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MRC-20 (mrc-20-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MRC-20 (mrc-20-il)
Reynolds number: 200,000
Max Cl/Cd: 68.42 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-20-il-200000-n5.txt
Download as CSV file: xf-mrc-20-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2869   0.08592   0.08222  -0.0853   0.9749   0.0287
  -9.500  -0.2903   0.07851   0.07480  -0.0932   0.9715   0.0286
  -9.000  -0.3615   0.06052   0.05623  -0.1015   0.9519   0.0183
  -8.750  -0.3541   0.05760   0.05322  -0.1026   0.9484   0.0181
  -8.500  -0.3515   0.05470   0.05019  -0.1022   0.9436   0.0178
  -8.250  -0.3531   0.05208   0.04741  -0.1001   0.9363   0.0176
  -8.000  -0.3440   0.04857   0.04367  -0.1001   0.9327   0.0173
  -7.750  -0.3438   0.04592   0.04081  -0.0971   0.9255   0.0171
  -7.500  -0.3360   0.04273   0.03735  -0.0954   0.9202   0.0169
  -7.250  -0.3209   0.03927   0.03354  -0.0946   0.9172   0.0167
  -7.000  -0.3158   0.03688   0.03089  -0.0912   0.9099   0.0167
  -6.750  -0.3007   0.03429   0.02796  -0.0895   0.9053   0.0173
  -6.500  -0.2800   0.03113   0.02429  -0.0884   0.9025   0.0179
  -6.250  -0.2543   0.02871   0.02149  -0.0884   0.9007   0.0180
  -6.000  -0.2454   0.02736   0.01992  -0.0848   0.8921   0.0180
  -5.750  -0.2190   0.02553   0.01781  -0.0845   0.8892   0.0181
  -5.500  -0.1892   0.02388   0.01586  -0.0849   0.8871   0.0183
  -5.250  -0.1582   0.02250   0.01439  -0.0857   0.8854   0.0186
  -5.000  -0.1452   0.02183   0.01368  -0.0829   0.8770   0.0190
  -4.750  -0.1171   0.02085   0.01263  -0.0830   0.8739   0.0195
  -4.500  -0.0871   0.01988   0.01158  -0.0835   0.8715   0.0201
  -4.250  -0.0678   0.01925   0.01089  -0.0819   0.8653   0.0211
  -4.000  -0.0447   0.01859   0.01017  -0.0810   0.8601   0.0224
  -3.750  -0.0168   0.01789   0.00948  -0.0812   0.8569   0.0238
  -3.500   0.0056   0.01728   0.00883  -0.0802   0.8517   0.0248
  -3.250   0.0257   0.01677   0.00826  -0.0787   0.8451   0.0259
  -3.000   0.0532   0.01611   0.00758  -0.0788   0.8413   0.0275
  -2.750   0.0750   0.01571   0.00715  -0.0777   0.8349   0.0297
  -2.500   0.0993   0.01530   0.00671  -0.0771   0.8287   0.0337
  -2.250   0.1295   0.01480   0.00615  -0.0776   0.8247   0.0398
  -2.000   0.1498   0.01451   0.00587  -0.0761   0.8165   0.0511
  -1.750   0.1749   0.01375   0.00541  -0.0759   0.8108   0.1435
  -1.500   0.1826   0.01212   0.00520  -0.0727   0.8029   0.5431
  -1.250   0.2072   0.01185   0.00512  -0.0719   0.7960   0.6129
  -1.000   0.2318   0.01167   0.00510  -0.0709   0.7890   0.6670
  -0.750   0.2568   0.01155   0.00504  -0.0701   0.7809   0.7017
  -0.500   0.2856   0.01145   0.00489  -0.0702   0.7734   0.7139
  -0.250   0.3135   0.01137   0.00477  -0.0702   0.7648   0.7235
   0.000   0.3414   0.01131   0.00466  -0.0702   0.7563   0.7345
   0.250   0.3699   0.01124   0.00456  -0.0703   0.7477   0.7464
   0.500   0.3963   0.01122   0.00452  -0.0699   0.7382   0.7590
   0.750   0.4258   0.01117   0.00442  -0.0702   0.7296   0.7725
   1.000   0.4507   0.01118   0.00443  -0.0696   0.7190   0.7871
   1.500   0.5051   0.01119   0.00440  -0.0692   0.6987   0.8193
   1.750   0.5306   0.01124   0.00446  -0.0687   0.6875   0.8370
   2.000   0.5576   0.01129   0.00450  -0.0685   0.6766   0.8549
   2.500   0.6139   0.01148   0.00465  -0.0685   0.6533   0.8913
   2.750   0.6438   0.01161   0.00476  -0.0690   0.6413   0.9089
   3.000   0.6752   0.01176   0.00486  -0.0699   0.6289   0.9251
   3.250   0.7074   0.01192   0.00497  -0.0709   0.6163   0.9402
   3.500   0.7408   0.01211   0.00512  -0.0723   0.6026   0.9533
   3.750   0.7743   0.01230   0.00527  -0.0738   0.5888   0.9654
   4.000   0.8077   0.01250   0.00543  -0.0754   0.5749   0.9767
   4.250   0.8417   0.01272   0.00561  -0.0771   0.5605   0.9869
   4.500   0.8765   0.01296   0.00580  -0.0790   0.5458   0.9956
   4.750   0.9018   0.01318   0.00597  -0.0790   0.5317   1.0000
   5.000   0.9149   0.01338   0.00611  -0.0762   0.5189   1.0000
   5.250   0.9281   0.01358   0.00627  -0.0735   0.5058   1.0000
   5.500   0.9418   0.01380   0.00644  -0.0710   0.4927   1.0000
   5.750   0.9561   0.01403   0.00664  -0.0685   0.4798   1.0000
   6.000   0.9702   0.01429   0.00686  -0.0660   0.4670   1.0000
   6.250   0.9838   0.01457   0.00709  -0.0635   0.4542   1.0000
   6.500   0.9982   0.01486   0.00735  -0.0611   0.4411   1.0000
   6.750   1.0135   0.01517   0.00764  -0.0590   0.4280   1.0000
   7.000   1.0291   0.01551   0.00797  -0.0570   0.4150   1.0000
   7.250   1.0448   0.01588   0.00831  -0.0551   0.4021   1.0000
   7.500   1.0602   0.01629   0.00869  -0.0531   0.3889   1.0000
   8.000   1.0911   0.01716   0.00955  -0.0495   0.3619   1.0000
   8.250   1.1066   0.01764   0.01001  -0.0477   0.3482   1.0000
   8.500   1.1216   0.01814   0.01052  -0.0459   0.3345   1.0000
   8.750   1.1361   0.01869   0.01106  -0.0441   0.3206   1.0000
   9.000   1.1499   0.01929   0.01165  -0.0423   0.3062   1.0000
   9.250   1.1631   0.01993   0.01228  -0.0404   0.2915   1.0000
   9.500   1.1757   0.02063   0.01296  -0.0385   0.2763   1.0000
   9.750   1.1877   0.02138   0.01370  -0.0366   0.2608   1.0000
  10.000   1.1989   0.02220   0.01449  -0.0347   0.2449   1.0000
  10.250   1.2095   0.02308   0.01536  -0.0328   0.2288   1.0000
  10.500   1.2194   0.02404   0.01630  -0.0309   0.2130   1.0000
  10.750   1.2287   0.02507   0.01730  -0.0290   0.1975   1.0000
  11.000   1.2374   0.02617   0.01838  -0.0272   0.1824   1.0000
  11.250   1.2456   0.02735   0.01954  -0.0254   0.1678   1.0000
  11.500   1.2531   0.02861   0.02078  -0.0236   0.1538   1.0000
  11.750   1.2600   0.02995   0.02212  -0.0219   0.1405   1.0000
  12.000   1.2663   0.03138   0.02354  -0.0202   0.1279   1.0000
  12.250   1.2719   0.03290   0.02506  -0.0186   0.1161   1.0000
  12.500   1.2768   0.03453   0.02669  -0.0170   0.1053   1.0000
  12.750   1.2807   0.03629   0.02846  -0.0155   0.0953   1.0000
  13.000   1.2841   0.03816   0.03035  -0.0142   0.0863   1.0000
  13.250   1.2882   0.04004   0.03227  -0.0130   0.0781   1.0000
  13.500   1.2909   0.04210   0.03437  -0.0118   0.0711   1.0000
  14.000   1.2948   0.04658   0.03896  -0.0099   0.0595   1.0000
  14.250   1.2948   0.04913   0.04155  -0.0092   0.0551   1.0000
  14.500   1.2961   0.05161   0.04413  -0.0085   0.0509   1.0000
  15.000   1.2948   0.05722   0.04991  -0.0077   0.0448   1.0000
  15.250   1.2931   0.06028   0.05305  -0.0075   0.0423   1.0000
  15.500   1.2888   0.06370   0.05653  -0.0075   0.0403   1.0000
  15.750   1.2878   0.06681   0.05978  -0.0075   0.0383   1.0000
  16.000   1.2849   0.07022   0.06330  -0.0077   0.0365   1.0000
  16.250   1.2798   0.07402   0.06718  -0.0082   0.0351   1.0000
  16.500   1.2739   0.07797   0.07123  -0.0087   0.0339   1.0000
  16.750   1.2707   0.08162   0.07501  -0.0093   0.0326   1.0000
  17.000   1.2664   0.08549   0.07901  -0.0101   0.0315   1.0000
  17.250   1.2612   0.08955   0.08318  -0.0110   0.0305   1.0000
  17.500   1.2549   0.09384   0.08756  -0.0121   0.0297   1.0000
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