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SA7035 (sa7035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.4 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7035-il-1000000.txt
Download as CSV file: xf-sa7035-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7035                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3394   0.08673   0.08522  -0.0282   1.0000   0.0084
  -9.500  -0.3390   0.08265   0.08115  -0.0294   1.0000   0.0085
  -9.250  -0.3392   0.07830   0.07681  -0.0308   1.0000   0.0085
  -9.000  -0.3397   0.07429   0.07281  -0.0320   1.0000   0.0086
  -8.750  -0.3409   0.07011   0.06865  -0.0333   1.0000   0.0087
  -8.500  -0.3425   0.06616   0.06472  -0.0345   1.0000   0.0089
  -8.250  -0.3486   0.06131   0.05990  -0.0362   1.0000   0.0088
  -8.000  -0.3578   0.05693   0.05554  -0.0372   1.0000   0.0089
  -7.500  -0.4325   0.05073   0.04916  -0.0572   0.9935   0.0084
  -7.250  -0.4161   0.04183   0.03999  -0.0656   0.9878   0.0085
  -7.000  -0.3916   0.03771   0.03568  -0.0704   0.9849   0.0088
  -6.750  -0.3689   0.03340   0.03111  -0.0734   0.9797   0.0090
  -6.500  -0.3471   0.03000   0.02747  -0.0750   0.9735   0.0094
  -6.250  -0.3271   0.02678   0.02397  -0.0753   0.9663   0.0098
  -6.000  -0.3084   0.02399   0.02088  -0.0745   0.9584   0.0105
  -5.750  -0.2955   0.01716   0.01318  -0.0717   0.9485   0.0074
  -5.500  -0.2759   0.01385   0.00937  -0.0700   0.9418   0.0066
  -5.250  -0.2523   0.01250   0.00781  -0.0690   0.9345   0.0067
  -5.000  -0.2279   0.01171   0.00687  -0.0682   0.9282   0.0073
  -4.750  -0.2023   0.01110   0.00616  -0.0676   0.9206   0.0077
  -4.500  -0.1766   0.01067   0.00562  -0.0670   0.9140   0.0080
  -4.250  -0.1511   0.00991   0.00477  -0.0664   0.9061   0.0082
  -4.000  -0.1260   0.00907   0.00381  -0.0658   0.8989   0.0086
  -3.750  -0.0996   0.00859   0.00328  -0.0655   0.8906   0.0093
  -3.500  -0.0728   0.00829   0.00292  -0.0652   0.8826   0.0101
  -3.250  -0.0458   0.00795   0.00249  -0.0648   0.8736   0.0107
  -3.000  -0.0184   0.00769   0.00215  -0.0645   0.8636   0.0116
  -2.750   0.0088   0.00729   0.00172  -0.0642   0.8534   0.0224
  -2.500   0.0353   0.00685   0.00148  -0.0640   0.8421   0.0840
  -2.250   0.0622   0.00655   0.00133  -0.0638   0.8298   0.1417
  -2.000   0.0889   0.00619   0.00120  -0.0638   0.8167   0.2256
  -1.750   0.1152   0.00572   0.00110  -0.0637   0.8027   0.3526
  -1.500   0.1419   0.00544   0.00103  -0.0635   0.7879   0.4417
  -1.250   0.1689   0.00526   0.00098  -0.0634   0.7718   0.5084
  -1.000   0.1958   0.00510   0.00095  -0.0632   0.7544   0.5817
  -0.750   0.2227   0.00500   0.00093  -0.0629   0.7361   0.6382
  -0.500   0.2492   0.00490   0.00092  -0.0626   0.7181   0.6984
  -0.250   0.2757   0.00482   0.00093  -0.0622   0.7005   0.7539
   0.000   0.3018   0.00476   0.00095  -0.0617   0.6827   0.8022
   0.250   0.3271   0.00471   0.00098  -0.0609   0.6648   0.8512
   0.500   0.3508   0.00470   0.00101  -0.0598   0.6467   0.9006
   0.750   0.3746   0.00471   0.00104  -0.0586   0.6285   0.9466
   1.000   0.4074   0.00479   0.00105  -0.0595   0.6079   0.9772
   1.250   0.4454   0.00490   0.00105  -0.0618   0.5855   0.9947
   1.500   0.4772   0.00503   0.00107  -0.0627   0.5633   1.0000
   1.750   0.5031   0.00516   0.00112  -0.0623   0.5437   1.0000
   2.000   0.5293   0.00530   0.00117  -0.0620   0.5246   1.0000
   2.500   0.5821   0.00560   0.00130  -0.0615   0.4856   1.0000
   2.750   0.6087   0.00576   0.00138  -0.0612   0.4656   1.0000
   3.000   0.6352   0.00594   0.00147  -0.0610   0.4453   1.0000
   3.250   0.6617   0.00612   0.00158  -0.0608   0.4231   1.0000
   3.500   0.6883   0.00632   0.00169  -0.0606   0.4027   1.0000
   3.750   0.7149   0.00650   0.00180  -0.0604   0.3831   1.0000
   4.000   0.7413   0.00672   0.00193  -0.0602   0.3627   1.0000
   4.250   0.7679   0.00691   0.00207  -0.0601   0.3444   1.0000
   4.500   0.7943   0.00713   0.00222  -0.0599   0.3252   1.0000
   4.750   0.8205   0.00737   0.00238  -0.0597   0.3047   1.0000
   5.000   0.8466   0.00763   0.00256  -0.0594   0.2833   1.0000
   5.250   0.8724   0.00791   0.00276  -0.0592   0.2602   1.0000
   5.750   0.9238   0.00849   0.00319  -0.0587   0.2198   1.0000
   6.000   0.9494   0.00879   0.00342  -0.0584   0.2006   1.0000
   6.250   0.9746   0.00914   0.00369  -0.0581   0.1806   1.0000
   6.500   0.9999   0.00945   0.00395  -0.0578   0.1634   1.0000
   6.750   1.0243   0.00987   0.00427  -0.0574   0.1420   1.0000
   7.000   1.0488   0.01027   0.00458  -0.0570   0.1219   1.0000
   7.250   1.0730   0.01071   0.00494  -0.0565   0.1040   1.0000
   7.500   1.0969   0.01115   0.00531  -0.0560   0.0869   1.0000
   7.750   1.1206   0.01161   0.00571  -0.0555   0.0718   1.0000
   8.000   1.1436   0.01213   0.00615  -0.0549   0.0565   1.0000
   8.250   1.1662   0.01269   0.00663  -0.0543   0.0432   1.0000
   8.500   1.1890   0.01321   0.00711  -0.0537   0.0343   1.0000
   8.750   1.2119   0.01369   0.00760  -0.0530   0.0275   1.0000
   9.000   1.2340   0.01424   0.00814  -0.0523   0.0210   1.0000
   9.250   1.2551   0.01488   0.00876  -0.0514   0.0154   1.0000
   9.500   1.2756   0.01556   0.00944  -0.0505   0.0116   1.0000
   9.750   1.2966   0.01615   0.01009  -0.0496   0.0098   1.0000
  10.000   1.3165   0.01682   0.01078  -0.0485   0.0082   1.0000
  10.250   1.3345   0.01764   0.01168  -0.0472   0.0068   1.0000
  10.500   1.3544   0.01822   0.01233  -0.0462   0.0061   1.0000
  10.750   1.3721   0.01895   0.01311  -0.0450   0.0054   1.0000
  11.000   1.3815   0.02034   0.01465  -0.0425   0.0045   1.0000
  11.250   1.3982   0.02101   0.01538  -0.0410   0.0043   1.0000
  11.500   1.4104   0.02180   0.01627  -0.0389   0.0040   1.0000
  11.750   1.4204   0.02261   0.01716  -0.0365   0.0038   1.0000
  12.000   1.4297   0.02347   0.01809  -0.0341   0.0035   1.0000
  12.250   1.4365   0.02452   0.01923  -0.0316   0.0033   1.0000
  12.500   1.4418   0.02572   0.02052  -0.0292   0.0032   1.0000
  12.750   1.4406   0.02745   0.02236  -0.0264   0.0029   1.0000
  13.000   1.4370   0.02948   0.02454  -0.0238   0.0029   1.0000
  13.250   1.4277   0.03216   0.02741  -0.0213   0.0028   1.0000
  13.500   1.4178   0.03518   0.03059  -0.0196   0.0027   1.0000
  13.750   1.4151   0.03780   0.03334  -0.0187   0.0027   1.0000
  14.000   1.4237   0.03941   0.03504  -0.0184   0.0026   1.0000
  14.250   1.4206   0.04243   0.03818  -0.0182   0.0025   1.0000
  14.500   1.4156   0.04587   0.04176  -0.0185   0.0025   1.0000
  14.750   1.4078   0.04995   0.04598  -0.0194   0.0025   1.0000
  15.000   1.3976   0.05463   0.05081  -0.0208   0.0024   1.0000
  15.250   1.3945   0.05857   0.05485  -0.0222   0.0023   1.0000
  15.500   1.3816   0.06426   0.06070  -0.0246   0.0023   1.0000
  15.750   1.3680   0.07034   0.06692  -0.0275   0.0022   1.0000
  16.000   1.3509   0.07733   0.07406  -0.0309   0.0023   1.0000
  16.250   1.3360   0.08423   0.08110  -0.0344   0.0023   1.0000
  16.500   1.3244   0.09081   0.08780  -0.0379   0.0022   1.0000
  16.750   1.2984   0.10028   0.09744  -0.0430   0.0023   1.0000
  17.000   1.2845   0.10776   0.10504  -0.0471   0.0022   1.0000
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