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SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7037-092-88 (sd7037-il)
Reynolds number: 50,000
Max Cl/Cd: 34.48 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7037-il-50000.txt
Download as CSV file: xf-sd7037-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7037-092-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3761   0.09841   0.09184  -0.0209   1.0000   0.2441
  -7.500  -0.3629   0.09449   0.08795  -0.0194   1.0000   0.2566
  -7.250  -0.3613   0.09164   0.08520  -0.0181   1.0000   0.2661
  -7.000  -0.3883   0.09175   0.08552  -0.0164   1.0000   0.2747
  -6.750  -0.3777   0.08817   0.08198  -0.0144   1.0000   0.2883
  -6.500  -0.3728   0.08510   0.07899  -0.0123   1.0000   0.2999
  -6.250  -0.3793   0.08300   0.07702  -0.0101   1.0000   0.3110
  -5.750  -0.3911   0.07875   0.07296  -0.0057   1.0000   0.3395
  -5.500  -0.3915   0.07633   0.07063  -0.0030   1.0000   0.3558
  -5.250  -0.3915   0.07398   0.06836  -0.0001   1.0000   0.3737
  -4.250  -0.3733   0.05561   0.04971  -0.0255   1.0000   0.2643
  -4.000  -0.3032   0.04012   0.03214  -0.0461   1.0000   0.1220
  -3.750  -0.2786   0.03675   0.02827  -0.0468   1.0000   0.1187
  -3.500  -0.2531   0.03400   0.02502  -0.0472   1.0000   0.1195
  -3.250  -0.2266   0.03161   0.02212  -0.0473   1.0000   0.1215
  -3.000  -0.1994   0.02950   0.01948  -0.0471   1.0000   0.1237
  -2.750  -0.1740   0.02771   0.01750  -0.0467   1.0000   0.1310
  -2.500  -0.1493   0.02631   0.01592  -0.0461   1.0000   0.1452
  -2.250  -0.1245   0.02499   0.01448  -0.0452   1.0000   0.1707
  -2.000  -0.1004   0.02362   0.01338  -0.0445   1.0000   0.2286
  -1.750  -0.0730   0.02089   0.01227  -0.0439   1.0000   0.4655
  -1.500  -0.0645   0.01883   0.01173  -0.0374   1.0000   1.0000
  -1.250  -0.0413   0.01914   0.01139  -0.0376   1.0000   1.0000
  -1.000  -0.0198   0.01952   0.01133  -0.0375   1.0000   1.0000
  -0.750   0.0009   0.01994   0.01140  -0.0374   1.0000   1.0000
  -0.500   0.0209   0.02043   0.01158  -0.0373   1.0000   1.0000
  -0.250   0.0406   0.02097   0.01184  -0.0372   1.0000   1.0000
   0.000   0.0597   0.02156   0.01222  -0.0371   1.0000   1.0000
   0.250   0.0783   0.02222   0.01268  -0.0371   1.0000   1.0000
   0.500   0.0966   0.02294   0.01323  -0.0371   1.0000   1.0000
   0.750   0.1387   0.02415   0.01422  -0.0415   0.9885   1.0000
   1.000   0.1935   0.02554   0.01541  -0.0480   0.9707   1.0000
   1.250   0.2409   0.02663   0.01636  -0.0529   0.9512   1.0000
   1.500   0.2902   0.02767   0.01730  -0.0579   0.9324   1.0000
   1.750   0.3394   0.02858   0.01814  -0.0625   0.9138   1.0000
   2.000   0.3770   0.02928   0.01880  -0.0649   0.8932   1.0000
   2.250   0.4214   0.02990   0.01941  -0.0682   0.8738   1.0000
   2.500   0.4713   0.03032   0.01987  -0.0719   0.8555   1.0000
   2.750   0.5031   0.03080   0.02037  -0.0728   0.8340   1.0000
   3.000   0.5482   0.03096   0.02059  -0.0752   0.8146   1.0000
   3.250   0.6017   0.03071   0.02046  -0.0783   0.7969   1.0000
   3.500   0.6324   0.03091   0.02074  -0.0783   0.7750   1.0000
   3.750   0.6765   0.03047   0.02041  -0.0792   0.7560   1.0000
   4.000   0.7240   0.02967   0.01975  -0.0801   0.7380   1.0000
   4.250   0.7523   0.02969   0.01986  -0.0790   0.7150   1.0000
   4.500   0.7943   0.02888   0.01916  -0.0787   0.6949   1.0000
   4.750   0.8243   0.02874   0.01914  -0.0774   0.6712   1.0000
   5.000   0.8628   0.02803   0.01848  -0.0765   0.6489   1.0000
   5.250   0.8886   0.02817   0.01869  -0.0749   0.6227   1.0000
   5.500   0.9163   0.02824   0.01884  -0.0733   0.5966   1.0000
   5.750   0.9450   0.02829   0.01889  -0.0717   0.5703   1.0000
   6.000   0.9737   0.02839   0.01894  -0.0702   0.5437   1.0000
   6.250   0.9967   0.02893   0.01955  -0.0685   0.5158   1.0000
   6.500   1.0193   0.02956   0.02021  -0.0668   0.4880   1.0000
   6.750   1.0417   0.03029   0.02096  -0.0651   0.4608   1.0000
   7.000   1.0644   0.03105   0.02172  -0.0635   0.4340   1.0000
   7.250   1.0880   0.03181   0.02246  -0.0620   0.4080   1.0000
   7.500   1.1097   0.03275   0.02341  -0.0605   0.3822   1.0000
   7.750   1.1281   0.03398   0.02474  -0.0587   0.3571   1.0000
   8.000   1.1495   0.03513   0.02587  -0.0572   0.3333   1.0000
   8.250   1.1691   0.03636   0.02716  -0.0556   0.3095   1.0000
   8.500   1.1860   0.03793   0.02884  -0.0539   0.2873   1.0000
   8.750   1.2064   0.03926   0.03014  -0.0524   0.2649   1.0000
   9.000   1.2202   0.04114   0.03220  -0.0504   0.2446   1.0000
   9.250   1.2349   0.04305   0.03424  -0.0485   0.2251   1.0000
   9.500   1.2545   0.04485   0.03595  -0.0471   0.2051   1.0000
   9.750   1.2618   0.04737   0.03878  -0.0447   0.1887   1.0000
  10.000   1.2687   0.05000   0.04165  -0.0424   0.1729   1.0000
  10.250   1.2742   0.05235   0.04415  -0.0399   0.1569   1.0000
  10.500   1.2787   0.05466   0.04657  -0.0375   0.1418   1.0000
  11.000   1.2802   0.06051   0.05267  -0.0329   0.1200   1.0000
  11.250   1.2628   0.06459   0.05719  -0.0299   0.1166   1.0000
  11.500   1.2692   0.06766   0.06020  -0.0284   0.1084   1.0000
  11.750   1.2452   0.07186   0.06472  -0.0256   0.1081   1.0000
  12.000   1.2193   0.07658   0.06969  -0.0241   0.1081   1.0000
  12.250   1.1936   0.08197   0.07528  -0.0240   0.1086   1.0000
  12.500   1.1683   0.08811   0.08158  -0.0252   0.1092   1.0000
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