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SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD7037-092-88 (sd7037-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.98 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7037-il-1000000.txt
Download as CSV file: xf-sd7037-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3851   0.09144   0.08980  -0.0317   1.0000   0.0118
  -9.000  -0.3865   0.08641   0.08479  -0.0343   1.0000   0.0123
  -8.750  -0.3876   0.08269   0.08110  -0.0355   1.0000   0.0124
  -8.500  -0.3300   0.06286   0.06142  -0.0395   0.9984   0.0128
  -8.250  -0.3241   0.05816   0.05673  -0.0433   0.9958   0.0129
  -8.000  -0.3188   0.05306   0.05164  -0.0479   0.9920   0.0131
  -7.750  -0.3149   0.04666   0.04524  -0.0552   0.9875   0.0132
  -7.500  -0.3122   0.03553   0.03403  -0.0721   0.9805   0.0132
  -7.250  -0.3081   0.02641   0.02469  -0.0805   0.9723   0.0134
  -7.000  -0.3045   0.02165   0.01974  -0.0819   0.9618   0.0136
  -6.750  -0.2972   0.01762   0.01548  -0.0822   0.9532   0.0138
  -6.500  -0.2868   0.01427   0.01187  -0.0819   0.9457   0.0144
  -6.250  -0.2817   0.01880   0.01507  -0.0874   0.9511   0.0117
  -6.000  -0.2629   0.01542   0.01117  -0.0861   0.9452   0.0111
  -5.750  -0.2392   0.01406   0.00959  -0.0854   0.9396   0.0113
  -5.500  -0.2148   0.01302   0.00837  -0.0846   0.9341   0.0115
  -5.250  -0.1898   0.01215   0.00735  -0.0840   0.9292   0.0116
  -5.000  -0.1642   0.01139   0.00648  -0.0835   0.9234   0.0118
  -4.750  -0.1386   0.01071   0.00571  -0.0829   0.9177   0.0119
  -4.500  -0.1125   0.01013   0.00504  -0.0824   0.9121   0.0121
  -4.250  -0.0857   0.00982   0.00468  -0.0821   0.9055   0.0124
  -4.000  -0.0598   0.00916   0.00393  -0.0815   0.8994   0.0127
  -3.750  -0.0334   0.00852   0.00322  -0.0812   0.8919   0.0131
  -3.250   0.0209   0.00784   0.00244  -0.0806   0.8768   0.0148
  -3.000   0.0482   0.00762   0.00216  -0.0803   0.8686   0.0159
  -2.750   0.0758   0.00738   0.00186  -0.0801   0.8589   0.0174
  -2.500   0.1034   0.00718   0.00163  -0.0799   0.8489   0.0209
  -2.250   0.1304   0.00676   0.00140  -0.0797   0.8377   0.0730
  -2.000   0.1575   0.00651   0.00127  -0.0795   0.8251   0.1228
  -1.750   0.1846   0.00627   0.00116  -0.0794   0.8110   0.1794
  -1.250   0.2385   0.00576   0.00102  -0.0791   0.7787   0.3369
  -1.000   0.2650   0.00548   0.00098  -0.0790   0.7607   0.4427
  -0.750   0.2915   0.00526   0.00096  -0.0787   0.7420   0.5404
  -0.500   0.3178   0.00510   0.00097  -0.0784   0.7230   0.6287
  -0.250   0.3437   0.00495   0.00100  -0.0779   0.7037   0.7180
   0.000   0.3694   0.00487   0.00103  -0.0773   0.6839   0.7839
   0.250   0.3946   0.00485   0.00107  -0.0765   0.6643   0.8367
   0.500   0.4184   0.00482   0.00110  -0.0754   0.6452   0.8892
   0.750   0.4422   0.00480   0.00112  -0.0742   0.6259   0.9477
   1.000   0.4821   0.00488   0.00111  -0.0767   0.6043   0.9963
   1.250   0.5100   0.00501   0.00114  -0.0767   0.5842   1.0000
   1.500   0.5368   0.00515   0.00118  -0.0765   0.5641   1.0000
   2.000   0.5906   0.00545   0.00129  -0.0761   0.5243   1.0000
   2.250   0.6174   0.00561   0.00136  -0.0759   0.5040   1.0000
   2.500   0.6442   0.00578   0.00144  -0.0756   0.4839   1.0000
   2.750   0.6711   0.00594   0.00152  -0.0755   0.4640   1.0000
   3.000   0.6978   0.00613   0.00161  -0.0753   0.4437   1.0000
   3.250   0.7245   0.00632   0.00172  -0.0750   0.4233   1.0000
   3.500   0.7512   0.00651   0.00183  -0.0748   0.4033   1.0000
   3.750   0.7776   0.00673   0.00195  -0.0746   0.3822   1.0000
   4.000   0.8041   0.00694   0.00208  -0.0744   0.3625   1.0000
   4.250   0.8304   0.00716   0.00223  -0.0742   0.3413   1.0000
   4.500   0.8566   0.00740   0.00239  -0.0739   0.3224   1.0000
   4.750   0.8829   0.00763   0.00255  -0.0737   0.3034   1.0000
   5.000   0.9089   0.00789   0.00273  -0.0734   0.2835   1.0000
   5.250   0.9347   0.00816   0.00293  -0.0731   0.2648   1.0000
   5.500   0.9602   0.00847   0.00313  -0.0728   0.2416   1.0000
   6.000   1.0108   0.00910   0.00360  -0.0721   0.2018   1.0000
   6.250   1.0357   0.00945   0.00385  -0.0717   0.1820   1.0000
   6.500   1.0604   0.00982   0.00413  -0.0713   0.1631   1.0000
   6.750   1.0851   0.01016   0.00442  -0.0708   0.1461   1.0000
   7.000   1.1098   0.01051   0.00471  -0.0704   0.1314   1.0000
   7.250   1.1340   0.01090   0.00502  -0.0699   0.1160   1.0000
   7.500   1.1580   0.01130   0.00536  -0.0694   0.1018   1.0000
   7.750   1.1813   0.01177   0.00574  -0.0688   0.0863   1.0000
   8.000   1.2044   0.01223   0.00614  -0.0682   0.0724   1.0000
   8.250   1.2273   0.01271   0.00656  -0.0675   0.0597   1.0000
   8.500   1.2492   0.01327   0.00704  -0.0667   0.0457   1.0000
   8.750   1.2695   0.01399   0.00765  -0.0657   0.0300   1.0000
   9.000   1.2875   0.01491   0.00844  -0.0644   0.0144   1.0000
   9.250   1.3076   0.01559   0.00912  -0.0632   0.0109   1.0000
   9.500   1.3289   0.01612   0.00971  -0.0623   0.0101   1.0000
   9.750   1.3490   0.01673   0.01036  -0.0612   0.0092   1.0000
  10.000   1.3676   0.01747   0.01117  -0.0599   0.0086   1.0000
  10.250   1.3846   0.01829   0.01208  -0.0584   0.0081   1.0000
  10.500   1.4028   0.01893   0.01279  -0.0570   0.0080   1.0000
  10.750   1.4197   0.01962   0.01356  -0.0555   0.0077   1.0000
  11.000   1.4347   0.02039   0.01440  -0.0538   0.0075   1.0000
  11.250   1.4465   0.02115   0.01524  -0.0514   0.0073   1.0000
  11.500   1.4568   0.02195   0.01612  -0.0489   0.0070   1.0000
  11.750   1.4657   0.02284   0.01709  -0.0464   0.0068   1.0000
  12.000   1.4726   0.02389   0.01822  -0.0438   0.0066   1.0000
  12.250   1.4777   0.02510   0.01952  -0.0411   0.0064   1.0000
  12.500   1.4796   0.02658   0.02110  -0.0384   0.0063   1.0000
  12.750   1.4754   0.02860   0.02324  -0.0354   0.0061   1.0000
  13.000   1.4741   0.03054   0.02530  -0.0331   0.0061   1.0000
  13.250   1.4645   0.03335   0.02825  -0.0307   0.0059   1.0000
  13.500   1.4612   0.03584   0.03086  -0.0292   0.0059   1.0000
  13.750   1.4601   0.03831   0.03345  -0.0282   0.0058   1.0000
  14.000   1.4572   0.04115   0.03641  -0.0276   0.0058   1.0000
  14.250   1.4565   0.04392   0.03930  -0.0273   0.0058   1.0000
  14.500   1.4523   0.04730   0.04281  -0.0274   0.0058   1.0000
  14.750   1.4476   0.05094   0.04656  -0.0279   0.0057   1.0000
  15.000   1.4457   0.05440   0.05014  -0.0287   0.0057   1.0000
  15.250   1.4370   0.05899   0.05486  -0.0299   0.0057   1.0000
  15.500   1.4288   0.06373   0.05973  -0.0315   0.0057   1.0000
  15.750   1.4203   0.06876   0.06488  -0.0335   0.0056   1.0000
  16.000   1.4123   0.07392   0.07017  -0.0357   0.0056   1.0000
  16.250   1.3988   0.08012   0.07650  -0.0384   0.0056   1.0000
  16.500   1.3891   0.08594   0.08244  -0.0412   0.0056   1.0000
  16.750   1.3772   0.09230   0.08894  -0.0443   0.0056   1.0000
  17.000   1.3651   0.09890   0.09566  -0.0476   0.0056   1.0000
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