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Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Supermarine 371-I (root) (supermarine371i-il)
Reynolds number: 100,000
Max Cl/Cd: 46.75 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-supermarine371i-il-100000.txt
Download as CSV file: xf-supermarine371i-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3861   0.12898   0.12420  -0.0251   1.0000   0.1244
 -12.500  -0.4028   0.12611   0.12137  -0.0284   1.0000   0.1288
 -12.250  -0.4406   0.12266   0.11802  -0.0340   1.0000   0.1301
 -12.000  -0.3971   0.11785   0.11313  -0.0305   1.0000   0.1327
 -11.750  -0.3856   0.11474   0.11002  -0.0304   1.0000   0.1375
 -11.500  -0.4000   0.11073   0.10604  -0.0332   1.0000   0.1429
 -11.250  -0.4440   0.10519   0.10061  -0.0394   1.0000   0.1445
 -11.000  -0.3958   0.10235   0.09771  -0.0349   1.0000   0.1489
 -10.750  -0.3941   0.09851   0.09388  -0.0357   1.0000   0.1528
 -10.500  -0.4436   0.09166   0.08718  -0.0420   1.0000   0.1598
 -10.250  -0.4145   0.08871   0.08418  -0.0396   1.0000   0.1623
 -10.000  -0.5736   0.05884   0.05413  -0.0589   1.0000   0.0855
  -9.750  -0.5980   0.05449   0.04973  -0.0577   1.0000   0.0834
  -9.500  -0.6975   0.06299   0.05785  -0.0496   1.0000   0.0856
  -9.250  -0.7210   0.06093   0.05578  -0.0443   1.0000   0.0836
  -9.000  -0.7524   0.05949   0.05427  -0.0374   1.0000   0.0818
  -8.750  -0.8031   0.05623   0.05045  -0.0284   1.0000   0.0755
  -8.500  -0.8091   0.05343   0.04755  -0.0248   1.0000   0.0741
  -8.250  -0.8174   0.05046   0.04434  -0.0208   1.0000   0.0724
  -8.000  -0.8251   0.04710   0.04061  -0.0167   1.0000   0.0705
  -7.750  -0.8274   0.04402   0.03713  -0.0130   1.0000   0.0697
  -7.500  -0.8237   0.04151   0.03427  -0.0099   1.0000   0.0702
  -7.250  -0.8148   0.03904   0.03142  -0.0075   0.9995   0.0709
  -7.000  -0.7924   0.03599   0.02787  -0.0072   0.9964   0.0710
  -6.750  -0.7661   0.03347   0.02491  -0.0074   0.9936   0.0717
  -6.500  -0.7404   0.03151   0.02258  -0.0072   0.9906   0.0739
  -6.250  -0.7140   0.02993   0.02066  -0.0072   0.9880   0.0775
  -6.000  -0.6865   0.02883   0.01958  -0.0077   0.9855   0.0818
  -5.750  -0.6566   0.02773   0.01826  -0.0081   0.9834   0.0869
  -5.500  -0.6326   0.02675   0.01732  -0.0079   0.9810   0.0939
  -5.250  -0.6084   0.02586   0.01633  -0.0074   0.9780   0.1039
  -5.000  -0.5841   0.02476   0.01530  -0.0072   0.9753   0.1180
  -4.750  -0.5632   0.02351   0.01428  -0.0065   0.9729   0.1422
  -4.500  -0.5451   0.02223   0.01343  -0.0055   0.9708   0.1907
  -4.250  -0.5304   0.02134   0.01291  -0.0038   0.9685   0.2485
  -4.000  -0.5207   0.02019   0.01248  -0.0013   0.9655   0.3502
  -3.750  -0.5186   0.01929   0.01319   0.0043   0.9629   0.6100
  -3.500  -0.5040   0.01980   0.01368   0.0076   0.9607   0.7087
  -3.250  -0.4838   0.02049   0.01431   0.0101   0.9582   0.7529
  -3.000  -0.4620   0.02132   0.01506   0.0125   0.9557   0.7881
  -2.750  -0.4496   0.02182   0.01551   0.0165   0.9536   0.8128
  -2.500  -0.4350   0.02227   0.01587   0.0199   0.9510   0.8356
  -2.250  -0.4140   0.02279   0.01629   0.0222   0.9483   0.8554
  -2.000  -0.3882   0.02330   0.01668   0.0232   0.9458   0.8734
  -1.750  -0.3527   0.02401   0.01727   0.0224   0.9430   0.8925
  -1.500  -0.3035   0.02493   0.01805   0.0191   0.9406   0.9106
  -1.250  -0.2371   0.02591   0.01888   0.0122   0.9382   0.9259
  -1.000  -0.1558   0.02667   0.01947   0.0018   0.9360   0.9328
  -0.750  -0.1135   0.02696   0.01968  -0.0018   0.9326   0.9421
  -0.500  -0.0458   0.02740   0.02001  -0.0101   0.9300   0.9497
  -0.250   0.0052   0.02772   0.02027  -0.0154   0.9270   0.9569
   0.000   0.0469   0.02786   0.02038  -0.0192   0.9229   0.9638
   0.250   0.0860   0.02804   0.02054  -0.0225   0.9182   0.9714
   0.500   0.1533   0.02824   0.02073  -0.0310   0.9151   0.9806
   0.750   0.2231   0.02832   0.02083  -0.0400   0.9122   0.9877
   1.000   0.2536   0.02847   0.02102  -0.0419   0.9059   0.9940
   1.250   0.3034   0.02848   0.02106  -0.0473   0.9004   0.9985
   1.500   0.3442   0.02856   0.02120  -0.0506   0.8939   1.0000
   1.750   0.3654   0.02868   0.02137  -0.0503   0.8845   1.0000
   2.000   0.3850   0.02885   0.02159  -0.0496   0.8746   1.0000
   2.250   0.4330   0.02875   0.02159  -0.0536   0.8674   1.0000
   2.500   0.4401   0.02903   0.02193  -0.0507   0.8559   1.0000
   2.750   0.4818   0.02888   0.02188  -0.0533   0.8461   1.0000
   3.000   0.5600   0.02787   0.02106  -0.0613   0.8366   1.0000
   3.250   0.5853   0.02758   0.02088  -0.0605   0.8231   1.0000
   3.500   0.6307   0.02642   0.01986  -0.0619   0.8081   1.0000
   3.750   0.6665   0.02528   0.01886  -0.0615   0.7929   1.0000
   4.000   0.6920   0.02446   0.01817  -0.0597   0.7785   1.0000
   4.250   0.7181   0.02339   0.01721  -0.0576   0.7631   1.0000
   4.500   0.7425   0.02219   0.01615  -0.0551   0.7465   1.0000
   4.750   0.7668   0.02085   0.01491  -0.0523   0.7285   1.0000
   5.000   0.7823   0.01996   0.01413  -0.0488   0.7073   1.0000
   5.250   0.8010   0.01873   0.01301  -0.0453   0.6809   1.0000
   5.500   0.8062   0.01822   0.01263  -0.0406   0.6438   1.0000
   5.750   0.8110   0.01761   0.01202  -0.0356   0.5791   1.0000
   6.000   0.8154   0.01744   0.01081  -0.0295   0.4266   1.0000
   6.250   0.8000   0.01853   0.01122  -0.0224   0.3345   1.0000
   6.500   0.7834   0.01949   0.01169  -0.0152   0.2738   1.0000
   6.750   0.7706   0.02043   0.01220  -0.0087   0.2288   1.0000
   7.000   0.7667   0.02149   0.01290  -0.0037   0.1907   1.0000
   7.250   0.7705   0.02264   0.01377   0.0000   0.1614   1.0000
   7.500   0.7800   0.02393   0.01475   0.0026   0.1393   1.0000
   7.750   0.7958   0.02519   0.01592   0.0043   0.1206   1.0000
   8.000   0.8165   0.02659   0.01723   0.0053   0.1060   1.0000
   8.250   0.8442   0.02833   0.01885   0.0051   0.0947   1.0000
   8.500   0.8685   0.02977   0.02028   0.0055   0.0860   1.0000
   8.750   0.8997   0.03196   0.02264   0.0050   0.0800   1.0000
   9.000   0.9233   0.03367   0.02447   0.0055   0.0749   1.0000
   9.250   0.9497   0.03638   0.02722   0.0052   0.0706   1.0000
   9.500   0.9658   0.03859   0.02988   0.0070   0.0686   1.0000
   9.750   0.9797   0.04121   0.03289   0.0088   0.0670   1.0000
  10.000   0.9897   0.04375   0.03577   0.0109   0.0652   1.0000
  10.250   1.0001   0.04603   0.03825   0.0127   0.0631   1.0000
  10.500   1.0135   0.04865   0.04095   0.0138   0.0612   1.0000
  10.750   1.0142   0.05192   0.04460   0.0165   0.0612   1.0000
  11.000   0.9981   0.05541   0.04860   0.0209   0.0621   1.0000
  11.250   0.9710   0.05901   0.05263   0.0260   0.0635   1.0000
  11.500   0.9448   0.06289   0.05681   0.0297   0.0647   1.0000
  11.750   0.9186   0.06709   0.06126   0.0321   0.0657   1.0000
  12.000   0.8931   0.07165   0.06602   0.0332   0.0669   1.0000
  12.250   0.8659   0.07678   0.07132   0.0332   0.0679   1.0000
  12.500   0.8436   0.08223   0.07688   0.0322   0.0691   1.0000
  12.750   0.8293   0.08806   0.08278   0.0308   0.0702   1.0000
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