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SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD7062 (14%) (sd7062-il)
Reynolds number: 100,000
Max Cl/Cd: 47.63 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7062-il-100000.txt
Download as CSV file: xf-sd7062-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7062 (14%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2591   0.10158   0.09693  -0.0384   1.0000   0.1255
  -8.750  -0.3090   0.10178   0.09738  -0.0404   1.0000   0.1277
  -8.500  -0.3489   0.10218   0.09797  -0.0369   1.0000   0.1279
  -8.250  -0.2988   0.09633   0.09207  -0.0331   1.0000   0.1307
  -8.000  -0.3110   0.09579   0.09163  -0.0287   1.0000   0.1321
  -7.750  -0.3284   0.09542   0.09137  -0.0247   1.0000   0.1335
  -7.500  -0.3340   0.09387   0.08989  -0.0243   0.9978   0.1370
  -7.250  -0.3436   0.08773   0.08380  -0.0403   0.9828   0.1447
  -7.000  -0.2961   0.08505   0.08108  -0.0372   0.9807   0.1508
  -6.750  -0.2988   0.07857   0.07462  -0.0523   0.9632   0.1612
  -6.500  -0.2597   0.07624   0.07228  -0.0505   0.9593   0.1672
  -6.250  -0.2500   0.07024   0.06624  -0.0618   0.9454   0.1790
  -6.000  -0.2723   0.04442   0.03870  -0.0853   0.9278   0.0852
  -5.750  -0.2499   0.03836   0.03147  -0.0875   0.9183   0.0758
  -5.500  -0.2141   0.03496   0.02774  -0.0901   0.9112   0.0748
  -5.250  -0.1682   0.03185   0.02413  -0.0938   0.9071   0.0745
  -5.000  -0.1431   0.03032   0.02218  -0.0934   0.8957   0.0757
  -4.750  -0.1000   0.02814   0.01988  -0.0962   0.8907   0.0790
  -4.500  -0.0730   0.02701   0.01864  -0.0959   0.8800   0.0818
  -4.250  -0.0321   0.02548   0.01689  -0.0974   0.8738   0.0857
  -4.000  -0.0050   0.02435   0.01579  -0.0970   0.8636   0.0908
  -3.750   0.0304   0.02320   0.01466  -0.0977   0.8562   0.1019
  -3.500   0.0556   0.02231   0.01389  -0.0969   0.8458   0.1174
  -3.250   0.0859   0.02093   0.01284  -0.0969   0.8380   0.1682
  -3.000   0.1073   0.01990   0.01242  -0.0959   0.8269   0.2762
  -2.750   0.1359   0.01914   0.01219  -0.0955   0.8192   0.4062
  -2.500   0.1566   0.01904   0.01236  -0.0937   0.8075   0.4904
  -2.250   0.1856   0.01873   0.01218  -0.0925   0.8003   0.5607
  -2.000   0.2055   0.01879   0.01235  -0.0904   0.7882   0.6132
  -1.750   0.2331   0.01855   0.01214  -0.0887   0.7811   0.6660
  -1.500   0.2518   0.01862   0.01228  -0.0862   0.7688   0.7099
  -1.250   0.2739   0.01853   0.01221  -0.0837   0.7598   0.7539
  -1.000   0.2936   0.01843   0.01214  -0.0808   0.7497   0.7958
  -0.750   0.3119   0.01840   0.01212  -0.0777   0.7396   0.8400
  -0.500   0.3355   0.01815   0.01184  -0.0751   0.7308   0.8850
  -0.250   0.3727   0.01806   0.01169  -0.0758   0.7197   0.9327
   0.000   0.4413   0.01765   0.01102  -0.0823   0.7111   0.9723
   0.250   0.5035   0.01752   0.01071  -0.0894   0.6978   1.0000
   0.500   0.5127   0.01764   0.01069  -0.0870   0.6876   1.0000
   0.750   0.5329   0.01767   0.01053  -0.0858   0.6778   1.0000
   1.000   0.5539   0.01792   0.01065  -0.0849   0.6663   1.0000
   1.250   0.5831   0.01786   0.01037  -0.0846   0.6581   1.0000
   1.500   0.6055   0.01816   0.01059  -0.0838   0.6456   1.0000
   1.750   0.6314   0.01833   0.01063  -0.0833   0.6352   1.0000
   2.000   0.6593   0.01840   0.01054  -0.0830   0.6254   1.0000
   2.250   0.6834   0.01870   0.01077  -0.0824   0.6137   1.0000
   2.500   0.7127   0.01875   0.01065  -0.0821   0.6048   1.0000
   2.750   0.7371   0.01902   0.01088  -0.0815   0.5929   1.0000
   3.000   0.7627   0.01929   0.01106  -0.0810   0.5822   1.0000
   3.250   0.7916   0.01937   0.01099  -0.0807   0.5727   1.0000
   3.500   0.8151   0.01974   0.01135  -0.0800   0.5608   1.0000
   3.750   0.8424   0.01994   0.01145  -0.0797   0.5510   1.0000
   4.000   0.8685   0.02018   0.01161  -0.0792   0.5402   1.0000
   4.250   0.8928   0.02055   0.01196  -0.0785   0.5291   1.0000
   4.500   0.9227   0.02068   0.01191  -0.0785   0.5202   1.0000
   4.750   0.9446   0.02112   0.01241  -0.0776   0.5082   1.0000
   5.000   0.9703   0.02147   0.01270  -0.0771   0.4981   1.0000
   5.250   0.9972   0.02171   0.01285  -0.0767   0.4881   1.0000
   5.500   1.0198   0.02219   0.01338  -0.0759   0.4770   1.0000
   5.750   1.0484   0.02245   0.01348  -0.0758   0.4681   1.0000
   6.000   1.0701   0.02292   0.01401  -0.0749   0.4568   1.0000
   6.250   1.0945   0.02337   0.01446  -0.0743   0.4469   1.0000
   6.500   1.1210   0.02369   0.01468  -0.0740   0.4373   1.0000
   6.750   1.1418   0.02427   0.01534  -0.0730   0.4266   1.0000
   7.000   1.1707   0.02458   0.01550  -0.0730   0.4180   1.0000
   7.250   1.1894   0.02520   0.01625  -0.0717   0.4072   1.0000
   7.500   1.2138   0.02570   0.01672  -0.0712   0.3980   1.0000
   7.750   1.2370   0.02618   0.01720  -0.0705   0.3884   1.0000
   8.000   1.2575   0.02685   0.01793  -0.0695   0.3789   1.0000
   8.250   1.2843   0.02723   0.01819  -0.0693   0.3701   1.0000
   8.500   1.3007   0.02804   0.01918  -0.0679   0.3605   1.0000
   8.750   1.3308   0.02841   0.01934  -0.0681   0.3523   1.0000
   9.000   1.3427   0.02931   0.02049  -0.0661   0.3426   1.0000
   9.250   1.3700   0.02981   0.02087  -0.0660   0.3346   1.0000
   9.500   1.3830   0.03068   0.02193  -0.0642   0.3255   1.0000
   9.750   1.4081   0.03129   0.02246  -0.0639   0.3176   1.0000
  10.000   1.4209   0.03219   0.02353  -0.0621   0.3091   1.0000
  10.250   1.4449   0.03286   0.02413  -0.0616   0.3013   1.0000
  10.500   1.4557   0.03383   0.02527  -0.0596   0.2932   1.0000
  10.750   1.4805   0.03453   0.02589  -0.0594   0.2857   1.0000
  11.000   1.4867   0.03567   0.02725  -0.0569   0.2781   1.0000
  11.250   1.5153   0.03627   0.02770  -0.0571   0.2707   1.0000
  11.500   1.5140   0.03769   0.02941  -0.0539   0.2638   1.0000
  11.750   1.5485   0.03810   0.02960  -0.0548   0.2563   1.0000
  12.000   1.5385   0.03981   0.03167  -0.0506   0.2504   1.0000
  12.250   1.5533   0.04063   0.03250  -0.0493   0.2438   1.0000
  12.500   1.5635   0.04188   0.03380  -0.0475   0.2378   1.0000
  12.750   1.5543   0.04357   0.03570  -0.0438   0.2325   1.0000
  13.000   1.5948   0.04386   0.03577  -0.0453   0.2250   1.0000
  13.250   1.5693   0.04628   0.03853  -0.0405   0.2213   1.0000
  13.500   1.5607   0.04831   0.04075  -0.0378   0.2165   1.0000
  13.750   1.5978   0.04850   0.04074  -0.0385   0.2095   1.0000
  14.000   1.5678   0.05183   0.04442  -0.0350   0.2063   1.0000
  14.250   1.5509   0.05490   0.04770  -0.0330   0.2023   1.0000
  14.500   1.5981   0.05414   0.04669  -0.0336   0.1950   1.0000
  14.750   1.5594   0.05880   0.05173  -0.0312   0.1927   1.0000
  15.000   1.5212   0.06438   0.05761  -0.0303   0.1901   1.0000
  15.250   1.4892   0.07013   0.06359  -0.0305   0.1871   1.0000
  15.500   1.5483   0.06705   0.06027  -0.0294   0.1799   1.0000
  15.750   1.4832   0.07650   0.07012  -0.0307   0.1790   1.0000
  16.500   1.4649   0.08775   0.08161  -0.0326   0.1670   1.0000
  16.750   0.9443   0.20443   0.19842  -0.1011   0.2046   1.0000
  17.000   0.9582   0.20698   0.20102  -0.1016   0.1989   1.0000
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