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SA7036 (sa7036-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 50,000
Max Cl/Cd: 33.61 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7036-il-50000.txt
Download as CSV file: xf-sa7036-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7036                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3999   0.11269   0.10589  -0.0199   1.0000   0.2055
  -8.750  -0.3805   0.10745   0.10065  -0.0187   1.0000   0.2139
  -8.500  -0.4021   0.10757   0.10094  -0.0209   1.0000   0.2203
  -8.250  -0.3796   0.10219   0.09555  -0.0192   1.0000   0.2322
  -8.000  -0.3731   0.09867   0.09209  -0.0188   1.0000   0.2405
  -7.750  -0.3965   0.09866   0.09228  -0.0197   1.0000   0.2490
  -7.500  -0.3794   0.09425   0.08788  -0.0181   1.0000   0.2618
  -7.250  -0.3715   0.09072   0.08441  -0.0168   1.0000   0.2737
  -6.500  -0.3793   0.08350   0.07750  -0.0116   1.0000   0.3112
  -6.250  -0.3792   0.08114   0.07524  -0.0090   1.0000   0.3289
  -6.000  -0.3878   0.07934   0.07358  -0.0066   1.0000   0.3474
  -5.750  -0.4052   0.07817   0.07255  -0.0047   1.0000   0.3643
  -5.500  -0.3865   0.07439   0.06880  -0.0005   1.0000   0.3887
  -4.750  -0.3795   0.05069   0.04394  -0.0408   1.0000   0.1498
  -4.500  -0.3591   0.04571   0.03856  -0.0419   1.0000   0.1324
  -4.250  -0.3350   0.04104   0.03303  -0.0436   1.0000   0.1202
  -4.000  -0.3141   0.03759   0.02931  -0.0433   1.0000   0.1173
  -3.750  -0.2900   0.03438   0.02559  -0.0433   1.0000   0.1138
  -3.500  -0.2645   0.03164   0.02231  -0.0431   1.0000   0.1127
  -3.250  -0.2393   0.02956   0.01977  -0.0426   1.0000   0.1170
  -3.000  -0.2149   0.02774   0.01768  -0.0420   1.0000   0.1254
  -2.750  -0.1889   0.02619   0.01573  -0.0411   1.0000   0.1346
  -2.500  -0.1651   0.02467   0.01432  -0.0402   1.0000   0.1541
  -2.250  -0.1408   0.02319   0.01297  -0.0392   1.0000   0.2012
  -2.000  -0.1172   0.01972   0.01180  -0.0376   1.0000   0.5280
  -1.750  -0.1007   0.01820   0.01125  -0.0322   1.0000   1.0000
  -1.500  -0.0785   0.01842   0.01086  -0.0322   1.0000   1.0000
  -1.250  -0.0575   0.01871   0.01069  -0.0321   1.0000   1.0000
  -1.000  -0.0371   0.01905   0.01063  -0.0318   1.0000   1.0000
  -0.750  -0.0171   0.01944   0.01069  -0.0316   1.0000   1.0000
  -0.500   0.0025   0.01989   0.01086  -0.0314   1.0000   1.0000
  -0.250   0.0216   0.02039   0.01112  -0.0312   1.0000   1.0000
   0.000   0.0404   0.02095   0.01144  -0.0311   1.0000   1.0000
   0.250   0.0587   0.02157   0.01187  -0.0310   1.0000   1.0000
   0.500   0.0766   0.02225   0.01239  -0.0310   1.0000   1.0000
   0.750   0.1158   0.02337   0.01332  -0.0349   0.9898   1.0000
   1.000   0.1712   0.02474   0.01448  -0.0416   0.9719   1.0000
   1.250   0.2206   0.02586   0.01547  -0.0469   0.9527   1.0000
   1.500   0.2682   0.02684   0.01635  -0.0516   0.9332   1.0000
   1.750   0.3199   0.02776   0.01721  -0.0567   0.9147   1.0000
   2.000   0.3578   0.02845   0.01788  -0.0593   0.8940   1.0000
   2.250   0.4036   0.02906   0.01849  -0.0628   0.8745   1.0000
   2.500   0.4475   0.02955   0.01901  -0.0657   0.8551   1.0000
   2.750   0.4861   0.02996   0.01946  -0.0676   0.8344   1.0000
   3.000   0.5371   0.03003   0.01963  -0.0709   0.8161   1.0000
   3.250   0.5724   0.03027   0.01995  -0.0717   0.7950   1.0000
   3.500   0.6169   0.03009   0.01987  -0.0732   0.7760   1.0000
   3.750   0.6650   0.02951   0.01946  -0.0746   0.7584   1.0000
   4.000   0.6920   0.02969   0.01973  -0.0736   0.7357   1.0000
   4.250   0.7353   0.02899   0.01915  -0.0738   0.7170   1.0000
   4.500   0.7635   0.02901   0.01932  -0.0725   0.6940   1.0000
   4.750   0.8034   0.02826   0.01866  -0.0719   0.6736   1.0000
   5.000   0.8293   0.02837   0.01887  -0.0702   0.6489   1.0000
   5.500   0.8896   0.02808   0.01873  -0.0672   0.6005   1.0000
   5.750   0.9164   0.02823   0.01892  -0.0656   0.5746   1.0000
   6.000   0.9405   0.02862   0.01937  -0.0639   0.5478   1.0000
   6.250   0.9646   0.02905   0.01988  -0.0621   0.5206   1.0000
   6.500   0.9884   0.02953   0.02040  -0.0604   0.4930   1.0000
   6.750   1.0116   0.03010   0.02099  -0.0587   0.4651   1.0000
   7.000   1.0341   0.03077   0.02168  -0.0569   0.4372   1.0000
   7.250   1.0560   0.03153   0.02245  -0.0552   0.4091   1.0000
   7.500   1.0772   0.03243   0.02343  -0.0535   0.3814   1.0000
   7.750   1.0976   0.03342   0.02443  -0.0517   0.3536   1.0000
   8.000   1.1171   0.03448   0.02549  -0.0499   0.3258   1.0000
   8.250   1.1360   0.03568   0.02669  -0.0481   0.2985   1.0000
   8.500   1.1540   0.03697   0.02797  -0.0462   0.2715   1.0000
   8.750   1.1717   0.03837   0.02935  -0.0444   0.2452   1.0000
   9.000   1.1873   0.04015   0.03119  -0.0425   0.2212   1.0000
   9.250   1.1987   0.04222   0.03343  -0.0403   0.1994   1.0000
   9.500   1.2147   0.04443   0.03565  -0.0386   0.1800   1.0000
   9.750   1.2274   0.04683   0.03810  -0.0368   0.1627   1.0000
  10.000   1.2388   0.04987   0.04132  -0.0350   0.1496   1.0000
  10.250   1.2504   0.05279   0.04433  -0.0333   0.1370   1.0000
  10.500   1.2375   0.05674   0.04900  -0.0299   0.1321   1.0000
  10.750   1.2508   0.06026   0.05250  -0.0287   0.1231   1.0000
  11.000   1.2326   0.06474   0.05752  -0.0258   0.1216   1.0000
  11.250   1.2109   0.06927   0.06242  -0.0233   0.1209   1.0000
  11.500   1.1863   0.07376   0.06715  -0.0212   0.1211   1.0000
  11.750   1.1602   0.07886   0.07243  -0.0204   0.1218   1.0000
  12.000   1.1348   0.08470   0.07841  -0.0211   0.1226   1.0000
  12.250   1.1108   0.09133   0.08513  -0.0230   0.1234   1.0000
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