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SA7036 (sa7036-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 500,000
Max Cl/Cd: 88.94 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7036-il-500000-n5.txt
Download as CSV file: xf-sa7036-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4122   0.08350   0.08127  -0.0322   1.0000   0.0049
  -8.750  -0.4154   0.07916   0.07697  -0.0339   1.0000   0.0048
  -8.250  -0.4294   0.07157   0.06948  -0.0361   1.0000   0.0047
  -8.000  -0.4457   0.06705   0.06502  -0.0380   0.9981   0.0047
  -7.750  -0.4310   0.05561   0.05351  -0.0557   0.9871   0.0046
  -7.500  -0.4369   0.03056   0.02750  -0.0743   0.9729   0.0046
  -7.250  -0.4236   0.02291   0.01888  -0.0761   0.9645   0.0048
  -7.000  -0.4019   0.01970   0.01515  -0.0766   0.9584   0.0050
  -6.750  -0.3766   0.01870   0.01400  -0.0767   0.9530   0.0053
  -6.500  -0.3521   0.01763   0.01274  -0.0764   0.9467   0.0055
  -6.250  -0.3267   0.01653   0.01143  -0.0763   0.9416   0.0058
  -6.000  -0.3026   0.01554   0.01023  -0.0757   0.9346   0.0062
  -5.750  -0.2769   0.01482   0.00935  -0.0753   0.9289   0.0068
  -5.500  -0.2515   0.01424   0.00861  -0.0748   0.9218   0.0074
  -5.250  -0.2262   0.01347   0.00768  -0.0742   0.9153   0.0079
  -5.000  -0.2018   0.01241   0.00651  -0.0737   0.9078   0.0085
  -4.750  -0.1761   0.01186   0.00588  -0.0732   0.9010   0.0091
  -4.500  -0.1500   0.01133   0.00527  -0.0728   0.8934   0.0100
  -4.250  -0.1239   0.01087   0.00470  -0.0724   0.8860   0.0108
  -4.000  -0.0972   0.01056   0.00432  -0.0721   0.8767   0.0116
  -3.750  -0.0713   0.00999   0.00367  -0.0717   0.8671   0.0135
  -3.500  -0.0446   0.00967   0.00326  -0.0713   0.8573   0.0146
  -3.250  -0.0175   0.00940   0.00290  -0.0710   0.8468   0.0157
  -3.000   0.0097   0.00919   0.00262  -0.0707   0.8362   0.0172
  -2.750   0.0368   0.00894   0.00230  -0.0704   0.8248   0.0212
  -2.500   0.0639   0.00871   0.00207  -0.0702   0.8123   0.0344
  -2.250   0.0908   0.00845   0.00186  -0.0700   0.7987   0.0662
  -2.000   0.1176   0.00819   0.00170  -0.0698   0.7836   0.1128
  -1.750   0.1443   0.00796   0.00156  -0.0696   0.7673   0.1634
  -1.500   0.1708   0.00768   0.00146  -0.0694   0.7502   0.2392
  -1.250   0.1970   0.00736   0.00137  -0.0693   0.7328   0.3394
  -1.000   0.2231   0.00704   0.00133  -0.0691   0.7157   0.4483
  -0.750   0.2493   0.00684   0.00130  -0.0688   0.6982   0.5334
  -0.500   0.2755   0.00669   0.00130  -0.0684   0.6805   0.6077
  -0.250   0.3016   0.00661   0.00130  -0.0680   0.6627   0.6674
   0.000   0.3275   0.00655   0.00131  -0.0675   0.6447   0.7196
   0.250   0.3528   0.00649   0.00134  -0.0668   0.6260   0.7734
   0.500   0.3767   0.00644   0.00138  -0.0657   0.6072   0.8316
   0.750   0.3993   0.00641   0.00142  -0.0642   0.5891   0.8910
   1.000   0.4277   0.00645   0.00144  -0.0640   0.5702   0.9468
   1.250   0.4648   0.00655   0.00144  -0.0660   0.5502   0.9848
   1.500   0.4962   0.00668   0.00147  -0.0668   0.5312   1.0000
   1.750   0.5223   0.00684   0.00153  -0.0665   0.5108   1.0000
   2.000   0.5483   0.00702   0.00159  -0.0662   0.4898   1.0000
   2.250   0.5744   0.00720   0.00168  -0.0659   0.4687   1.0000
   2.500   0.6006   0.00739   0.00177  -0.0656   0.4502   1.0000
   2.750   0.6270   0.00757   0.00186  -0.0653   0.4322   1.0000
   3.000   0.6532   0.00776   0.00199  -0.0651   0.4133   1.0000
   3.250   0.6795   0.00796   0.00211  -0.0648   0.3960   1.0000
   3.500   0.7056   0.00817   0.00224  -0.0645   0.3779   1.0000
   3.750   0.7317   0.00838   0.00239  -0.0643   0.3599   1.0000
   4.000   0.7575   0.00863   0.00257  -0.0640   0.3387   1.0000
   4.250   0.7833   0.00889   0.00274  -0.0637   0.3181   1.0000
   4.500   0.8090   0.00915   0.00293  -0.0634   0.2988   1.0000
   4.750   0.8347   0.00942   0.00313  -0.0631   0.2818   1.0000
   5.000   0.8604   0.00968   0.00336  -0.0628   0.2661   1.0000
   5.250   0.8858   0.00996   0.00359  -0.0625   0.2482   1.0000
   5.500   0.9112   0.01026   0.00383  -0.0621   0.2312   1.0000
   5.750   0.9360   0.01060   0.00410  -0.0617   0.2122   1.0000
   6.000   0.9608   0.01095   0.00439  -0.0614   0.1942   1.0000
   6.250   0.9855   0.01131   0.00471  -0.0609   0.1763   1.0000
   6.500   1.0097   0.01170   0.00504  -0.0605   0.1585   1.0000
   6.750   1.0338   0.01210   0.00539  -0.0600   0.1435   1.0000
   7.000   1.0576   0.01252   0.00576  -0.0595   0.1266   1.0000
   7.250   1.0810   0.01297   0.00616  -0.0589   0.1099   1.0000
   7.500   1.1042   0.01344   0.00660  -0.0583   0.0955   1.0000
   7.750   1.1272   0.01391   0.00704  -0.0577   0.0830   1.0000
   8.000   1.1493   0.01446   0.00754  -0.0570   0.0691   1.0000
   8.250   1.1710   0.01503   0.00806  -0.0562   0.0563   1.0000
   8.500   1.1918   0.01568   0.00864  -0.0554   0.0433   1.0000
   8.750   1.2127   0.01628   0.00922  -0.0545   0.0345   1.0000
   9.000   1.2334   0.01688   0.00985  -0.0536   0.0276   1.0000
   9.250   1.2536   0.01750   0.01048  -0.0526   0.0227   1.0000
   9.500   1.2733   0.01813   0.01113  -0.0516   0.0184   1.0000
   9.750   1.2926   0.01877   0.01181  -0.0505   0.0151   1.0000
  10.000   1.3101   0.01952   0.01258  -0.0492   0.0113   1.0000
  10.250   1.3269   0.02029   0.01337  -0.0478   0.0080   1.0000
  10.500   1.3415   0.02118   0.01429  -0.0462   0.0051   1.0000
  10.750   1.3546   0.02205   0.01525  -0.0442   0.0038   1.0000
  11.000   1.3650   0.02296   0.01624  -0.0419   0.0032   1.0000
  11.250   1.3748   0.02390   0.01728  -0.0395   0.0029   1.0000
  11.500   1.3841   0.02490   0.01838  -0.0373   0.0026   1.0000
  11.750   1.3930   0.02593   0.01953  -0.0351   0.0025   1.0000
  12.000   1.3998   0.02715   0.02087  -0.0330   0.0023   1.0000
  12.250   1.4063   0.02844   0.02229  -0.0310   0.0022   1.0000
  12.500   1.4110   0.02992   0.02389  -0.0290   0.0021   1.0000
  12.750   1.4152   0.03151   0.02560  -0.0273   0.0020   1.0000
  13.000   1.4172   0.03338   0.02759  -0.0257   0.0019   1.0000
  13.250   1.4181   0.03546   0.02982  -0.0244   0.0018   1.0000
  13.500   1.4147   0.03811   0.03261  -0.0233   0.0017   1.0000
  13.750   1.4125   0.04082   0.03546  -0.0227   0.0017   1.0000
  14.000   1.4019   0.04470   0.03955  -0.0225   0.0016   1.0000
  14.250   1.3967   0.04823   0.04323  -0.0229   0.0016   1.0000
  14.500   1.3878   0.05251   0.04766  -0.0238   0.0016   1.0000
  14.750   1.3797   0.05696   0.05227  -0.0251   0.0016   1.0000
  15.000   1.3695   0.06201   0.05748  -0.0270   0.0016   1.0000
  15.250   1.3592   0.06737   0.06299  -0.0293   0.0015   1.0000
  15.500   1.3454   0.07358   0.06936  -0.0322   0.0015   1.0000
  15.750   1.3311   0.08018   0.07612  -0.0354   0.0015   1.0000
  16.000   1.3160   0.08718   0.08327  -0.0389   0.0015   1.0000
  16.250   1.2991   0.09482   0.09106  -0.0429   0.0015   1.0000
  16.500   1.2814   0.10287   0.09926  -0.0472   0.0015   1.0000
  16.750   1.2639   0.11106   0.10759  -0.0516   0.0015   1.0000
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