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Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Supermarine 371-I (root) (supermarine371i-il)
Reynolds number: 50,000
Max Cl/Cd: 27.6 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-supermarine371i-il-50000-n5.txt
Download as CSV file: xf-supermarine371i-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Supermarine 371-I (root)                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5961   0.09049   0.08319  -0.0496   1.0000   0.0550
 -11.500  -0.6134   0.08413   0.07681  -0.0532   1.0000   0.0547
 -11.250  -0.6329   0.07843   0.07107  -0.0560   1.0000   0.0544
 -11.000  -0.6551   0.07334   0.06590  -0.0577   1.0000   0.0542
 -10.750  -0.6772   0.06904   0.06148  -0.0580   1.0000   0.0541
 -10.500  -0.6978   0.06542   0.05773  -0.0568   1.0000   0.0541
 -10.250  -0.7163   0.06240   0.05456  -0.0543   1.0000   0.0540
 -10.000  -0.7326   0.05933   0.05129  -0.0515   1.0000   0.0542
  -9.750  -0.7460   0.05639   0.04809  -0.0482   1.0000   0.0545
  -9.500  -0.7570   0.05373   0.04517  -0.0446   1.0000   0.0547
  -9.250  -0.7669   0.05142   0.04260  -0.0404   1.0000   0.0549
  -9.000  -0.7757   0.04934   0.04026  -0.0360   1.0000   0.0552
  -8.750  -0.7787   0.04741   0.03818  -0.0322   1.0000   0.0557
  -8.500  -0.7793   0.04564   0.03625  -0.0287   1.0000   0.0564
  -8.250  -0.7773   0.04395   0.03439  -0.0254   1.0000   0.0573
  -8.000  -0.7731   0.04244   0.03271  -0.0224   1.0000   0.0587
  -7.750  -0.7670   0.04097   0.03100  -0.0196   1.0000   0.0609
  -7.500  -0.7437   0.03882   0.02843  -0.0197   0.9956   0.0644
  -7.250  -0.7163   0.03702   0.02646  -0.0204   0.9911   0.0674
  -7.000  -0.6880   0.03558   0.02489  -0.0210   0.9868   0.0708
  -6.750  -0.6586   0.03430   0.02340  -0.0217   0.9830   0.0767
  -6.500  -0.6316   0.03334   0.02227  -0.0220   0.9783   0.0842
  -6.250  -0.6011   0.03228   0.02109  -0.0228   0.9746   0.0932
  -6.000  -0.5728   0.03125   0.01994  -0.0232   0.9708   0.1066
  -5.750  -0.5484   0.03010   0.01873  -0.0230   0.9665   0.1234
  -5.500  -0.5267   0.02884   0.01761  -0.0228   0.9624   0.1474
  -5.250  -0.5084   0.02781   0.01674  -0.0221   0.9580   0.1784
  -5.000  -0.4927   0.02686   0.01602  -0.0209   0.9530   0.2182
  -4.750  -0.4760   0.02573   0.01533  -0.0202   0.9485   0.2854
  -4.500  -0.4655   0.02454   0.01487  -0.0179   0.9438   0.3968
  -4.250  -0.4443   0.02478   0.01630  -0.0139   0.9409   0.5830
  -4.000  -0.4313   0.02513   0.01650  -0.0107   0.9361   0.6717
  -3.750  -0.4084   0.02563   0.01679  -0.0090   0.9327   0.7157
  -3.500  -0.3882   0.02601   0.01697  -0.0070   0.9287   0.7414
  -3.250  -0.3689   0.02631   0.01705  -0.0051   0.9244   0.7631
  -3.000  -0.3423   0.02685   0.01742  -0.0039   0.9213   0.7877
  -2.750  -0.3094   0.02754   0.01794  -0.0035   0.9192   0.8138
  -2.500  -0.2741   0.02809   0.01828  -0.0040   0.9171   0.8367
  -2.250  -0.2449   0.02844   0.01848  -0.0039   0.9140   0.8546
  -2.000  -0.2132   0.02875   0.01864  -0.0045   0.9109   0.8699
  -1.750  -0.1752   0.02905   0.01877  -0.0064   0.9085   0.8840
  -1.500  -0.1265   0.02938   0.01894  -0.0103   0.9069   0.8975
  -1.250  -0.0706   0.02963   0.01904  -0.0159   0.9056   0.9094
  -1.000  -0.0260   0.02974   0.01904  -0.0197   0.9035   0.9192
  -0.750   0.0169   0.02982   0.01902  -0.0234   0.9014   0.9273
  -0.500   0.0398   0.02988   0.01903  -0.0235   0.8967   0.9344
  -0.250   0.0701   0.02993   0.01904  -0.0250   0.8924   0.9401
   0.000   0.1000   0.03002   0.01909  -0.0264   0.8885   0.9461
   0.250   0.1401   0.03007   0.01912  -0.0297   0.8852   0.9499
   0.500   0.1608   0.03021   0.01926  -0.0295   0.8789   0.9565
   0.750   0.1952   0.03032   0.01939  -0.0318   0.8744   0.9617
   1.000   0.2401   0.03040   0.01950  -0.0358   0.8712   0.9660
   1.250   0.2600   0.03062   0.01977  -0.0356   0.8638   0.9737
   1.500   0.2990   0.03073   0.01995  -0.0386   0.8590   0.9780
   1.750   0.3319   0.03090   0.02018  -0.0405   0.8536   0.9826
   2.000   0.3583   0.03109   0.02048  -0.0413   0.8461   0.9876
   2.250   0.3995   0.03115   0.02064  -0.0444   0.8410   0.9904
   2.500   0.4223   0.03138   0.02098  -0.0446   0.8311   0.9963
   2.750   0.4669   0.03129   0.02105  -0.0478   0.8246   0.9990
   3.000   0.4782   0.03149   0.02135  -0.0455   0.8127   1.0000
   3.250   0.4886   0.03165   0.02161  -0.0428   0.8011   1.0000
   3.500   0.5126   0.03160   0.02170  -0.0422   0.7912   1.0000
   3.750   0.5362   0.03145   0.02172  -0.0412   0.7800   1.0000
   4.000   0.5479   0.03139   0.02178  -0.0383   0.7660   1.0000
   4.250   0.5626   0.03118   0.02170  -0.0356   0.7514   1.0000
   4.500   0.5789   0.03084   0.02150  -0.0330   0.7362   1.0000
   4.750   0.5991   0.03024   0.02108  -0.0306   0.7197   1.0000
   5.000   0.6185   0.02945   0.02044  -0.0278   0.7010   1.0000
   5.250   0.6169   0.02922   0.02030  -0.0223   0.6796   1.0000
   5.500   0.6353   0.02828   0.01952  -0.0191   0.6575   1.0000
   5.750   0.6288   0.02828   0.01957  -0.0133   0.6320   1.0000
   6.000   0.6276   0.02816   0.01952  -0.0081   0.6036   1.0000
   6.250   0.6358   0.02773   0.01921  -0.0040   0.5678   1.0000
   6.500   0.6666   0.02633   0.01780  -0.0017   0.5065   1.0000
   6.750   0.7042   0.02551   0.01629  -0.0002   0.3931   1.0000
   7.000   0.7054   0.02647   0.01672   0.0041   0.3258   1.0000
   7.250   0.7044   0.02770   0.01758   0.0080   0.2719   1.0000
   7.500   0.7058   0.02906   0.01858   0.0112   0.2281   1.0000
   7.750   0.7109   0.03047   0.01971   0.0137   0.1939   1.0000
   8.000   0.7192   0.03185   0.02088   0.0157   0.1660   1.0000
   8.250   0.7295   0.03326   0.02207   0.0175   0.1451   1.0000
   8.500   0.7443   0.03457   0.02335   0.0188   0.1271   1.0000
   8.750   0.7620   0.03589   0.02466   0.0199   0.1125   1.0000
   9.000   0.7837   0.03723   0.02597   0.0207   0.1004   1.0000
   9.250   0.8082   0.03857   0.02736   0.0211   0.0898   1.0000
   9.500   0.8393   0.04015   0.02917   0.0210   0.0811   1.0000
   9.750   0.8656   0.04189   0.03088   0.0209   0.0747   1.0000
  10.000   0.8881   0.04386   0.03323   0.0214   0.0688   1.0000
  10.250   0.9116   0.04601   0.03554   0.0215   0.0654   1.0000
  10.500   0.9313   0.04850   0.03815   0.0218   0.0623   1.0000
  10.750   0.9369   0.05106   0.04116   0.0238   0.0597   1.0000
  11.000   0.9401   0.05361   0.04402   0.0256   0.0573   1.0000
  11.250   0.9419   0.05624   0.04690   0.0273   0.0556   1.0000
  11.500   0.9412   0.05915   0.05004   0.0289   0.0545   1.0000
  11.750   0.9376   0.06222   0.05337   0.0304   0.0537   1.0000
  12.000   0.9310   0.06550   0.05686   0.0316   0.0531   1.0000
  12.250   0.9230   0.06899   0.06052   0.0325   0.0525   1.0000
  12.500   0.9139   0.07279   0.06447   0.0330   0.0519   1.0000
  12.750   0.8955   0.07719   0.06906   0.0330   0.0518   1.0000
  13.000   0.8724   0.08232   0.07440   0.0321   0.0518   1.0000
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