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SA7036 (sa7036-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 500,000
Max Cl/Cd: 97.12 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7036-il-500000.txt
Download as CSV file: xf-sa7036-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3927   0.08148   0.07933  -0.0362   1.0000   0.0151
  -8.250  -0.3974   0.07758   0.07547  -0.0374   1.0000   0.0152
  -8.000  -0.4081   0.07440   0.07234  -0.0371   1.0000   0.0155
  -7.750  -0.4285   0.07160   0.06963  -0.0359   1.0000   0.0154
  -7.500  -0.4449   0.06854   0.06661  -0.0359   1.0000   0.0154
  -7.250  -0.4399   0.06376   0.06182  -0.0409   0.9980   0.0157
  -7.000  -0.4153   0.05857   0.05655  -0.0489   0.9945   0.0163
  -6.750  -0.3914   0.05227   0.05011  -0.0570   0.9895   0.0168
  -6.500  -0.3638   0.04588   0.04351  -0.0644   0.9856   0.0180
  -6.250  -0.3266   0.04007   0.03718  -0.0702   0.9823   0.0210
  -6.000  -0.3113   0.03130   0.02787  -0.0746   0.9757   0.0224
  -5.750  -0.2791   0.02948   0.02604  -0.0773   0.9735   0.0239
  -5.500  -0.2448   0.02701   0.02329  -0.0799   0.9714   0.0266
  -5.250  -0.2185   0.02398   0.01980  -0.0808   0.9659   0.0318
  -5.000  -0.1900   0.01620   0.01087  -0.0793   0.9607   0.0156
  -4.750  -0.1579   0.01463   0.00908  -0.0799   0.9575   0.0154
  -4.500  -0.1331   0.01320   0.00749  -0.0792   0.9508   0.0157
  -4.250  -0.1061   0.01210   0.00631  -0.0789   0.9452   0.0167
  -4.000  -0.0806   0.01144   0.00559  -0.0782   0.9384   0.0179
  -3.750  -0.0549   0.01095   0.00505  -0.0775   0.9313   0.0196
  -3.500  -0.0294   0.01055   0.00459  -0.0767   0.9241   0.0210
  -3.250  -0.0046   0.00973   0.00366  -0.0759   0.9165   0.0235
  -3.000   0.0213   0.00936   0.00324  -0.0752   0.9086   0.0272
  -2.750   0.0474   0.00895   0.00280  -0.0745   0.9010   0.0394
  -2.500   0.0723   0.00822   0.00247  -0.0740   0.8916   0.1379
  -2.250   0.0980   0.00777   0.00226  -0.0736   0.8828   0.2237
  -2.000   0.1235   0.00729   0.00211  -0.0732   0.8729   0.3313
  -1.750   0.1488   0.00684   0.00200  -0.0728   0.8617   0.4475
  -1.500   0.1739   0.00642   0.00193  -0.0722   0.8503   0.5680
  -1.250   0.1990   0.00611   0.00188  -0.0714   0.8384   0.6648
  -1.000   0.2237   0.00588   0.00183  -0.0704   0.8259   0.7423
  -0.750   0.2473   0.00569   0.00180  -0.0691   0.8125   0.8146
  -0.500   0.2693   0.00555   0.00178  -0.0672   0.7981   0.8829
  -0.250   0.2954   0.00549   0.00173  -0.0662   0.7831   0.9423
   0.000   0.3350   0.00548   0.00164  -0.0685   0.7670   0.9787
   0.250   0.3779   0.00551   0.00153  -0.0717   0.7490   1.0000
   0.500   0.4025   0.00560   0.00150  -0.0709   0.7309   1.0000
   0.750   0.4276   0.00570   0.00149  -0.0703   0.7123   1.0000
   1.000   0.4531   0.00582   0.00149  -0.0697   0.6932   1.0000
   1.250   0.4788   0.00595   0.00150  -0.0692   0.6744   1.0000
   1.500   0.5047   0.00607   0.00153  -0.0688   0.6550   1.0000
   1.750   0.5307   0.00622   0.00157  -0.0684   0.6344   1.0000
   2.000   0.5566   0.00638   0.00163  -0.0679   0.6134   1.0000
   2.250   0.5827   0.00653   0.00169  -0.0676   0.5922   1.0000
   2.500   0.6087   0.00671   0.00177  -0.0672   0.5718   1.0000
   2.750   0.6350   0.00688   0.00185  -0.0669   0.5512   1.0000
   3.250   0.6872   0.00726   0.00207  -0.0662   0.5097   1.0000
   3.500   0.7132   0.00747   0.00220  -0.0659   0.4895   1.0000
   3.750   0.7392   0.00768   0.00233  -0.0656   0.4677   1.0000
   4.250   0.7907   0.00816   0.00266  -0.0649   0.4220   1.0000
   4.500   0.8163   0.00842   0.00284  -0.0645   0.4011   1.0000
   4.750   0.8420   0.00867   0.00303  -0.0642   0.3794   1.0000
   5.000   0.8675   0.00895   0.00325  -0.0638   0.3586   1.0000
   5.250   0.8930   0.00922   0.00347  -0.0635   0.3379   1.0000
   5.500   0.9181   0.00955   0.00371  -0.0631   0.3162   1.0000
   5.750   0.9432   0.00986   0.00396  -0.0627   0.2945   1.0000
   6.000   0.9679   0.01022   0.00425  -0.0623   0.2725   1.0000
   6.250   0.9925   0.01058   0.00454  -0.0619   0.2506   1.0000
   6.500   1.0170   0.01095   0.00486  -0.0614   0.2304   1.0000
   6.750   1.0411   0.01136   0.00520  -0.0610   0.2086   1.0000
   7.000   1.0649   0.01179   0.00557  -0.0604   0.1883   1.0000
   7.250   1.0885   0.01224   0.00596  -0.0599   0.1681   1.0000
   7.500   1.1116   0.01273   0.00638  -0.0593   0.1489   1.0000
   7.750   1.1347   0.01320   0.00681  -0.0587   0.1315   1.0000
   8.000   1.1572   0.01374   0.00729  -0.0580   0.1137   1.0000
   8.250   1.1790   0.01432   0.00783  -0.0573   0.0963   1.0000
   8.500   1.2005   0.01492   0.00838  -0.0565   0.0800   1.0000
   8.750   1.2208   0.01563   0.00900  -0.0555   0.0638   1.0000
   9.000   1.2401   0.01641   0.00969  -0.0545   0.0491   1.0000
   9.250   1.2595   0.01714   0.01039  -0.0534   0.0393   1.0000
   9.500   1.2794   0.01778   0.01106  -0.0524   0.0328   1.0000
   9.750   1.2976   0.01856   0.01188  -0.0511   0.0273   1.0000
  10.000   1.3150   0.01936   0.01270  -0.0498   0.0224   1.0000
  10.250   1.3316   0.02017   0.01360  -0.0483   0.0184   1.0000
  10.500   1.3430   0.02137   0.01483  -0.0461   0.0136   1.0000
  10.750   1.3536   0.02244   0.01595  -0.0438   0.0107   1.0000
  11.000   1.3560   0.02387   0.01751  -0.0403   0.0094   1.0000
  11.250   1.3642   0.02494   0.01868  -0.0378   0.0084   1.0000
  11.500   1.3723   0.02602   0.01985  -0.0356   0.0077   1.0000
  11.750   1.3743   0.02757   0.02148  -0.0329   0.0070   1.0000
  12.000   1.3677   0.02985   0.02392  -0.0298   0.0067   1.0000
  12.250   1.3718   0.03145   0.02564  -0.0279   0.0063   1.0000
  12.500   1.3731   0.03338   0.02773  -0.0262   0.0061   1.0000
  12.750   1.3737   0.03551   0.03000  -0.0248   0.0059   1.0000
  13.000   1.3716   0.03805   0.03268  -0.0236   0.0057   1.0000
  13.250   1.3685   0.04088   0.03565  -0.0228   0.0057   1.0000
  13.500   1.3655   0.04388   0.03880  -0.0225   0.0055   1.0000
  13.750   1.3616   0.04718   0.04223  -0.0226   0.0053   1.0000
  14.000   1.3553   0.05101   0.04621  -0.0230   0.0053   1.0000
  14.250   1.3508   0.05482   0.05016  -0.0239   0.0051   1.0000
  14.500   1.3437   0.05919   0.05467  -0.0252   0.0050   1.0000
  14.750   1.3356   0.06391   0.05953  -0.0269   0.0050   1.0000
  15.000   1.3265   0.06903   0.06479  -0.0289   0.0049   1.0000
  15.250   1.3162   0.07460   0.07049  -0.0314   0.0048   1.0000
  15.500   1.3057   0.08037   0.07642  -0.0340   0.0048   1.0000
  15.750   1.2938   0.08664   0.08282  -0.0371   0.0047   1.0000
  16.000   1.2822   0.09308   0.08941  -0.0403   0.0047   1.0000
  16.250   1.2699   0.09983   0.09631  -0.0438   0.0047   1.0000
  16.500   1.2565   0.10701   0.10365  -0.0475   0.0048   1.0000
  16.750   1.2447   0.11409   0.11083  -0.0515   0.0047   1.0000
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