -0.3793   0.09647   0.09421  -0.0508   1.0000   0.0276
 -10.500  -0.6395   0.04133   0.03807  -0.0820   0.9869   0.0177
 -10.250  -0.6354   0.03603   0.03228  -0.0843   0.9821   0.0176
 -10.000  -0.6272   0.03182   0.02766  -0.0849   0.9756   0.0177
  -9.750  -0.6071   0.02894   0.02451  -0.0861   0.9719   0.0180
  -9.500  -0.5860   0.02739   0.02281  -0.0862   0.9662   0.0184
  -9.250  -0.5613   0.02649   0.02185  -0.0866   0.9607   0.0190
  -9.000  -0.5378   0.02503   0.02020  -0.0868   0.9562   0.0196
  -8.750  -0.5212   0.02349   0.01840  -0.0853   0.9477   0.0201
  -8.500  -0.5007   0.02186   0.01648  -0.0845   0.9420   0.0206
  -8.250  -0.4809   0.02065   0.01504  -0.0832   0.9343   0.0210
  -8.000  -0.4585   0.01979   0.01396  -0.0823   0.9280   0.0214
  -7.750  -0.4387   0.01798   0.01200  -0.0812   0.9213   0.0221
  -7.500  -0.4160   0.01720   0.01117  -0.0804   0.9143   0.0228
  -7.250  -0.3920   0.01658   0.01048  -0.0798   0.9085   0.0237
  -7.000  -0.3684   0.01603   0.00986  -0.0791   0.9010   0.0247
  -6.750  -0.3433   0.01557   0.00928  -0.0785   0.8952   0.0258
  -6.500  -0.3208   0.01467   0.00829  -0.0776   0.8878   0.0269
  -6.250  -0.2971   0.01404   0.00764  -0.0769   0.8812   0.0282
  -6.000  -0.2724   0.01361   0.00717  -0.0763   0.8745   0.0297
  -5.750  -0.2474   0.01321   0.00669  -0.0758   0.8674   0.0313
  -5.500  -0.2237   0.01260   0.00602  -0.0750   0.8610   0.0334
  -5.250  -0.1986   0.01225   0.00567  -0.0745   0.8534   0.0360
  -4.750  -0.1486   0.01146   0.00479  -0.0735   0.8393   0.0426
  -4.500  -0.1220   0.01124   0.00450  -0.0732   0.8327   0.0469
  -4.250  -0.0972   0.01084   0.00413  -0.0726   0.8250   0.0542
  -4.000  -0.0715   0.01052   0.00379  -0.0722   0.8180   0.0640
  -3.750  -0.0459   0.01023   0.00353  -0.0718   0.8103   0.0795
  -3.500  -0.0205   0.00988   0.00327  -0.0713   0.8029   0.1080
  -3.250   0.0039   0.00946   0.00306  -0.0709   0.7952   0.1619
  -3.000   0.0277   0.00898   0.00285  -0.0703   0.7876   0.2450
  -2.750   0.0508   0.00849   0.00270  -0.0696   0.7798   0.3446
  -2.500   0.0739   0.00805   0.00257  -0.0689   0.7720   0.4436
  -2.250   0.0968   0.00768   0.00248  -0.0680   0.7640   0.5354
  -2.000   0.1198   0.00738   0.00242  -0.0669   0.7561   0.6183
  -1.750   0.1435   0.00717   0.00241  -0.0659   0.7479   0.6843
  -1.500   0.1681   0.00705   0.00239  -0.0651   0.7401   0.7362
  -1.250   0.1932   0.00698   0.00240  -0.0643   0.7316   0.7777
  -1.000   0.2188   0.00695   0.00240  -0.0636   0.7238   0.8116
  -0.750   0.2442   0.00693   0.00243  -0.0628   0.7151   0.8420
  -0.500   0.2700   0.00697   0.00246  -0.0620   0.7073   0.8687
  -0.250   0.2954   0.00701   0.00251  -0.0613   0.6982   0.8916
   0.000   0.3218   0.00709   0.00255  -0.0606   0.6901   0.9095
   0.250   0.3484   0.00716   0.00260  -0.0601   0.6810   0.9249
   0.500   0.3755   0.00725   0.00265  -0.0597   0.6725   0.9384
   0.750   0.4072   0.00737   0.00271  -0.0604   0.6634   0.9476
   1.000   0.4379   0.00746   0.00276  -0.0609   0.6543   0.9571
   1.250   0.4735   0.00760   0.00281  -0.0625   0.6452   0.9634
   1.500   0.5073   0.00769   0.00287  -0.0638   0.6352   0.9706
   1.750   0.5481   0.00780   0.00292  -0.0666   0.6255   0.9736
   2.000   0.5866   0.00792   0.00296  -0.0690   0.6153   0.9779
   2.250   0.6222   0.00801   0.00302  -0.0708   0.6047   0.9833
   2.500   0.6624   0.00810   0.00306  -0.0737   0.5941   0.9863
   2.750   0.7006   0.00821   0.00310  -0.0761   0.5834   0.9903
   3.000   0.7379   0.00829   0.00316  -0.0784   0.5720   0.9943
   3.250   0.7770   0.00837   0.00321  -0.0811   0.5607   0.9973
   3.500   0.8127   0.00848   0.00327  -0.0830   0.5494   1.0000
   3.750   0.8343   0.00858   0.00333  -0.0820   0.5387   1.0000
   4.000   0.8557   0.00868   0.00341  -0.0810   0.5279   1.0000
   4.250   0.8764   0.00880   0.00350  -0.0797   0.5175   1.0000
   4.750   0.9169   0.00907   0.00373  -0.0771   0.4953   1.0000
   5.000   0.9369   0.00922   0.00385  -0.0756   0.4842   1.0000
   5.250   0.9563   0.00940   0.00399  -0.0741   0.4730   1.0000
   5.500   0.9756   0.00958   0.00414  -0.0725   0.4615   1.0000
   5.750   0.9953   0.00975   0.00430  -0.0711   0.4495   1.0000
   6.000   1.0148   0.00994   0.00447  -0.0695   0.4377   1.0000
   6.250   1.0339   0.01016   0.00466  -0.0679   0.4256   1.0000
   6.500   1.0525   0.01040   0.00486  -0.0663   0.4130   1.0000
   6.750   1.0718   0.01064   0.00507  -0.0648   0.3999   1.0000
   7.000   1.0915   0.01088   0.00530  -0.0634   0.3865   1.0000
   7.250   1.1111   0.01115   0.00554  -0.0620   0.3726   1.0000
   7.500   1.1306   0.01145   0.00581  -0.0606   0.3583   1.0000
   7.750   1.1498   0.01177   0.00610  -0.0592   0.3434   1.0000
   8.000   1.1687   0.01212   0.00641  -0.0578   0.3279   1.0000
   8.250   1.1869   0.01250   0.00675  -0.0563   0.3119   1.0000
   8.500   1.2041   0.01291   0.00711  -0.0546   0.2954   1.0000
   8.750   1.2194   0.01336   0.00751  -0.0526   0.2788   1.0000
   9.000   1.2347   0.01384   0.00793  -0.0507   0.2620   1.0000
   9.250   1.2500   0.01435   0.00841  -0.0489   0.2449   1.0000
   9.500   1.2648   0.01492   0.00892  -0.0471   0.2278   1.0000
   9.750   1.2790   0.01555   0.00949  -0.0452   0.2108   1.0000
  10.000   1.2923   0.01624   0.01012  -0.0434   0.1940   1.0000
  10.250   1.3047   0.01701   0.01083  -0.0415   0.1775   1.0000
  10.500   1.3166   0.01784   0.01160  -0.0396   0.1613   1.0000
  10.750   1.3283   0.01871   0.01242  -0.0378   0.1454   1.0000
  11.000   1.3390   0.01967   0.01333  -0.0360   0.1300   1.0000
  11.250   1.3485   0.02073   0.01434  -0.0342   0.1151   1.0000
  11.500   1.3571   0.02189   0.01545  -0.0323   0.1011   1.0000
  11.750   1.3647   0.02315   0.01667  -0.0305   0.0881   1.0000
  12.000   1.3714   0.02453   0.01801  -0.0288   0.0761   1.0000
  12.250   1.3773   0.02600   0.01945  -0.0271   0.0655   1.0000
  12.500   1.3824   0.02759   0.02102  -0.0255   0.0562   1.0000
  12.750   1.3866   0.02931   0.02274  -0.0239   0.0485   1.0000
  13.000   1.3895   0.03120   0.02463  -0.0224   0.0420   1.0000
  13.250   1.3919   0.03318   0.02662  -0.0211   0.0369   1.0000
  13.500   1.3949   0.03518   0.02868  -0.0199   0.0329   1.0000
  13.750   1.3942   0.03759   0.03111  -0.0187   0.0296   1.0000
  14.000   1.3969   0.03975   0.03336  -0.0178   0.0271   1.0000
  14.250   1.3972   0.04224   0.03590  -0.0171   0.0251   1.0000
  14.500   1.3925   0.04535   0.03907  -0.0163   0.0234   1.0000
  14.750   1.3946   0.04781   0.04164  -0.0159   0.0221   1.0000
  15.000   1.3943   0.05063   0.04454  -0.0156   0.0209   1.0000
  15.250   1.3901   0.05397   0.04796  -0.0154   0.0199   1.0000
  15.500   1.3785   0.05828   0.05235  -0.0154   0.0190   1.0000
  15.750   1.3783   0.06133   0.05552  -0.0155   0.0184   1.0000
  16.000   1.3758   0.06474   0.05905  -0.0158   0.0177   1.0000
  16.250   1.3720   0.06838   0.06278  -0.0162   0.0171   1.0000
  16.500   1.3672   0.07220   0.06670  -0.0168   0.0165   1.0000
  16.750   1.3597   0.07646   0.07104  -0.0175   0.0161   1.0000
  17.000   1.3487   0.08126   0.07592  -0.0185   0.0156   1.0000
  17.250   1.3343   0.08661   0.08136  -0.0196   0.0152   1.0000
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