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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 500,000
Max Cl/Cd: 104.81 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9037-il-500000.txt
Download as CSV file: xf-s9037-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9037 (9%)                                      
  
 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  -0.3451   0.08765   0.08548  -0.0355   1.0000   0.0147
  -8.250  -0.3429   0.08531   0.08317  -0.0351   1.0000   0.0150
  -8.000  -0.3429   0.08298   0.08088  -0.0347   1.0000   0.0153
  -7.750  -0.3478   0.08102   0.07897  -0.0335   1.0000   0.0155
  -7.500  -0.3697   0.07999   0.07802  -0.0293   1.0000   0.0155
  -7.250  -0.3514   0.07544   0.07348  -0.0361   0.9952   0.0158
  -7.000  -0.3270   0.07045   0.06848  -0.0446   0.9895   0.0169
  -6.750  -0.2969   0.06371   0.06170  -0.0569   0.9846   0.0184
  -6.500  -0.2571   0.05514   0.05299  -0.0717   0.9782   0.0198
  -6.250  -0.2236   0.04774   0.04535  -0.0812   0.9734   0.0200
  -6.000  -0.2082   0.03817   0.03544  -0.0884   0.9651   0.0209
  -5.750  -0.1840   0.03554   0.03273  -0.0904   0.9590   0.0215
  -5.500  -0.1621   0.03302   0.03005  -0.0915   0.9511   0.0223
  -5.250  -0.1397   0.03037   0.02720  -0.0921   0.9434   0.0234
  -5.000  -0.1190   0.02766   0.02421  -0.0917   0.9337   0.0253
  -4.750  -0.0911   0.02762   0.02377  -0.0906   0.9258   0.0279
  -4.500  -0.0768   0.02191   0.01762  -0.0904   0.9161   0.0299
  -4.250  -0.0510   0.01674   0.01157  -0.0879   0.9076   0.0144
  -4.000  -0.0276   0.01391   0.00841  -0.0869   0.9002   0.0128
  -3.750  -0.0024   0.01248   0.00676  -0.0860   0.8914   0.0123
  -3.500   0.0233   0.01147   0.00556  -0.0852   0.8838   0.0121
  -3.250   0.0491   0.01070   0.00469  -0.0845   0.8748   0.0124
  -3.000   0.0753   0.01011   0.00400  -0.0839   0.8661   0.0129
  -2.750   0.1020   0.00967   0.00345  -0.0833   0.8575   0.0141
  -2.500   0.1286   0.00912   0.00283  -0.0828   0.8475   0.0191
  -2.250   0.1550   0.00848   0.00236  -0.0824   0.8381   0.0727
  -2.000   0.1814   0.00807   0.00218  -0.0822   0.8289   0.1497
  -1.750   0.2076   0.00763   0.00207  -0.0820   0.8184   0.2525
  -1.500   0.2339   0.00726   0.00198  -0.0818   0.8083   0.3566
  -1.250   0.2596   0.00684   0.00190  -0.0814   0.7983   0.4887
  -1.000   0.2839   0.00635   0.00187  -0.0807   0.7874   0.6512
  -0.750   0.3035   0.00582   0.00190  -0.0784   0.7757   0.8350
  -0.500   0.3361   0.00564   0.00184  -0.0787   0.7640   0.9619
  -0.250   0.3834   0.00562   0.00170  -0.0827   0.7518   1.0000
   0.000   0.4088   0.00569   0.00165  -0.0821   0.7391   1.0000
   0.250   0.4345   0.00576   0.00161  -0.0816   0.7264   1.0000
   0.500   0.4604   0.00585   0.00159  -0.0810   0.7135   1.0000
   0.750   0.4864   0.00593   0.00158  -0.0806   0.7001   1.0000
   1.000   0.5126   0.00603   0.00158  -0.0801   0.6864   1.0000
   1.250   0.5388   0.00613   0.00159  -0.0797   0.6716   1.0000
   1.500   0.5650   0.00624   0.00161  -0.0793   0.6554   1.0000
   1.750   0.5912   0.00635   0.00164  -0.0789   0.6388   1.0000
   2.000   0.6175   0.00648   0.00170  -0.0785   0.6225   1.0000
   2.250   0.6438   0.00662   0.00175  -0.0782   0.6063   1.0000
   2.500   0.6700   0.00676   0.00182  -0.0778   0.5898   1.0000
   2.750   0.6961   0.00692   0.00190  -0.0774   0.5724   1.0000
   3.000   0.7221   0.00709   0.00198  -0.0770   0.5522   1.0000
   3.250   0.7477   0.00729   0.00210  -0.0766   0.5318   1.0000
   3.500   0.7737   0.00747   0.00222  -0.0762   0.5121   1.0000
   3.750   0.7995   0.00767   0.00234  -0.0759   0.4928   1.0000
   4.000   0.8251   0.00790   0.00249  -0.0755   0.4734   1.0000
   4.250   0.8508   0.00812   0.00266  -0.0751   0.4532   1.0000
   4.500   0.8762   0.00836   0.00284  -0.0747   0.4341   1.0000
   4.750   0.9015   0.00862   0.00302  -0.0743   0.4143   1.0000
   5.000   0.9265   0.00890   0.00324  -0.0739   0.3917   1.0000
   5.250   0.9515   0.00919   0.00346  -0.0734   0.3696   1.0000
   5.500   0.9762   0.00949   0.00369  -0.0730   0.3487   1.0000
   5.750   1.0010   0.00980   0.00394  -0.0725   0.3298   1.0000
   6.000   1.0255   0.01012   0.00422  -0.0720   0.3084   1.0000
   6.250   1.0497   0.01048   0.00451  -0.0715   0.2875   1.0000
   6.500   1.0739   0.01083   0.00482  -0.0710   0.2679   1.0000
   6.750   1.0972   0.01125   0.00516  -0.0704   0.2460   1.0000
   7.000   1.1203   0.01170   0.00551  -0.0698   0.2223   1.0000
   7.250   1.1433   0.01214   0.00591  -0.0691   0.2012   1.0000
   7.500   1.1658   0.01263   0.00632  -0.0684   0.1812   1.0000
   7.750   1.1881   0.01312   0.00676  -0.0677   0.1642   1.0000
   8.000   1.2104   0.01360   0.00721  -0.0669   0.1475   1.0000
   8.250   1.2318   0.01414   0.00770  -0.0661   0.1296   1.0000
   8.500   1.2521   0.01477   0.00824  -0.0651   0.1117   1.0000
   8.750   1.2728   0.01534   0.00878  -0.0642   0.0971   1.0000
   9.000   1.2928   0.01595   0.00935  -0.0632   0.0826   1.0000
   9.250   1.3119   0.01661   0.00995  -0.0621   0.0692   1.0000
   9.500   1.3304   0.01728   0.01061  -0.0609   0.0586   1.0000
   9.750   1.3479   0.01800   0.01131  -0.0595   0.0493   1.0000
  10.000   1.3645   0.01874   0.01205  -0.0581   0.0414   1.0000
  10.250   1.3816   0.01940   0.01276  -0.0567   0.0355   1.0000
  10.500   1.3952   0.02020   0.01357  -0.0547   0.0295   1.0000
  10.750   1.4062   0.02104   0.01440  -0.0524   0.0236   1.0000
  11.000   1.4137   0.02212   0.01548  -0.0497   0.0165   1.0000
  11.250   1.4163   0.02358   0.01694  -0.0465   0.0105   1.0000
  11.500   1.4236   0.02473   0.01819  -0.0441   0.0090   1.0000
  11.750   1.4269   0.02621   0.01975  -0.0415   0.0079   1.0000
  12.000   1.4265   0.02803   0.02171  -0.0388   0.0071   1.0000
  12.250   1.4300   0.02965   0.02349  -0.0367   0.0068   1.0000
  12.500   1.4327   0.03141   0.02538  -0.0349   0.0065   1.0000
  12.750   1.4340   0.03340   0.02749  -0.0333   0.0062   1.0000
  13.000   1.4339   0.03563   0.02985  -0.0319   0.0059   1.0000
  13.250   1.4331   0.03806   0.03240  -0.0308   0.0057   1.0000
  13.500   1.4303   0.04084   0.03532  -0.0300   0.0055   1.0000
  13.750   1.4243   0.04415   0.03876  -0.0296   0.0053   1.0000
  14.000   1.4177   0.04776   0.04250  -0.0296   0.0052   1.0000
  14.250   1.4063   0.05218   0.04707  -0.0300   0.0050   1.0000
  14.500   1.3988   0.05633   0.05137  -0.0307   0.0050   1.0000
  14.750   1.3813   0.06215   0.05735  -0.0322   0.0049   1.0000
  15.000   1.3718   0.06709   0.06244  -0.0337   0.0049   1.0000
  15.250   1.3593   0.07274   0.06825  -0.0357   0.0048   1.0000
  15.500   1.3435   0.07908   0.07475  -0.0380   0.0047   1.0000
  15.750   1.3363   0.08432   0.08013  -0.0403   0.0048   1.0000
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