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MRC-20 (mrc-20-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MRC-20 (mrc-20-il)
Reynolds number: 50,000
Max Cl/Cd: 29.35 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-20-il-50000-n5.txt
Download as CSV file: xf-mrc-20-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3754   0.12975   0.12279  -0.0412   1.0000   0.1256
 -10.500  -0.3825   0.12724   0.12036  -0.0409   1.0000   0.1295
 -10.250  -0.4291   0.12613   0.11947  -0.0437   1.0000   0.1341
 -10.000  -0.4113   0.12173   0.11508  -0.0411   1.0000   0.1362
  -9.750  -0.4044   0.11879   0.11217  -0.0391   1.0000   0.1389
  -9.500  -0.4074   0.11613   0.10957  -0.0378   1.0000   0.1418
  -9.250  -0.4178   0.11347   0.10700  -0.0371   1.0000   0.1453
  -8.750  -0.3825   0.09908   0.09320  -0.0385   1.0000   0.0696
  -8.500  -0.4006   0.09412   0.08828  -0.0395   1.0000   0.0661
  -8.250  -0.4334   0.08699   0.08108  -0.0439   0.9973   0.0605
  -8.000  -0.4405   0.08216   0.07621  -0.0456   0.9930   0.0588
  -7.750  -0.4582   0.07766   0.07164  -0.0461   0.9872   0.0575
  -7.500  -0.5711   0.08279   0.07625  -0.0368   0.9981   0.0593
  -7.250  -0.5651   0.07801   0.07126  -0.0388   0.9924   0.0564
  -7.000  -0.5617   0.07267   0.06533  -0.0406   0.9851   0.0514
  -6.750  -0.5490   0.06899   0.06149  -0.0413   0.9794   0.0503
  -6.500  -0.5339   0.06527   0.05749  -0.0424   0.9741   0.0492
  -6.250  -0.5206   0.06189   0.05378  -0.0425   0.9679   0.0483
  -6.000  -0.5021   0.05869   0.05020  -0.0431   0.9623   0.0482
  -5.750  -0.4838   0.05589   0.04701  -0.0431   0.9566   0.0485
  -5.500  -0.4634   0.05327   0.04398  -0.0432   0.9506   0.0490
  -5.250  -0.4362   0.05070   0.04096  -0.0442   0.9463   0.0493
  -5.000  -0.4167   0.04852   0.03841  -0.0433   0.9396   0.0492
  -4.750  -0.3890   0.04633   0.03582  -0.0438   0.9345   0.0489
  -4.500  -0.3564   0.04432   0.03339  -0.0448   0.9305   0.0490
  -4.250  -0.3336   0.04273   0.03150  -0.0440   0.9238   0.0493
  -4.000  -0.3011   0.04120   0.02965  -0.0448   0.9190   0.0503
  -3.750  -0.2664   0.03994   0.02805  -0.0458   0.9148   0.0525
  -3.500  -0.2425   0.03883   0.02699  -0.0453   0.9080   0.0550
  -3.250  -0.2084   0.03783   0.02592  -0.0461   0.9033   0.0574
  -3.000  -0.1775   0.03701   0.02495  -0.0462   0.8982   0.0597
  -2.750  -0.1536   0.03630   0.02415  -0.0455   0.8911   0.0634
  -2.500  -0.1215   0.03552   0.02330  -0.0465   0.8863   0.0696
  -2.250  -0.1019   0.03495   0.02258  -0.0453   0.8779   0.0745
  -2.000  -0.0710   0.03418   0.02170  -0.0464   0.8722   0.0856
  -1.750  -0.0487   0.03354   0.02099  -0.0459   0.8644   0.1008
  -1.250  -0.0150   0.03034   0.02064  -0.0409   0.8525   0.7098
  -1.000  -0.0056   0.03058   0.02121  -0.0345   0.8441   0.8142
  -0.500   0.0717   0.03153   0.02188  -0.0355   0.8316   0.9236
  -0.250   0.1216   0.03159   0.02167  -0.0402   0.8262   0.9369
   0.000   0.1630   0.03176   0.02164  -0.0438   0.8179   0.9528
   0.250   0.2137   0.03181   0.02148  -0.0489   0.8117   0.9672
   0.500   0.2622   0.03189   0.02138  -0.0539   0.8046   0.9826
   0.750   0.3116   0.03192   0.02128  -0.0591   0.7969   0.9983
   1.250   0.3441   0.03153   0.02062  -0.0564   0.7787   1.0000
   1.500   0.3506   0.03164   0.02061  -0.0533   0.7666   1.0000
   1.750   0.3853   0.03133   0.02017  -0.0546   0.7614   1.0000
   2.000   0.3941   0.03161   0.02036  -0.0519   0.7488   1.0000
   2.250   0.4119   0.03180   0.02045  -0.0505   0.7386   1.0000
   2.500   0.4430   0.03162   0.02019  -0.0510   0.7317   1.0000
   2.750   0.4587   0.03195   0.02045  -0.0494   0.7203   1.0000
   3.000   0.4945   0.03160   0.02004  -0.0504   0.7148   1.0000
   3.250   0.5091   0.03202   0.02042  -0.0486   0.7027   1.0000
   3.500   0.5482   0.03154   0.01991  -0.0501   0.6978   1.0000
   3.750   0.5618   0.03204   0.02039  -0.0481   0.6852   1.0000
   4.000   0.5828   0.03228   0.02062  -0.0472   0.6747   1.0000
   4.250   0.6166   0.03198   0.02031  -0.0478   0.6676   1.0000
   4.500   0.6337   0.03240   0.02076  -0.0463   0.6557   1.0000
   4.750   0.6737   0.03182   0.02019  -0.0477   0.6500   1.0000
   5.250   0.7104   0.03261   0.02104  -0.0450   0.6264   1.0000
   5.500   0.7464   0.03219   0.02066  -0.0458   0.6186   1.0000
   5.750   0.7625   0.03271   0.02121  -0.0442   0.6060   1.0000
   6.000   0.7885   0.03277   0.02132  -0.0438   0.5957   1.0000
   6.250   0.8214   0.03251   0.02113  -0.0441   0.5863   1.0000
   6.500   0.8375   0.03305   0.02173  -0.0426   0.5735   1.0000
   6.750   0.8609   0.03326   0.02200  -0.0418   0.5621   1.0000
   7.000   0.8989   0.03278   0.02159  -0.0428   0.5527   1.0000
   7.250   0.9124   0.03345   0.02234  -0.0408   0.5392   1.0000
   7.500   0.9298   0.03396   0.02293  -0.0394   0.5264   1.0000
   7.750   0.9530   0.03420   0.02325  -0.0386   0.5143   1.0000
   8.000   0.9843   0.03404   0.02315  -0.0387   0.5028   1.0000
   8.250   1.0009   0.03459   0.02379  -0.0372   0.4894   1.0000
   8.500   1.0146   0.03530   0.02459  -0.0354   0.4758   1.0000
   8.750   1.0307   0.03590   0.02530  -0.0339   0.4625   1.0000
   9.000   1.0491   0.03639   0.02587  -0.0326   0.4493   1.0000
   9.250   1.0691   0.03678   0.02633  -0.0314   0.4359   1.0000
   9.500   1.0898   0.03713   0.02675  -0.0304   0.4225   1.0000
   9.750   1.1016   0.03795   0.02766  -0.0284   0.4084   1.0000
  10.000   1.1101   0.03897   0.02879  -0.0263   0.3943   1.0000
  10.500   1.1286   0.04098   0.03100  -0.0223   0.3662   1.0000
  10.750   1.1377   0.04201   0.03212  -0.0203   0.3521   1.0000
  11.000   1.1460   0.04310   0.03329  -0.0184   0.3380   1.0000
  11.250   1.1534   0.04426   0.03452  -0.0165   0.3239   1.0000
  11.500   1.1595   0.04552   0.03585  -0.0146   0.3097   1.0000
  11.750   1.1647   0.04688   0.03726  -0.0127   0.2956   1.0000
  12.000   1.1669   0.04850   0.03896  -0.0108   0.2816   1.0000
  12.250   1.1656   0.05052   0.04109  -0.0089   0.2678   1.0000
  12.500   1.1641   0.05265   0.04330  -0.0073   0.2541   1.0000
  12.750   1.1624   0.05488   0.04563  -0.0058   0.2407   1.0000
  13.000   1.1604   0.05723   0.04805  -0.0045   0.2276   1.0000
  13.250   1.1583   0.05967   0.05055  -0.0033   0.2149   1.0000
  13.500   1.1561   0.06220   0.05310  -0.0023   0.2025   1.0000
  13.750   1.1543   0.06474   0.05564  -0.0015   0.1906   1.0000
  14.000   1.1484   0.06799   0.05901  -0.0010   0.1791   1.0000
  14.250   1.1425   0.07142   0.06254  -0.0007   0.1683   1.0000
  14.500   1.1381   0.07470   0.06585  -0.0005   0.1582   1.0000
  14.750   1.1364   0.07758   0.06869  -0.0003   0.1486   1.0000
  15.000   1.1279   0.08179   0.07310  -0.0007   0.1396   1.0000
  15.250   1.1233   0.08542   0.07677  -0.0010   0.1316   1.0000
  15.500   1.1203   0.08883   0.08020  -0.0013   0.1238   1.0000
  15.750   1.1120   0.09338   0.08491  -0.0022   0.1171   1.0000
  16.000   1.1120   0.09638   0.08789  -0.0025   0.1105   1.0000
  16.250   1.1015   0.10159   0.09331  -0.0040   0.1052   1.0000
  16.500   1.0976   0.10556   0.09735  -0.0050   0.0998   1.0000
  16.750   1.0935   0.10970   0.10156  -0.0062   0.0953   1.0000
  17.000   1.0777   0.11639   0.10851  -0.0089   0.0919   1.0000
  17.250   1.0761   0.12015   0.11232  -0.0102   0.0877   1.0000
  17.500   1.0698   0.12508   0.11734  -0.0121   0.0844   1.0000
  17.750   1.0375   0.13621   0.12874  -0.0180   0.0831   1.0000
  18.000   0.9830   0.15435   0.14702  -0.0281   0.0823   1.0000
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