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SD7034 (sd7034-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7034 (sd7034-il)
Reynolds number: 50,000
Max Cl/Cd: 27.84 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7034-il-50000.txt
Download as CSV file: xf-sd7034-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7034                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3167   0.10700   0.10052  -0.0275   1.0000   0.2096
  -8.250  -0.2949   0.10160   0.09513  -0.0262   1.0000   0.2171
  -8.000  -0.3108   0.10134   0.09504  -0.0272   1.0000   0.2253
  -7.750  -0.2912   0.09653   0.09025  -0.0258   1.0000   0.2342
  -7.500  -0.3159   0.09693   0.09087  -0.0252   1.0000   0.2412
  -7.250  -0.2993   0.09277   0.08674  -0.0232   1.0000   0.2534
  -7.000  -0.3344   0.09382   0.08804  -0.0199   1.0000   0.2569
  -6.750  -0.3226   0.09024   0.08449  -0.0173   1.0000   0.2695
  -6.500  -0.3574   0.09102   0.08547  -0.0132   1.0000   0.2724
  -6.250  -0.3526   0.08810   0.08261  -0.0098   1.0000   0.2829
  -6.000  -0.3887   0.08877   0.08345  -0.0080   1.0000   0.2890
  -5.750  -0.3821   0.08572   0.08046  -0.0041   1.0000   0.3015
  -5.500  -0.3921   0.08390   0.07873  -0.0016   1.0000   0.3109
  -5.000  -0.4213   0.08146   0.07648   0.0003   1.0000   0.3382
  -4.750  -0.4234   0.07916   0.07424   0.0030   1.0000   0.3545
  -4.500  -0.4225   0.07661   0.07174   0.0066   1.0000   0.3719
  -4.250  -0.4199   0.07429   0.06949   0.0109   1.0000   0.3932
  -3.500  -0.3003   0.04708   0.04025  -0.0440   1.0000   0.1659
  -3.250  -0.2707   0.04293   0.03558  -0.0468   1.0000   0.1545
  -3.000  -0.2427   0.03983   0.03194  -0.0488   1.0000   0.1543
  -2.750  -0.2158   0.03739   0.02899  -0.0500   1.0000   0.1560
  -2.500  -0.1890   0.03539   0.02641  -0.0509   1.0000   0.1597
  -2.250  -0.1654   0.03389   0.02463  -0.0511   1.0000   0.1678
  -2.000  -0.1231   0.03255   0.02285  -0.0543   0.9934   0.1818
  -1.750  -0.0764   0.03167   0.02175  -0.0582   0.9838   0.2071
  -1.500  -0.0345   0.03098   0.02096  -0.0612   0.9735   0.2410
  -1.250   0.0063   0.03040   0.02048  -0.0638   0.9631   0.2914
  -1.000   0.0488   0.02956   0.02019  -0.0666   0.9531   0.4000
  -0.750   0.0888   0.02740   0.01982  -0.0666   0.9436   1.0000
  -0.500   0.1251   0.02822   0.02006  -0.0691   0.9308   1.0000
  -0.250   0.1606   0.02907   0.02049  -0.0713   0.9178   1.0000
   0.000   0.1952   0.02995   0.02104  -0.0734   0.9049   1.0000
   0.250   0.2301   0.03083   0.02164  -0.0755   0.8921   1.0000
   0.500   0.2667   0.03172   0.02228  -0.0777   0.8792   1.0000
   0.750   0.3074   0.03260   0.02293  -0.0804   0.8666   1.0000
   1.000   0.3360   0.03341   0.02359  -0.0812   0.8529   1.0000
   1.250   0.3631   0.03426   0.02429  -0.0818   0.8391   1.0000
   1.500   0.3914   0.03511   0.02503  -0.0824   0.8252   1.0000
   1.750   0.4202   0.03598   0.02579  -0.0831   0.8116   1.0000
   2.000   0.4505   0.03681   0.02654  -0.0839   0.7980   1.0000
   2.250   0.4827   0.03759   0.02725  -0.0848   0.7846   1.0000
   2.500   0.5200   0.03823   0.02783  -0.0862   0.7716   1.0000
   2.750   0.5522   0.03890   0.02846  -0.0869   0.7580   1.0000
   3.000   0.5754   0.03978   0.02932  -0.0865   0.7436   1.0000
   3.250   0.5991   0.04065   0.03018  -0.0862   0.7291   1.0000
   3.500   0.6230   0.04153   0.03105  -0.0858   0.7148   1.0000
   3.750   0.6472   0.04240   0.03193  -0.0854   0.7005   1.0000
   4.000   0.6719   0.04324   0.03279  -0.0850   0.6863   1.0000
   4.250   0.6977   0.04401   0.03359  -0.0847   0.6721   1.0000
   4.500   0.7243   0.04473   0.03435  -0.0843   0.6584   1.0000
   4.750   0.7556   0.04514   0.03481  -0.0840   0.6450   1.0000
   5.000   0.8026   0.04434   0.03411  -0.0842   0.6341   1.0000
   5.250   0.8234   0.04517   0.03500  -0.0831   0.6194   1.0000
   5.500   0.8426   0.04616   0.03605  -0.0820   0.6048   1.0000
   5.750   0.8625   0.04707   0.03705  -0.0808   0.5903   1.0000
   6.000   0.8814   0.04810   0.03816  -0.0796   0.5759   1.0000
   6.250   0.9005   0.04909   0.03923  -0.0783   0.5615   1.0000
   7.000   0.9667   0.05120   0.04165  -0.0745   0.5203   1.0000
   7.250   1.0500   0.04591   0.03656  -0.0738   0.5109   1.0000
   7.500   1.0711   0.04655   0.03731  -0.0724   0.4961   1.0000
   7.750   1.0953   0.04686   0.03775  -0.0709   0.4812   1.0000
   8.000   1.1198   0.04717   0.03819  -0.0695   0.4662   1.0000
   8.250   1.1522   0.04668   0.03781  -0.0681   0.4508   1.0000
   8.500   1.1871   0.04599   0.03722  -0.0669   0.4349   1.0000
   8.750   1.2108   0.04633   0.03768  -0.0653   0.4185   1.0000
   9.000   1.2262   0.04742   0.03890  -0.0636   0.4021   1.0000
   9.250   1.0355   0.07144   0.06274  -0.0640   0.3978   1.0000
   9.500   1.2576   0.04942   0.04115  -0.0599   0.3685   1.0000
   9.750   1.2802   0.04974   0.04158  -0.0582   0.3503   1.0000
  10.000   1.3294   0.04776   0.03947  -0.0574   0.3271   1.0000
  10.250   0.9928   0.09260   0.08405  -0.0663   0.3531   1.0000
  10.500   1.3465   0.05085   0.04282  -0.0530   0.2926   1.0000
  10.750   1.3643   0.05162   0.04362  -0.0511   0.2734   1.0000
  11.000   1.3925   0.05189   0.04374  -0.0499   0.2524   1.0000
  11.250   1.3977   0.05383   0.04578  -0.0476   0.2372   1.0000
  11.500   1.4045   0.05586   0.04787  -0.0455   0.2228   1.0000
  11.750   1.3773   0.06002   0.05239  -0.0421   0.2176   1.0000
  12.000   1.3795   0.06226   0.05467  -0.0400   0.2061   1.0000
  12.250   1.3425   0.06760   0.06027  -0.0376   0.2049   1.0000
  12.500   1.2937   0.07535   0.06823  -0.0376   0.2068   1.0000
  12.750   1.2397   0.08576   0.07873  -0.0403   0.2092   1.0000
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