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SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD8040 (10%) (sd8040-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.71 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8040-il-1000000.txt
Download as CSV file: xf-sd8040-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8040 (10%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4381   0.08312   0.08146  -0.0341   1.0000   0.0146
  -9.250  -0.4364   0.08014   0.07850  -0.0353   1.0000   0.0148
  -9.000  -0.5930   0.04038   0.03837  -0.0611   0.9973   0.0113
  -8.750  -0.5964   0.02767   0.02472  -0.0702   0.9886   0.0110
  -8.500  -0.5724   0.02348   0.02000  -0.0729   0.9859   0.0112
  -8.250  -0.5449   0.02128   0.01748  -0.0744   0.9828   0.0113
  -8.000  -0.5189   0.01966   0.01560  -0.0749   0.9778   0.0113
  -7.750  -0.4918   0.01819   0.01390  -0.0755   0.9737   0.0114
  -7.500  -0.4700   0.01648   0.01194  -0.0750   0.9670   0.0115
  -7.250  -0.4480   0.01494   0.01020  -0.0742   0.9609   0.0116
  -7.000  -0.4260   0.01381   0.00895  -0.0733   0.9545   0.0118
  -6.750  -0.4029   0.01306   0.00812  -0.0724   0.9482   0.0121
  -6.500  -0.3786   0.01253   0.00753  -0.0717   0.9426   0.0124
  -6.250  -0.3538   0.01205   0.00700  -0.0711   0.9361   0.0127
  -6.000  -0.3291   0.01159   0.00647  -0.0703   0.9304   0.0132
  -5.750  -0.3036   0.01108   0.00591  -0.0698   0.9241   0.0136
  -5.500  -0.2780   0.01065   0.00539  -0.0692   0.9177   0.0139
  -5.250  -0.2519   0.01032   0.00500  -0.0687   0.9115   0.0143
  -5.000  -0.2267   0.00963   0.00425  -0.0681   0.9043   0.0149
  -4.750  -0.2006   0.00929   0.00385  -0.0676   0.8978   0.0156
  -4.500  -0.1734   0.00899   0.00354  -0.0674   0.8903   0.0163
  -4.250  -0.1466   0.00874   0.00323  -0.0669   0.8830   0.0172
  -4.000  -0.1194   0.00841   0.00286  -0.0667   0.8751   0.0184
  -3.750  -0.0924   0.00818   0.00260  -0.0663   0.8670   0.0203
  -3.500  -0.0648   0.00793   0.00233  -0.0661   0.8580   0.0232
  -3.250  -0.0376   0.00771   0.00209  -0.0658   0.8490   0.0286
  -3.000  -0.0102   0.00745   0.00187  -0.0656   0.8386   0.0418
  -2.750   0.0172   0.00723   0.00171  -0.0654   0.8281   0.0619
  -2.500   0.0445   0.00703   0.00156  -0.0651   0.8168   0.0883
  -2.250   0.0718   0.00681   0.00144  -0.0650   0.8041   0.1243
  -2.000   0.0992   0.00660   0.00133  -0.0648   0.7909   0.1666
  -1.750   0.1264   0.00639   0.00124  -0.0646   0.7769   0.2191
  -1.500   0.1532   0.00609   0.00116  -0.0645   0.7623   0.3018
  -1.250   0.1800   0.00583   0.00111  -0.0643   0.7468   0.3865
  -1.000   0.2068   0.00561   0.00107  -0.0641   0.7304   0.4673
  -0.750   0.2335   0.00542   0.00105  -0.0638   0.7134   0.5498
  -0.500   0.2602   0.00527   0.00105  -0.0635   0.6957   0.6234
  -0.250   0.2866   0.00518   0.00106  -0.0631   0.6774   0.6881
   0.000   0.3131   0.00512   0.00109  -0.0626   0.6589   0.7418
   0.250   0.3393   0.00508   0.00112  -0.0621   0.6399   0.7906
   0.500   0.3651   0.00507   0.00115  -0.0614   0.6202   0.8331
   0.750   0.3901   0.00507   0.00120  -0.0606   0.6008   0.8736
   1.000   0.4142   0.00511   0.00124  -0.0594   0.5813   0.9134
   1.250   0.4397   0.00516   0.00128  -0.0586   0.5620   0.9520
   1.500   0.4752   0.00526   0.00130  -0.0601   0.5398   0.9799
   1.750   0.5146   0.00541   0.00133  -0.0626   0.5160   0.9970
   2.000   0.5433   0.00555   0.00138  -0.0628   0.4945   1.0000
   2.250   0.5690   0.00572   0.00144  -0.0623   0.4734   1.0000
   2.500   0.5950   0.00590   0.00152  -0.0619   0.4527   1.0000
   2.750   0.6213   0.00607   0.00160  -0.0616   0.4317   1.0000
   3.000   0.6476   0.00625   0.00169  -0.0612   0.4106   1.0000
   3.250   0.6739   0.00646   0.00179  -0.0609   0.3908   1.0000
   3.500   0.7004   0.00664   0.00189  -0.0606   0.3710   1.0000
   3.750   0.7268   0.00684   0.00201  -0.0603   0.3514   1.0000
   4.000   0.7531   0.00706   0.00214  -0.0601   0.3319   1.0000
   4.250   0.7794   0.00728   0.00227  -0.0598   0.3138   1.0000
   4.500   0.8057   0.00750   0.00242  -0.0595   0.2957   1.0000
   4.750   0.8320   0.00773   0.00257  -0.0592   0.2787   1.0000
   5.000   0.8582   0.00797   0.00274  -0.0589   0.2608   1.0000
   5.250   0.8843   0.00821   0.00292  -0.0586   0.2442   1.0000
   5.500   0.9101   0.00848   0.00310  -0.0583   0.2271   1.0000
   5.750   0.9357   0.00876   0.00330  -0.0580   0.2101   1.0000
   6.000   0.9612   0.00906   0.00353  -0.0576   0.1932   1.0000
   6.250   0.9866   0.00936   0.00375  -0.0572   0.1780   1.0000
   6.500   1.0120   0.00965   0.00399  -0.0569   0.1644   1.0000
   6.750   1.0372   0.00996   0.00424  -0.0565   0.1512   1.0000
   7.000   1.0624   0.01027   0.00449  -0.0561   0.1389   1.0000
   7.250   1.0873   0.01058   0.00477  -0.0557   0.1274   1.0000
   7.500   1.1120   0.01092   0.00505  -0.0552   0.1165   1.0000
   7.750   1.1364   0.01128   0.00537  -0.0547   0.1061   1.0000
   8.250   1.1847   0.01199   0.00601  -0.0537   0.0881   1.0000
   8.500   1.2085   0.01237   0.00636  -0.0532   0.0800   1.0000
   8.750   1.2316   0.01280   0.00674  -0.0525   0.0717   1.0000
   9.000   1.2550   0.01318   0.00711  -0.0519   0.0655   1.0000
   9.250   1.2779   0.01360   0.00752  -0.0512   0.0590   1.0000
   9.500   1.2997   0.01411   0.00798  -0.0504   0.0521   1.0000
   9.750   1.3221   0.01452   0.00841  -0.0496   0.0476   1.0000
  10.000   1.3434   0.01502   0.00890  -0.0488   0.0430   1.0000
  10.250   1.3645   0.01552   0.00939  -0.0478   0.0392   1.0000
  10.500   1.3848   0.01605   0.00993  -0.0468   0.0359   1.0000
  10.750   1.4052   0.01654   0.01044  -0.0458   0.0334   1.0000
  11.000   1.4225   0.01724   0.01114  -0.0444   0.0305   1.0000
  11.250   1.4427   0.01767   0.01163  -0.0433   0.0292   1.0000
  11.500   1.4606   0.01823   0.01221  -0.0420   0.0275   1.0000
  11.750   1.4745   0.01897   0.01297  -0.0401   0.0256   1.0000
  12.000   1.4884   0.01954   0.01360  -0.0381   0.0246   1.0000
  12.250   1.5023   0.02009   0.01422  -0.0361   0.0237   1.0000
  12.500   1.5144   0.02076   0.01493  -0.0340   0.0227   1.0000
  12.750   1.5237   0.02162   0.01583  -0.0317   0.0216   1.0000
  13.000   1.5300   0.02269   0.01697  -0.0291   0.0206   1.0000
  13.250   1.5430   0.02339   0.01773  -0.0275   0.0200   1.0000
  13.500   1.5537   0.02425   0.01866  -0.0258   0.0193   1.0000
  13.750   1.5629   0.02526   0.01974  -0.0240   0.0187   1.0000
  14.000   1.5699   0.02646   0.02099  -0.0222   0.0181   1.0000
  14.250   1.5727   0.02803   0.02262  -0.0203   0.0174   1.0000
  14.500   1.5723   0.02994   0.02464  -0.0184   0.0168   1.0000
  14.750   1.5801   0.03130   0.02608  -0.0173   0.0165   1.0000
  15.000   1.5856   0.03292   0.02780  -0.0163   0.0161   1.0000
  15.250   1.5916   0.03458   0.02953  -0.0154   0.0155   1.0000
  15.500   1.5937   0.03671   0.03174  -0.0147   0.0152   1.0000
  15.750   1.5949   0.03903   0.03415  -0.0142   0.0148   1.0000
  16.000   1.5924   0.04189   0.03711  -0.0140   0.0145   1.0000
  16.250   1.5867   0.04530   0.04060  -0.0142   0.0141   1.0000
  16.500   1.5754   0.04962   0.04505  -0.0149   0.0139   1.0000
  16.750   1.5617   0.05455   0.05012  -0.0163   0.0136   1.0000
  17.000   1.5601   0.05810   0.05378  -0.0174   0.0134   1.0000
  17.250   1.5527   0.06263   0.05843  -0.0190   0.0133   1.0000
  17.500   1.5438   0.06754   0.06347  -0.0210   0.0131   1.0000
  17.750   1.5326   0.07303   0.06909  -0.0234   0.0130   1.0000
  18.000   1.5195   0.07901   0.07519  -0.0261   0.0129   1.0000
  18.250   1.5055   0.08530   0.08161  -0.0292   0.0127   1.0000
  18.500   1.4871   0.09256   0.08901  -0.0328   0.0127   1.0000
  18.750   1.4691   0.09993   0.09651  -0.0367   0.0126   1.0000
  19.000   1.4528   0.10718   0.10388  -0.0405   0.0124   1.0000
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