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SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD7037-092-88 (sd7037-il)
Reynolds number: 500,000
Max Cl/Cd: 99.29 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7037-il-500000.txt
Download as CSV file: xf-sd7037-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3023   0.08198   0.07986  -0.0377   1.0000   0.0211
  -9.000  -0.3055   0.07804   0.07595  -0.0384   1.0000   0.0212
  -8.750  -0.3163   0.07293   0.07088  -0.0381   1.0000   0.0215
  -8.500  -0.3211   0.07030   0.06829  -0.0367   1.0000   0.0217
  -8.250  -0.3294   0.06810   0.06613  -0.0347   1.0000   0.0219
  -8.000  -0.3406   0.06613   0.06420  -0.0324   1.0000   0.0221
  -7.750  -0.3399   0.06267   0.06076  -0.0337   0.9986   0.0224
  -7.500  -0.3309   0.05784   0.05594  -0.0382   0.9956   0.0228
  -7.250  -0.3254   0.05223   0.05033  -0.0446   0.9904   0.0231
  -7.000  -0.3121   0.04451   0.04257  -0.0565   0.9861   0.0237
  -6.750  -0.2982   0.03622   0.03415  -0.0672   0.9816   0.0245
  -6.500  -0.2789   0.02661   0.02394  -0.0776   0.9763   0.0272
  -6.250  -0.2634   0.01818   0.01517  -0.0830   0.9735   0.0283
  -6.000  -0.2382   0.01601   0.01297  -0.0846   0.9698   0.0292
  -5.750  -0.2142   0.01382   0.01062  -0.0858   0.9646   0.0307
  -5.500  -0.2188   0.02082   0.01619  -0.0860   0.9658   0.0204
  -5.250  -0.1884   0.01699   0.01180  -0.0870   0.9625   0.0183
  -5.000  -0.1552   0.01525   0.00978  -0.0880   0.9599   0.0182
  -4.750  -0.1272   0.01436   0.00878  -0.0880   0.9550   0.0188
  -4.500  -0.0997   0.01327   0.00754  -0.0877   0.9497   0.0189
  -4.250  -0.0703   0.01227   0.00643  -0.0878   0.9456   0.0189
  -4.000  -0.0454   0.01157   0.00565  -0.0869   0.9390   0.0193
  -3.750  -0.0189   0.01095   0.00497  -0.0864   0.9330   0.0201
  -3.500   0.0073   0.01047   0.00442  -0.0857   0.9271   0.0209
  -3.250   0.0324   0.00986   0.00376  -0.0850   0.9195   0.0226
  -3.000   0.0589   0.00950   0.00336  -0.0844   0.9133   0.0252
  -2.750   0.0847   0.00913   0.00298  -0.0837   0.9048   0.0319
  -2.500   0.1105   0.00847   0.00258  -0.0832   0.8975   0.0997
  -2.250   0.1363   0.00806   0.00239  -0.0827   0.8884   0.1647
  -2.000   0.1623   0.00765   0.00223  -0.0824   0.8794   0.2480
  -1.750   0.1881   0.00717   0.00208  -0.0820   0.8703   0.3616
  -1.500   0.2132   0.00667   0.00201  -0.0815   0.8588   0.4970
  -1.250   0.2383   0.00629   0.00195  -0.0808   0.8471   0.6132
  -1.000   0.2632   0.00601   0.00191  -0.0799   0.8347   0.7049
  -0.750   0.2871   0.00578   0.00188  -0.0786   0.8212   0.7886
  -0.500   0.3094   0.00561   0.00185  -0.0768   0.8065   0.8607
  -0.250   0.3326   0.00552   0.00180  -0.0752   0.7905   0.9198
   0.000   0.3702   0.00548   0.00169  -0.0769   0.7733   0.9736
   0.250   0.4083   0.00551   0.00160  -0.0790   0.7547   1.0000
   0.500   0.4340   0.00562   0.00156  -0.0784   0.7353   1.0000
   0.750   0.4600   0.00573   0.00155  -0.0779   0.7151   1.0000
   1.000   0.4860   0.00586   0.00156  -0.0775   0.6948   1.0000
   1.250   0.5122   0.00600   0.00158  -0.0770   0.6745   1.0000
   1.500   0.5384   0.00614   0.00161  -0.0766   0.6535   1.0000
   1.750   0.5645   0.00631   0.00166  -0.0762   0.6332   1.0000
   2.000   0.5909   0.00646   0.00171  -0.0759   0.6122   1.0000
   2.250   0.6170   0.00663   0.00179  -0.0755   0.5912   1.0000
   2.500   0.6432   0.00681   0.00187  -0.0751   0.5703   1.0000
   2.750   0.6695   0.00699   0.00196  -0.0748   0.5490   1.0000
   3.000   0.6955   0.00720   0.00206  -0.0744   0.5280   1.0000
   3.250   0.7217   0.00739   0.00219  -0.0741   0.5066   1.0000
   3.500   0.7475   0.00762   0.00231  -0.0737   0.4851   1.0000
   3.750   0.7736   0.00783   0.00245  -0.0734   0.4637   1.0000
   4.000   0.7993   0.00807   0.00260  -0.0730   0.4416   1.0000
   4.250   0.8251   0.00831   0.00278  -0.0726   0.4199   1.0000
   4.500   0.8506   0.00858   0.00296  -0.0722   0.3976   1.0000
   4.750   0.8761   0.00885   0.00315  -0.0719   0.3758   1.0000
   5.000   0.9014   0.00914   0.00337  -0.0715   0.3536   1.0000
   5.250   0.9266   0.00944   0.00360  -0.0711   0.3327   1.0000
   5.500   0.9516   0.00976   0.00384  -0.0707   0.3106   1.0000
   5.750   0.9765   0.01009   0.00410  -0.0702   0.2900   1.0000
   6.000   1.0010   0.01046   0.00439  -0.0697   0.2666   1.0000
   6.250   1.0253   0.01084   0.00469  -0.0692   0.2452   1.0000
   6.500   1.0496   0.01122   0.00500  -0.0688   0.2249   1.0000
   6.750   1.0734   0.01164   0.00535  -0.0682   0.2054   1.0000
   7.000   1.0972   0.01205   0.00570  -0.0677   0.1850   1.0000
   7.250   1.1204   0.01252   0.00608  -0.0670   0.1657   1.0000
   7.500   1.1436   0.01298   0.00648  -0.0664   0.1488   1.0000
   7.750   1.1666   0.01345   0.00690  -0.0658   0.1310   1.0000
   8.000   1.1892   0.01394   0.00735  -0.0651   0.1154   1.0000
   8.250   1.2109   0.01451   0.00783  -0.0643   0.0988   1.0000
   8.500   1.2325   0.01507   0.00834  -0.0635   0.0849   1.0000
   8.750   1.2536   0.01565   0.00890  -0.0626   0.0715   1.0000
   9.000   1.2741   0.01628   0.00948  -0.0616   0.0583   1.0000
   9.250   1.2921   0.01713   0.01022  -0.0604   0.0412   1.0000
   9.500   1.3063   0.01830   0.01127  -0.0585   0.0229   1.0000
   9.750   1.3222   0.01927   0.01224  -0.0568   0.0174   1.0000
  10.000   1.3374   0.02023   0.01325  -0.0551   0.0152   1.0000
  10.250   1.3517   0.02118   0.01430  -0.0532   0.0141   1.0000
  10.500   1.3652   0.02202   0.01524  -0.0512   0.0135   1.0000
  10.750   1.3756   0.02293   0.01624  -0.0487   0.0128   1.0000
  11.000   1.3841   0.02395   0.01735  -0.0461   0.0123   1.0000
  11.250   1.3903   0.02513   0.01862  -0.0434   0.0119   1.0000
  11.500   1.3934   0.02657   0.02016  -0.0406   0.0116   1.0000
  11.750   1.3929   0.02832   0.02202  -0.0377   0.0113   1.0000
  12.000   1.3887   0.03049   0.02433  -0.0348   0.0110   1.0000
  12.250   1.3921   0.03220   0.02616  -0.0329   0.0109   1.0000
  12.500   1.3946   0.03407   0.02816  -0.0312   0.0107   1.0000
  12.750   1.3955   0.03622   0.03044  -0.0297   0.0105   1.0000
  13.000   1.3954   0.03858   0.03292  -0.0285   0.0105   1.0000
  13.250   1.3973   0.04088   0.03534  -0.0277   0.0101   1.0000
  13.500   1.3962   0.04362   0.03821  -0.0271   0.0101   1.0000
  13.750   1.3946   0.04657   0.04129  -0.0268   0.0098   1.0000
  14.000   1.3920   0.04981   0.04466  -0.0269   0.0097   1.0000
  14.250   1.3888   0.05326   0.04824  -0.0272   0.0096   1.0000
  14.500   1.3837   0.05715   0.05227  -0.0278   0.0095   1.0000
  14.750   1.3785   0.06118   0.05644  -0.0287   0.0094   1.0000
  15.000   1.3733   0.06541   0.06080  -0.0300   0.0093   1.0000
  15.250   1.3663   0.07007   0.06562  -0.0315   0.0092   1.0000
  15.500   1.3589   0.07494   0.07064  -0.0333   0.0092   1.0000
  15.750   1.3509   0.08014   0.07598  -0.0354   0.0092   1.0000
  16.000   1.3425   0.08557   0.08155  -0.0379   0.0091   1.0000
  16.250   1.3318   0.09156   0.08771  -0.0406   0.0091   1.0000
  16.500   1.3217   0.09767   0.09397  -0.0437   0.0091   1.0000
  16.750   1.3102   0.10423   0.10068  -0.0471   0.0091   1.0000
  17.000   1.2978   0.11118   0.10779  -0.0508   0.0091   1.0000
  17.250   1.2852   0.11841   0.11518  -0.0549   0.0091   1.0000
  17.500   1.2717   0.12605   0.12298  -0.0594   0.0091   1.0000
  17.750   1.2573   0.13411   0.13120  -0.0643   0.0092   1.0000
  18.000   1.2417   0.14273   0.13998  -0.0696   0.0092   1.0000
  18.250   1.2245   0.15212   0.14954  -0.0756   0.0093   1.0000
  18.500   1.1999   0.16410   0.16172  -0.0834   0.0095   1.0000
  18.750   1.1689   0.17880   0.17662  -0.0929   0.0098   1.0000
  19.000   1.0539   0.23638   0.23430  -0.1202   0.0197   1.0000
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