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MRC-20 (mrc-20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MRC-20 (mrc-20-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.08 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-20-il-1000000-n5.txt
Download as CSV file: xf-mrc-20-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2735   0.09326   0.09135  -0.0874   0.9568   0.0070
 -11.250  -0.2767   0.08832   0.08641  -0.0898   0.9534   0.0070
  -9.750  -0.5393   0.02222   0.01796  -0.0993   0.9093   0.0070
  -9.500  -0.5223   0.02064   0.01615  -0.0982   0.9054   0.0071
  -9.250  -0.5027   0.01948   0.01480  -0.0974   0.9021   0.0072
  -9.000  -0.4817   0.01850   0.01365  -0.0967   0.8987   0.0072
  -8.750  -0.4604   0.01754   0.01256  -0.0961   0.8947   0.0073
  -8.500  -0.4404   0.01632   0.01118  -0.0952   0.8905   0.0074
  -8.250  -0.4178   0.01558   0.01033  -0.0946   0.8869   0.0076
  -8.000  -0.3944   0.01499   0.00966  -0.0942   0.8831   0.0077
  -7.750  -0.3707   0.01446   0.00908  -0.0938   0.8786   0.0078
  -7.500  -0.3465   0.01401   0.00856  -0.0934   0.8741   0.0079
  -7.250  -0.3223   0.01353   0.00801  -0.0930   0.8700   0.0080
  -7.000  -0.2981   0.01308   0.00752  -0.0926   0.8653   0.0081
  -6.750  -0.2739   0.01265   0.00703  -0.0921   0.8601   0.0083
  -6.500  -0.2496   0.01224   0.00655  -0.0917   0.8552   0.0084
  -6.250  -0.2253   0.01185   0.00611  -0.0912   0.8500   0.0086
  -6.000  -0.2010   0.01149   0.00569  -0.0907   0.8441   0.0088
  -5.750  -0.1763   0.01117   0.00531  -0.0903   0.8387   0.0090
  -5.500  -0.1514   0.01088   0.00497  -0.0899   0.8325   0.0093
  -5.250  -0.1265   0.01062   0.00466  -0.0895   0.8261   0.0095
  -5.000  -0.1024   0.01028   0.00427  -0.0889   0.8198   0.0097
  -4.750  -0.0783   0.00997   0.00391  -0.0884   0.8124   0.0101
  -4.500  -0.0533   0.00975   0.00366  -0.0880   0.8054   0.0104
  -4.250  -0.0281   0.00955   0.00343  -0.0876   0.7974   0.0108
  -4.000  -0.0029   0.00938   0.00320  -0.0872   0.7897   0.0112
  -3.750   0.0223   0.00921   0.00300  -0.0868   0.7808   0.0116
  -3.500   0.0477   0.00907   0.00281  -0.0864   0.7719   0.0120
  -3.250   0.0724   0.00893   0.00261  -0.0858   0.7620   0.0125
  -3.000   0.0977   0.00880   0.00245  -0.0854   0.7518   0.0132
  -2.750   0.1229   0.00871   0.00232  -0.0850   0.7414   0.0142
  -2.500   0.1479   0.00864   0.00219  -0.0845   0.7303   0.0155
  -2.250   0.1732   0.00856   0.00209  -0.0841   0.7197   0.0174
  -2.000   0.1983   0.00850   0.00199  -0.0836   0.7094   0.0200
  -1.750   0.2231   0.00845   0.00191  -0.0831   0.6982   0.0252
  -1.500   0.2483   0.00837   0.00184  -0.0827   0.6875   0.0361
  -1.250   0.2726   0.00828   0.00178  -0.0821   0.6765   0.0621
  -1.000   0.2951   0.00806   0.00172  -0.0813   0.6653   0.1348
  -0.750   0.3072   0.00686   0.00149  -0.0788   0.6545   0.4644
  -0.500   0.3308   0.00676   0.00150  -0.0781   0.6435   0.5157
  -0.250   0.3542   0.00669   0.00152  -0.0774   0.6321   0.5633
   0.000   0.3783   0.00665   0.00156  -0.0767   0.6202   0.6011
   0.250   0.4040   0.00671   0.00158  -0.0764   0.6089   0.6106
   0.500   0.4293   0.00678   0.00160  -0.0760   0.5973   0.6170
   0.750   0.4545   0.00686   0.00163  -0.0756   0.5853   0.6239
   1.000   0.4802   0.00693   0.00167  -0.0753   0.5733   0.6305
   1.250   0.5054   0.00701   0.00171  -0.0749   0.5615   0.6385
   2.000   0.5802   0.00729   0.00190  -0.0736   0.5239   0.6648
   2.250   0.6049   0.00738   0.00197  -0.0731   0.5116   0.6747
   2.500   0.6295   0.00749   0.00205  -0.0726   0.4993   0.6848
   2.750   0.6536   0.00761   0.00215  -0.0721   0.4862   0.6971
   3.000   0.6778   0.00772   0.00225  -0.0715   0.4731   0.7104
   3.250   0.7019   0.00782   0.00235  -0.0710   0.4600   0.7243
   3.500   0.7253   0.00794   0.00247  -0.0703   0.4475   0.7390
   3.750   0.7480   0.00806   0.00259  -0.0694   0.4347   0.7551
   4.000   0.7704   0.00819   0.00272  -0.0685   0.4222   0.7737
   4.250   0.7932   0.00831   0.00287  -0.0677   0.4093   0.7946
   4.500   0.8163   0.00844   0.00303  -0.0670   0.3970   0.8165
   4.750   0.8391   0.00859   0.00320  -0.0662   0.3849   0.8389
   5.000   0.8613   0.00875   0.00339  -0.0653   0.3730   0.8642
   5.250   0.8831   0.00890   0.00359  -0.0643   0.3611   0.8919
   5.500   0.9044   0.00907   0.00380  -0.0631   0.3493   0.9220
   5.750   0.9277   0.00929   0.00403  -0.0624   0.3372   0.9515
   6.000   0.9573   0.00957   0.00427  -0.0633   0.3233   0.9745
   6.250   0.9878   0.00987   0.00452  -0.0645   0.3087   0.9915
   6.500   1.0132   0.01017   0.00476  -0.0645   0.2947   1.0000
   7.000   1.0509   0.01076   0.00525  -0.0617   0.2678   1.0000
   7.250   1.0701   0.01109   0.00552  -0.0605   0.2537   1.0000
   7.500   1.0889   0.01146   0.00582  -0.0592   0.2391   1.0000
   7.750   1.1069   0.01186   0.00616  -0.0578   0.2235   1.0000
   8.000   1.1246   0.01231   0.00653  -0.0564   0.2072   1.0000
   8.250   1.1417   0.01279   0.00693  -0.0549   0.1902   1.0000
   8.500   1.1586   0.01329   0.00736  -0.0534   0.1742   1.0000
   8.750   1.1755   0.01380   0.00780  -0.0520   0.1594   1.0000
   9.000   1.1920   0.01434   0.00828  -0.0505   0.1448   1.0000
   9.250   1.2077   0.01492   0.00879  -0.0490   0.1309   1.0000
   9.500   1.2233   0.01553   0.00933  -0.0475   0.1174   1.0000
   9.750   1.2384   0.01616   0.00991  -0.0459   0.1052   1.0000
  10.000   1.2532   0.01682   0.01052  -0.0444   0.0942   1.0000
  10.250   1.2675   0.01752   0.01117  -0.0428   0.0835   1.0000
  10.500   1.2813   0.01825   0.01187  -0.0412   0.0742   1.0000
  10.750   1.2956   0.01897   0.01257  -0.0398   0.0662   1.0000
  11.000   1.3093   0.01973   0.01330  -0.0383   0.0590   1.0000
  11.250   1.3224   0.02054   0.01410  -0.0368   0.0522   1.0000
  11.500   1.3347   0.02142   0.01496  -0.0352   0.0463   1.0000
  11.750   1.3470   0.02231   0.01584  -0.0337   0.0412   1.0000
  12.000   1.3597   0.02318   0.01673  -0.0323   0.0373   1.0000
  12.250   1.3713   0.02416   0.01771  -0.0309   0.0338   1.0000
  12.500   1.3832   0.02513   0.01871  -0.0295   0.0308   1.0000
  12.750   1.3940   0.02619   0.01979  -0.0281   0.0281   1.0000
  13.000   1.4048   0.02728   0.02090  -0.0268   0.0257   1.0000
  13.250   1.4147   0.02846   0.02211  -0.0255   0.0238   1.0000
  13.500   1.4254   0.02963   0.02332  -0.0244   0.0223   1.0000
  13.750   1.4346   0.03094   0.02467  -0.0231   0.0209   1.0000
  14.000   1.4436   0.03228   0.02606  -0.0220   0.0198   1.0000
  14.250   1.4528   0.03366   0.02748  -0.0210   0.0187   1.0000
  14.500   1.4605   0.03519   0.02907  -0.0199   0.0177   1.0000
  14.750   1.4670   0.03689   0.03080  -0.0189   0.0167   1.0000
  15.000   1.4748   0.03850   0.03248  -0.0181   0.0161   1.0000
  15.250   1.4815   0.04025   0.03429  -0.0173   0.0154   1.0000
  15.500   1.4870   0.04214   0.03624  -0.0165   0.0148   1.0000
  15.750   1.4913   0.04421   0.03836  -0.0158   0.0142   1.0000
  16.000   1.4944   0.04645   0.04067  -0.0151   0.0137   1.0000
  16.250   1.4991   0.04859   0.04289  -0.0147   0.0133   1.0000
  16.500   1.5025   0.05089   0.04526  -0.0143   0.0130   1.0000
  16.750   1.5048   0.05336   0.04781  -0.0139   0.0126   1.0000
  17.000   1.5060   0.05600   0.05052  -0.0137   0.0122   1.0000
  17.250   1.5060   0.05883   0.05343  -0.0136   0.0119   1.0000
  17.500   1.5048   0.06187   0.05654  -0.0135   0.0115   1.0000
  17.750   1.5019   0.06515   0.05990  -0.0136   0.0112   1.0000
  18.000   1.4996   0.06841   0.06325  -0.0138   0.0110   1.0000
  18.250   1.4974   0.07172   0.06666  -0.0141   0.0108   1.0000
  18.500   1.4942   0.07522   0.07026  -0.0146   0.0106   1.0000
  18.750   1.4899   0.07891   0.07404  -0.0151   0.0104   1.0000
  19.000   1.4846   0.08278   0.07800  -0.0158   0.0102   1.0000
  19.250   1.4783   0.08681   0.08212  -0.0166   0.0100   1.0000
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