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SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7043 (9.1%) (sd7043-il)
Reynolds number: 50,000
Max Cl/Cd: 38.65 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7043-il-50000.txt
Download as CSV file: xf-sd7043-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7043 (9.1%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3491   0.10352   0.09692  -0.0258   1.0000   0.2226
  -7.750  -0.3299   0.09861   0.09200  -0.0241   1.0000   0.2318
  -7.500  -0.3569   0.09934   0.09297  -0.0233   1.0000   0.2381
  -7.250  -0.3347   0.09434   0.08795  -0.0216   1.0000   0.2485
  -7.000  -0.3693   0.09552   0.08937  -0.0192   1.0000   0.2534
  -6.750  -0.3500   0.09094   0.08480  -0.0172   1.0000   0.2655
  -6.500  -0.3766   0.09066   0.08472  -0.0148   1.0000   0.2705
  -6.250  -0.3754   0.08828   0.08240  -0.0122   1.0000   0.2828
  -6.000  -0.3709   0.08528   0.07947  -0.0094   1.0000   0.2929
  -5.500  -0.3983   0.08246   0.07690  -0.0066   1.0000   0.3164
  -5.250  -0.4011   0.08029   0.07480  -0.0044   1.0000   0.3317
  -5.000  -0.3955   0.07740   0.07197  -0.0004   1.0000   0.3495
  -4.750  -0.3933   0.07508   0.06972   0.0032   1.0000   0.3702
  -4.500  -0.4009   0.07330   0.06803   0.0052   1.0000   0.3945
  -3.750  -0.2699   0.04370   0.03626  -0.0538   1.0000   0.1460
  -3.500  -0.2322   0.03872   0.03037  -0.0579   1.0000   0.1320
  -3.250  -0.2024   0.03570   0.02686  -0.0594   1.0000   0.1316
  -3.000  -0.1725   0.03309   0.02378  -0.0605   1.0000   0.1338
  -2.750  -0.1445   0.03094   0.02133  -0.0609   1.0000   0.1359
  -2.500  -0.1175   0.02937   0.01947  -0.0610   1.0000   0.1424
  -2.250  -0.0911   0.02799   0.01783  -0.0610   1.0000   0.1522
  -2.000  -0.0655   0.02680   0.01638  -0.0605   1.0000   0.1641
  -1.750  -0.0417   0.02582   0.01548  -0.0599   1.0000   0.1875
  -1.500  -0.0143   0.02467   0.01448  -0.0597   1.0000   0.2403
  -1.250   0.0098   0.02167   0.01405  -0.0573   1.0000   0.6568
  -1.000   0.0127   0.02069   0.01344  -0.0518   1.0000   1.0000
  -0.750   0.0379   0.02115   0.01329  -0.0524   1.0000   1.0000
  -0.500   0.0611   0.02166   0.01338  -0.0528   1.0000   1.0000
  -0.250   0.0832   0.02223   0.01360  -0.0530   1.0000   1.0000
   0.000   0.1046   0.02284   0.01392  -0.0532   1.0000   1.0000
   0.250   0.1254   0.02351   0.01435  -0.0534   1.0000   1.0000
   0.500   0.1456   0.02423   0.01486  -0.0535   1.0000   1.0000
   0.750   0.1652   0.02501   0.01546  -0.0537   1.0000   1.0000
   1.000   0.1990   0.02617   0.01642  -0.0565   0.9933   1.0000
   1.250   0.2483   0.02758   0.01764  -0.0620   0.9765   1.0000
   1.500   0.2973   0.02894   0.01885  -0.0672   0.9596   1.0000
   1.750   0.3464   0.03022   0.02002  -0.0722   0.9425   1.0000
   2.000   0.3851   0.03120   0.02094  -0.0752   0.9233   1.0000
   2.250   0.4265   0.03215   0.02185  -0.0784   0.9042   1.0000
   2.500   0.4715   0.03303   0.02271  -0.0818   0.8852   1.0000
   2.750   0.5161   0.03376   0.02346  -0.0849   0.8661   1.0000
   3.000   0.5500   0.03439   0.02412  -0.0861   0.8447   1.0000
   3.250   0.5956   0.03476   0.02455  -0.0887   0.8248   1.0000
   3.500   0.6367   0.03501   0.02489  -0.0903   0.8041   1.0000
   3.750   0.6759   0.03509   0.02507  -0.0913   0.7823   1.0000
   4.000   0.7332   0.03431   0.02444  -0.0938   0.7632   1.0000
   4.250   0.7659   0.03412   0.02439  -0.0932   0.7396   1.0000
   4.500   0.8167   0.03276   0.02318  -0.0936   0.7197   1.0000
   4.750   0.8530   0.03196   0.02254  -0.0925   0.6958   1.0000
   5.000   0.9025   0.03008   0.02079  -0.0918   0.6738   1.0000
   5.250   0.9372   0.02910   0.01990  -0.0901   0.6457   1.0000
   5.500   0.9728   0.02807   0.01892  -0.0883   0.6154   1.0000
   5.750   1.0053   0.02738   0.01818  -0.0863   0.5819   1.0000
   6.000   1.0306   0.02737   0.01812  -0.0841   0.5445   1.0000
   6.250   1.0586   0.02739   0.01797  -0.0822   0.5074   1.0000
   6.500   1.0800   0.02804   0.01852  -0.0801   0.4692   1.0000
   6.750   1.1045   0.02870   0.01893  -0.0784   0.4336   1.0000
   7.000   1.1248   0.02978   0.01992  -0.0767   0.3995   1.0000
   7.250   1.1456   0.03096   0.02103  -0.0751   0.3681   1.0000
   7.500   1.1670   0.03228   0.02224  -0.0737   0.3397   1.0000
   7.750   1.1900   0.03364   0.02339  -0.0725   0.3136   1.0000
   8.000   1.2073   0.03539   0.02531  -0.0710   0.2904   1.0000
   8.250   1.2311   0.03698   0.02671  -0.0701   0.2692   1.0000
   8.500   1.2478   0.03906   0.02902  -0.0686   0.2512   1.0000
   8.750   1.2649   0.04111   0.03123  -0.0672   0.2344   1.0000
   9.000   1.2828   0.04348   0.03376  -0.0659   0.2207   1.0000
   9.250   1.3002   0.04584   0.03626  -0.0647   0.2079   1.0000
   9.500   1.3206   0.04819   0.03859  -0.0638   0.1959   1.0000
   9.750   1.3207   0.05184   0.04293  -0.0612   0.1893   1.0000
  10.000   1.3385   0.05461   0.04574  -0.0602   0.1805   1.0000
  10.250   1.3302   0.05862   0.05035  -0.0573   0.1755   1.0000
  10.500   1.3556   0.06138   0.05298  -0.0571   0.1674   1.0000
  10.750   1.3378   0.06623   0.05840  -0.0541   0.1660   1.0000
  11.000   1.3153   0.07132   0.06391  -0.0515   0.1653   1.0000
  11.250   1.2863   0.07657   0.06945  -0.0491   0.1654   1.0000
  11.500   1.2542   0.08213   0.07519  -0.0474   0.1661   1.0000
  11.750   1.2226   0.08867   0.08186  -0.0475   0.1670   1.0000
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