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SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD2083 (9.0%) (sd2083-il)
Reynolds number: 500,000
Max Cl/Cd: 93.3 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd2083-il-500000-n5.txt
Download as CSV file: xf-sd2083-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2083 (9.0%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4040   0.08812   0.08588  -0.0354   1.0000   0.0097
  -9.000  -0.4058   0.08398   0.08178  -0.0372   1.0000   0.0098
  -8.750  -0.4092   0.07990   0.07774  -0.0389   1.0000   0.0096
  -8.500  -0.4079   0.07496   0.07283  -0.0431   0.9883   0.0097
  -8.000  -0.3909   0.05934   0.05713  -0.0653   0.9500   0.0097
  -7.750  -0.3909   0.05234   0.04998  -0.0709   0.9334   0.0098
  -7.500  -0.3919   0.04558   0.04300  -0.0735   0.9204   0.0098
  -7.250  -0.3917   0.03849   0.03557  -0.0744   0.9100   0.0098
  -7.000  -0.3869   0.03226   0.02891  -0.0740   0.9017   0.0100
  -6.750  -0.3754   0.02769   0.02391  -0.0732   0.8943   0.0103
  -6.500  -0.3606   0.02409   0.01983  -0.0721   0.8883   0.0105
  -6.250  -0.3424   0.02115   0.01645  -0.0711   0.8825   0.0105
  -6.000  -0.3214   0.01900   0.01393  -0.0702   0.8770   0.0106
  -5.750  -0.2986   0.01739   0.01200  -0.0694   0.8725   0.0108
  -5.500  -0.2743   0.01609   0.01043  -0.0689   0.8672   0.0111
  -5.250  -0.2495   0.01507   0.00921  -0.0684   0.8624   0.0114
  -5.000  -0.2241   0.01425   0.00822  -0.0679   0.8579   0.0118
  -4.750  -0.1982   0.01356   0.00740  -0.0675   0.8527   0.0120
  -4.500  -0.1721   0.01300   0.00672  -0.0672   0.8479   0.0123
  -4.250  -0.1460   0.01248   0.00610  -0.0668   0.8435   0.0124
  -4.000  -0.1206   0.01168   0.00521  -0.0664   0.8382   0.0127
  -3.750  -0.0956   0.01092   0.00434  -0.0659   0.8334   0.0137
  -3.500  -0.0693   0.01049   0.00384  -0.0656   0.8287   0.0143
  -3.250  -0.0427   0.01011   0.00340  -0.0653   0.8233   0.0145
  -3.000  -0.0160   0.00981   0.00302  -0.0650   0.8185   0.0148
  -2.750   0.0111   0.00954   0.00270  -0.0648   0.8132   0.0153
  -2.500   0.0383   0.00932   0.00240  -0.0646   0.8077   0.0161
  -2.250   0.0655   0.00914   0.00216  -0.0644   0.8027   0.0172
  -2.000   0.0930   0.00898   0.00195  -0.0643   0.7964   0.0190
  -1.500   0.1471   0.00856   0.00165  -0.0639   0.7841   0.0620
  -1.250   0.1732   0.00819   0.00153  -0.0637   0.7772   0.1372
  -1.000   0.1994   0.00785   0.00144  -0.0636   0.7697   0.2221
  -0.750   0.2254   0.00755   0.00136  -0.0634   0.7621   0.3108
  -0.500   0.2503   0.00708   0.00133  -0.0630   0.7534   0.4510
  -0.250   0.2716   0.00642   0.00135  -0.0618   0.7449   0.6621
   0.000   0.2918   0.00594   0.00138  -0.0599   0.7354   0.8210
   0.250   0.3289   0.00576   0.00143  -0.0613   0.7249   0.9384
   0.500   0.3702   0.00579   0.00140  -0.0642   0.7132   0.9697
   0.750   0.4097   0.00584   0.00137  -0.0667   0.6994   0.9846
   1.000   0.4474   0.00590   0.00135  -0.0689   0.6847   0.9947
   1.250   0.4814   0.00597   0.00134  -0.0703   0.6704   1.0000
   1.500   0.5062   0.00605   0.00136  -0.0697   0.6562   1.0000
   1.750   0.5310   0.00616   0.00139  -0.0690   0.6401   1.0000
   2.250   0.5803   0.00641   0.00149  -0.0677   0.6040   1.0000
   2.500   0.6046   0.00657   0.00156  -0.0670   0.5821   1.0000
   2.750   0.6286   0.00676   0.00166  -0.0663   0.5570   1.0000
   3.000   0.6522   0.00699   0.00177  -0.0655   0.5278   1.0000
   3.250   0.6754   0.00726   0.00191  -0.0646   0.4947   1.0000
   3.500   0.6980   0.00759   0.00207  -0.0637   0.4567   1.0000
   3.750   0.7206   0.00793   0.00228  -0.0628   0.4195   1.0000
   4.000   0.7433   0.00830   0.00249  -0.0619   0.3839   1.0000
   4.250   0.7659   0.00867   0.00271  -0.0611   0.3484   1.0000
   4.500   0.7887   0.00904   0.00295  -0.0603   0.3168   1.0000
   4.750   0.8117   0.00940   0.00319  -0.0595   0.2877   1.0000
   5.000   0.8346   0.00978   0.00348  -0.0588   0.2591   1.0000
   5.250   0.8560   0.01028   0.00379  -0.0578   0.2197   1.0000
   5.500   0.8771   0.01083   0.00413  -0.0569   0.1792   1.0000
   5.750   0.8991   0.01129   0.00445  -0.0560   0.1504   1.0000
   6.000   0.9201   0.01185   0.00483  -0.0550   0.1154   1.0000
   6.250   0.9415   0.01236   0.00522  -0.0541   0.0904   1.0000
   6.500   0.9627   0.01288   0.00566  -0.0532   0.0689   1.0000
   6.750   0.9833   0.01346   0.00613  -0.0521   0.0480   1.0000
   7.000   1.0010   0.01431   0.00677  -0.0507   0.0190   1.0000
   7.250   1.0205   0.01497   0.00738  -0.0495   0.0089   1.0000
   7.500   1.0420   0.01544   0.00789  -0.0485   0.0078   1.0000
   7.750   1.0626   0.01597   0.00848  -0.0474   0.0068   1.0000
   8.000   1.0828   0.01653   0.00914  -0.0463   0.0062   1.0000
   8.250   1.1019   0.01717   0.00987  -0.0450   0.0058   1.0000
   8.500   1.1184   0.01803   0.01086  -0.0432   0.0053   1.0000
   8.750   1.1361   0.01872   0.01163  -0.0418   0.0052   1.0000
   9.000   1.1529   0.01943   0.01242  -0.0402   0.0051   1.0000
   9.250   1.1686   0.02016   0.01324  -0.0385   0.0049   1.0000
   9.500   1.1826   0.02086   0.01402  -0.0365   0.0046   1.0000
   9.750   1.1938   0.02171   0.01496  -0.0341   0.0044   1.0000
  10.000   1.2044   0.02262   0.01599  -0.0317   0.0043   1.0000
  10.250   1.2142   0.02361   0.01708  -0.0294   0.0041   1.0000
  10.500   1.2236   0.02466   0.01824  -0.0272   0.0040   1.0000
  10.750   1.2315   0.02586   0.01954  -0.0250   0.0039   1.0000
  11.000   1.2393   0.02710   0.02089  -0.0229   0.0038   1.0000
  11.250   1.2460   0.02847   0.02237  -0.0208   0.0037   1.0000
  11.500   1.2521   0.02992   0.02394  -0.0189   0.0036   1.0000
  11.750   1.2559   0.03165   0.02579  -0.0169   0.0036   1.0000
  12.000   1.2606   0.03331   0.02757  -0.0153   0.0035   1.0000
  12.250   1.2635   0.03523   0.02963  -0.0137   0.0035   1.0000
  12.500   1.2641   0.03742   0.03194  -0.0122   0.0033   1.0000
  12.750   1.2641   0.03975   0.03444  -0.0109   0.0033   1.0000
  13.000   1.2614   0.04248   0.03732  -0.0099   0.0032   1.0000
  13.250   1.2600   0.04520   0.04019  -0.0091   0.0032   1.0000
  13.500   1.2507   0.04897   0.04415  -0.0086   0.0031   1.0000
  13.750   1.2391   0.05326   0.04863  -0.0085   0.0030   1.0000
  14.000   1.2272   0.05784   0.05340  -0.0091   0.0030   1.0000
  14.250   1.2218   0.06175   0.05747  -0.0100   0.0030   1.0000
  14.500   1.2060   0.06755   0.06348  -0.0118   0.0030   1.0000
  14.750   1.1977   0.07253   0.06861  -0.0138   0.0030   1.0000
  15.000   1.1748   0.08040   0.07670  -0.0174   0.0029   1.0000
  15.250   1.1680   0.08584   0.08227  -0.0203   0.0030   1.0000
  15.500   1.1588   0.09202   0.08859  -0.0236   0.0030   1.0000
  15.750   1.1355   0.10141   0.09818  -0.0289   0.0030   1.0000
  16.000   1.1253   0.10844   0.10533  -0.0330   0.0030   1.0000
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