Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SD7037-092-88 (sd7037-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.61 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7037-il-1000000-n5.txt
Download as CSV file: xf-sd7037-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4063   0.08590   0.08425  -0.0332   1.0000   0.0054
  -9.000  -0.4103   0.08165   0.08003  -0.0348   1.0000   0.0054
  -8.500  -0.5124   0.02416   0.02119  -0.0843   0.9547   0.0055
  -8.250  -0.4972   0.02132   0.01795  -0.0839   0.9472   0.0056
  -8.000  -0.4773   0.01956   0.01590  -0.0835   0.9416   0.0057
  -7.750  -0.4558   0.01808   0.01418  -0.0830   0.9357   0.0058
  -7.500  -0.4329   0.01697   0.01287  -0.0825   0.9307   0.0059
  -7.250  -0.4088   0.01599   0.01170  -0.0822   0.9256   0.0059
  -7.000  -0.3841   0.01520   0.01076  -0.0819   0.9200   0.0060
  -6.500  -0.3361   0.01284   0.00801  -0.0811   0.9089   0.0062
  -6.250  -0.3107   0.01211   0.00716  -0.0807   0.9030   0.0063
  -6.000  -0.2847   0.01153   0.00648  -0.0805   0.8974   0.0065
  -5.750  -0.2582   0.01108   0.00596  -0.0803   0.8908   0.0066
  -5.500  -0.2316   0.01070   0.00551  -0.0800   0.8846   0.0069
  -5.250  -0.2046   0.01031   0.00507  -0.0798   0.8775   0.0071
  -5.000  -0.1779   0.00991   0.00458  -0.0796   0.8703   0.0073
  -4.750  -0.1508   0.00951   0.00411  -0.0794   0.8621   0.0075
  -4.500  -0.1238   0.00916   0.00368  -0.0792   0.8534   0.0078
  -4.250  -0.0966   0.00886   0.00331  -0.0790   0.8430   0.0081
  -4.000  -0.0692   0.00861   0.00299  -0.0788   0.8320   0.0084
  -3.750  -0.0419   0.00841   0.00271  -0.0786   0.8195   0.0085
  -3.500  -0.0147   0.00811   0.00232  -0.0784   0.8055   0.0091
  -3.250   0.0126   0.00792   0.00206  -0.0781   0.7898   0.0096
  -3.000   0.0399   0.00780   0.00185  -0.0779   0.7727   0.0102
  -2.750   0.0672   0.00770   0.00167  -0.0777   0.7549   0.0109
  -2.250   0.1220   0.00755   0.00136  -0.0773   0.7182   0.0141
  -2.000   0.1493   0.00744   0.00123  -0.0772   0.6991   0.0265
  -1.750   0.1765   0.00732   0.00112  -0.0770   0.6802   0.0521
  -1.500   0.2036   0.00720   0.00105  -0.0769   0.6615   0.0867
  -1.250   0.2309   0.00707   0.00099  -0.0768   0.6430   0.1298
  -1.000   0.2581   0.00693   0.00094  -0.0768   0.6245   0.1843
  -0.750   0.2853   0.00684   0.00092  -0.0767   0.6058   0.2344
  -0.250   0.3393   0.00651   0.00092  -0.0766   0.5686   0.3957
   0.000   0.3663   0.00641   0.00093  -0.0765   0.5494   0.4681
   0.250   0.3933   0.00635   0.00096  -0.0764   0.5304   0.5280
   0.750   0.4470   0.00624   0.00106  -0.0761   0.4936   0.6587
   1.000   0.4736   0.00622   0.00112  -0.0758   0.4748   0.7157
   1.250   0.4999   0.00623   0.00119  -0.0754   0.4565   0.7663
   1.500   0.5257   0.00624   0.00127  -0.0749   0.4391   0.8154
   1.750   0.5505   0.00626   0.00135  -0.0742   0.4208   0.8648
   2.000   0.5737   0.00626   0.00143  -0.0730   0.4034   0.9176
   2.250   0.6066   0.00633   0.00148  -0.0740   0.3843   0.9819
   2.500   0.6362   0.00651   0.00156  -0.0744   0.3654   1.0000
   3.000   0.6899   0.00687   0.00176  -0.0741   0.3308   1.0000
   3.250   0.7167   0.00706   0.00187  -0.0739   0.3140   1.0000
   3.500   0.7434   0.00726   0.00199  -0.0737   0.2963   1.0000
   3.750   0.7700   0.00746   0.00212  -0.0735   0.2796   1.0000
   4.000   0.7965   0.00769   0.00227  -0.0733   0.2622   1.0000
   4.250   0.8229   0.00791   0.00242  -0.0731   0.2466   1.0000
   4.500   0.8492   0.00815   0.00259  -0.0729   0.2303   1.0000
   4.750   0.8756   0.00837   0.00276  -0.0727   0.2171   1.0000
   5.250   0.9276   0.00889   0.00314  -0.0722   0.1861   1.0000
   5.500   0.9524   0.00928   0.00339  -0.0718   0.1606   1.0000
   5.750   0.9776   0.00961   0.00364  -0.0714   0.1419   1.0000
   6.000   1.0032   0.00990   0.00388  -0.0711   0.1301   1.0000
   6.250   1.0284   0.01021   0.00413  -0.0708   0.1167   1.0000
   6.500   1.0528   0.01061   0.00444  -0.0703   0.0989   1.0000
   6.750   1.0769   0.01103   0.00477  -0.0698   0.0827   1.0000
   7.000   1.1015   0.01139   0.00509  -0.0694   0.0716   1.0000
   7.250   1.1257   0.01178   0.00542  -0.0689   0.0607   1.0000
   7.500   1.1491   0.01225   0.00582  -0.0683   0.0479   1.0000
   7.750   1.1724   0.01272   0.00623  -0.0677   0.0374   1.0000
   8.000   1.1952   0.01322   0.00668  -0.0670   0.0277   1.0000
   8.250   1.2168   0.01383   0.00722  -0.0662   0.0164   1.0000
   8.500   1.2377   0.01450   0.00784  -0.0652   0.0087   1.0000
   8.750   1.2604   0.01494   0.00831  -0.0645   0.0074   1.0000
   9.000   1.2829   0.01540   0.00880  -0.0638   0.0068   1.0000
   9.250   1.3046   0.01591   0.00935  -0.0629   0.0062   1.0000
   9.500   1.3262   0.01640   0.00989  -0.0621   0.0059   1.0000
   9.750   1.3476   0.01689   0.01043  -0.0612   0.0057   1.0000
  10.000   1.3682   0.01741   0.01100  -0.0602   0.0055   1.0000
  10.250   1.3883   0.01795   0.01160  -0.0592   0.0053   1.0000
  10.500   1.4074   0.01854   0.01225  -0.0580   0.0051   1.0000
  10.750   1.4257   0.01915   0.01292  -0.0568   0.0050   1.0000
  11.000   1.4428   0.01981   0.01365  -0.0553   0.0048   1.0000
  11.250   1.4581   0.02050   0.01440  -0.0536   0.0046   1.0000
  11.500   1.4701   0.02123   0.01520  -0.0513   0.0045   1.0000
  11.750   1.4804   0.02204   0.01608  -0.0489   0.0044   1.0000
  12.000   1.4881   0.02302   0.01715  -0.0462   0.0042   1.0000
  12.250   1.4920   0.02429   0.01852  -0.0433   0.0040   1.0000
  12.500   1.5019   0.02521   0.01952  -0.0413   0.0040   1.0000
  12.750   1.5100   0.02627   0.02067  -0.0393   0.0039   1.0000
  13.000   1.5163   0.02752   0.02200  -0.0372   0.0039   1.0000
  13.250   1.5229   0.02880   0.02338  -0.0354   0.0039   1.0000
  13.500   1.5276   0.03030   0.02497  -0.0336   0.0038   1.0000
  13.750   1.5305   0.03202   0.02680  -0.0319   0.0038   1.0000
  14.000   1.5343   0.03377   0.02864  -0.0306   0.0037   1.0000
  14.250   1.5342   0.03598   0.03097  -0.0294   0.0037   1.0000
  14.500   1.5336   0.03841   0.03351  -0.0285   0.0036   1.0000
  14.750   1.5322   0.04108   0.03629  -0.0280   0.0036   1.0000
  15.000   1.5303   0.04398   0.03931  -0.0278   0.0035   1.0000
  15.250   1.5253   0.04747   0.04293  -0.0280   0.0035   1.0000
  15.500   1.5189   0.05136   0.04695  -0.0287   0.0035   1.0000
  15.750   1.5110   0.05570   0.05142  -0.0298   0.0034   1.0000
  16.000   1.5005   0.06070   0.05656  -0.0315   0.0034   1.0000
  16.250   1.4903   0.06592   0.06190  -0.0335   0.0034   1.0000
  16.500   1.4790   0.07157   0.06769  -0.0360   0.0034   1.0000
  16.750   1.4635   0.07820   0.07446  -0.0390   0.0034   1.0000
  17.000   1.4467   0.08531   0.08171  -0.0425   0.0033   1.0000
  17.250   1.4303   0.09261   0.08915  -0.0462   0.0033   1.0000
  17.500   1.4116   0.10053   0.09721  -0.0503   0.0034   1.0000
  17.750   1.3931   0.10868   0.10549  -0.0546   0.0033   1.0000
  18.000   1.3745   0.11699   0.11394  -0.0591   0.0034   1.0000
<< Back to SD7037-092-88 (sd7037-il)

Polar data table (+)

Polar graphs


<< Back to SD7037-092-88 (sd7037-il)