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S4310 (s4310-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 50,000
Max Cl/Cd: 28.18 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4310-il-50000.txt
Download as CSV file: xf-s4310-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4310                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3060   0.11386   0.10749  -0.0342   1.0000   0.1881
  -8.750  -0.2798   0.10781   0.10144  -0.0321   1.0000   0.1988
  -8.500  -0.3025   0.10845   0.10228  -0.0331   1.0000   0.2029
  -8.250  -0.2798   0.10303   0.09687  -0.0310   1.0000   0.2130
  -8.000  -0.3060   0.10376   0.09783  -0.0300   1.0000   0.2175
  -7.750  -0.2903   0.09925   0.09336  -0.0278   1.0000   0.2254
  -7.500  -0.3129   0.09937   0.09365  -0.0248   1.0000   0.2310
  -7.250  -0.3492   0.10068   0.09516  -0.0207   1.0000   0.2326
  -7.000  -0.3323   0.09637   0.09087  -0.0183   1.0000   0.2411
  -6.750  -0.3615   0.09676   0.09142  -0.0142   1.0000   0.2456
  -6.500  -0.3990   0.09768   0.09252  -0.0116   1.0000   0.2477
  -6.250  -0.3865   0.09389   0.08876  -0.0079   1.0000   0.2571
  -6.000  -0.4203   0.09425   0.08927  -0.0074   1.0000   0.2626
  -5.750  -0.4112   0.09085   0.08592  -0.0035   1.0000   0.2718
  -5.500  -0.4319   0.08961   0.08478  -0.0033   1.0000   0.2801
  -5.250  -0.4425   0.08819   0.08341  -0.0027   1.0000   0.2929
  -5.000  -0.4377   0.08520   0.08048   0.0013   1.0000   0.3049
  -4.750  -0.4408   0.08287   0.07821   0.0033   1.0000   0.3183
  -4.250  -0.4498   0.07846   0.07389   0.0060   1.0000   0.3560
  -4.000  -0.4521   0.07666   0.07212   0.0081   1.0000   0.3836
  -3.750  -0.4488   0.07406   0.06961   0.0139   1.0000   0.4077
  -3.000  -0.2857   0.04698   0.03964  -0.0432   1.0000   0.1443
  -2.750  -0.2630   0.04395   0.03643  -0.0437   1.0000   0.1375
  -2.500  -0.2317   0.04074   0.03234  -0.0454   1.0000   0.1306
  -2.250  -0.1886   0.03871   0.02993  -0.0491   0.9928   0.1351
  -2.000  -0.1433   0.03681   0.02743  -0.0525   0.9848   0.1366
  -1.750  -0.1027   0.03566   0.02563  -0.0548   0.9769   0.1432
  -1.500  -0.0608   0.03484   0.02457  -0.0576   0.9686   0.1582
  -1.250  -0.0252   0.03399   0.02371  -0.0590   0.9602   0.1765
  -1.000   0.0136   0.03331   0.02314  -0.0609   0.9518   0.2334
  -0.750   0.0542   0.02963   0.02230  -0.0611   0.9447   1.0000
  -0.500   0.0851   0.03048   0.02248  -0.0625   0.9346   1.0000
  -0.250   0.1201   0.03147   0.02299  -0.0648   0.9246   1.0000
   0.000   0.1567   0.03250   0.02359  -0.0672   0.9145   1.0000
   0.250   0.1811   0.03332   0.02413  -0.0677   0.9038   1.0000
   0.500   0.2104   0.03429   0.02483  -0.0690   0.8931   1.0000
   0.750   0.2455   0.03534   0.02560  -0.0711   0.8824   1.0000
   1.000   0.2748   0.03630   0.02636  -0.0722   0.8712   1.0000
   1.250   0.2977   0.03723   0.02713  -0.0725   0.8596   1.0000
   1.500   0.3244   0.03824   0.02799  -0.0732   0.8480   1.0000
   1.750   0.3552   0.03927   0.02887  -0.0744   0.8363   1.0000
   2.000   0.3909   0.04028   0.02975  -0.0763   0.8245   1.0000
   2.250   0.4153   0.04126   0.03063  -0.0765   0.8118   1.0000
   2.500   0.4372   0.04227   0.03157  -0.0764   0.7988   1.0000
   2.750   0.4605   0.04331   0.03255  -0.0765   0.7858   1.0000
   3.000   0.4854   0.04435   0.03353  -0.0767   0.7724   1.0000
   3.250   0.5107   0.04539   0.03454  -0.0769   0.7592   1.0000
   3.500   0.5368   0.04640   0.03552  -0.0772   0.7457   1.0000
   3.750   0.5633   0.04739   0.03649  -0.0773   0.7320   1.0000
   4.000   0.5898   0.04835   0.03747  -0.0775   0.7182   1.0000
   4.250   0.6164   0.04928   0.03841  -0.0775   0.7043   1.0000
   4.500   0.6431   0.05018   0.03932  -0.0775   0.6904   1.0000
   4.750   0.6695   0.05104   0.04022  -0.0773   0.6762   1.0000
   5.000   0.6962   0.05185   0.04109  -0.0771   0.6621   1.0000
   5.250   0.7220   0.05264   0.04192  -0.0767   0.6478   1.0000
   5.500   0.7471   0.05339   0.04274  -0.0762   0.6333   1.0000
   5.750   0.7707   0.05419   0.04360  -0.0755   0.6187   1.0000
   6.000   0.7918   0.05510   0.04461  -0.0746   0.6037   1.0000
   6.250   0.8140   0.05592   0.04550  -0.0737   0.5890   1.0000
   6.500   0.8333   0.05688   0.04655  -0.0726   0.5738   1.0000
   6.750   0.8548   0.05769   0.04745  -0.0716   0.5592   1.0000
   7.000   0.8736   0.05863   0.04852  -0.0704   0.5441   1.0000
   7.250   0.8953   0.05934   0.04934  -0.0693   0.5295   1.0000
   7.500   0.9163   0.06002   0.05012  -0.0680   0.5148   1.0000
   7.750   0.9863   0.05555   0.04594  -0.0665   0.5041   1.0000
   8.000   1.0206   0.05449   0.04505  -0.0649   0.4898   1.0000
   8.250   1.0729   0.05184   0.04261  -0.0639   0.4755   1.0000
   8.500   1.1499   0.04706   0.03807  -0.0639   0.4595   1.0000
   8.750   1.1523   0.04895   0.04008  -0.0614   0.4427   1.0000
   9.000   1.1704   0.04952   0.04078  -0.0596   0.4260   1.0000
   9.250   1.2272   0.04681   0.03822  -0.0592   0.4059   1.0000
   9.500   1.2750   0.04530   0.03672  -0.0589   0.3856   1.0000
   9.750   1.2852   0.04672   0.03826  -0.0567   0.3687   1.0000
  10.000   1.3007   0.04787   0.03952  -0.0550   0.3520   1.0000
  10.250   1.3269   0.04830   0.04003  -0.0538   0.3336   1.0000
  10.500   1.3635   0.04839   0.04006  -0.0534   0.3145   1.0000
  10.750   1.1335   0.07220   0.06407  -0.0483   0.3343   1.0000
  11.000   1.0499   0.08971   0.08134  -0.0542   0.3283   1.0000
  11.250   1.1939   0.07054   0.06275  -0.0439   0.3061   1.0000
  11.500   1.1376   0.08212   0.07427  -0.0465   0.3017   1.0000
  11.750   1.3368   0.06242   0.05493  -0.0404   0.2623   1.0000
  12.000   1.3925   0.06200   0.05453  -0.0409   0.2427   1.0000
  12.250   1.3477   0.06748   0.06022  -0.0374   0.2422   1.0000
  12.500   1.2949   0.07512   0.06797  -0.0363   0.2429   1.0000
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