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SG6051 (sg6051-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SG6051 (sg6051-il)
Reynolds number: 200,000
Max Cl/Cd: 78.4 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6051-il-200000-n5.txt
Download as CSV file: xf-sg6051-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6051                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4654   0.08422   0.08085  -0.0487   1.0000   0.0119
  -9.750  -0.4829   0.07678   0.07350  -0.0531   1.0000   0.0118
  -9.250  -0.5837   0.03711   0.03260  -0.0822   0.9559   0.0109
  -9.000  -0.5775   0.03190   0.02670  -0.0825   0.9469   0.0112
  -8.750  -0.5619   0.02850   0.02270  -0.0825   0.9401   0.0118
  -8.500  -0.5424   0.02628   0.02008  -0.0822   0.9332   0.0126
  -8.250  -0.5181   0.02550   0.01917  -0.0823   0.9280   0.0134
  -8.000  -0.4955   0.02427   0.01771  -0.0821   0.9213   0.0144
  -7.750  -0.4730   0.02260   0.01569  -0.0816   0.9158   0.0154
  -7.500  -0.4494   0.02133   0.01421  -0.0813   0.9104   0.0166
  -7.250  -0.4245   0.02060   0.01337  -0.0811   0.9046   0.0181
  -7.000  -0.3999   0.01958   0.01210  -0.0807   0.8999   0.0207
  -6.750  -0.3738   0.01913   0.01160  -0.0807   0.8947   0.0234
  -6.500  -0.3475   0.01865   0.01098  -0.0806   0.8893   0.0275
  -6.250  -0.3210   0.01841   0.01064  -0.0805   0.8849   0.0316
  -6.000  -0.2943   0.01804   0.01017  -0.0806   0.8799   0.0359
  -5.750  -0.2671   0.01785   0.00988  -0.0807   0.8749   0.0407
  -5.500  -0.2409   0.01723   0.00913  -0.0805   0.8705   0.0439
  -5.250  -0.2144   0.01671   0.00858  -0.0805   0.8660   0.0472
  -5.000  -0.1873   0.01626   0.00804  -0.0805   0.8608   0.0507
  -4.750  -0.1602   0.01584   0.00748  -0.0804   0.8564   0.0534
  -4.500  -0.1337   0.01529   0.00692  -0.0804   0.8523   0.0575
  -4.250  -0.1060   0.01493   0.00651  -0.0806   0.8470   0.0619
  -4.000  -0.0784   0.01462   0.00608  -0.0806   0.8424   0.0662
  -3.750  -0.0512   0.01423   0.00569  -0.0806   0.8387   0.0737
  -3.500  -0.0230   0.01393   0.00538  -0.0809   0.8334   0.0835
  -3.250   0.0049   0.01362   0.00508  -0.0811   0.8287   0.0991
  -3.000   0.0325   0.01325   0.00480  -0.0813   0.8248   0.1330
  -2.750   0.0600   0.01275   0.00458  -0.0817   0.8201   0.2070
  -2.500   0.0868   0.01214   0.00448  -0.0820   0.8151   0.3438
  -2.250   0.1145   0.01192   0.00438  -0.0821   0.8109   0.4136
  -2.000   0.1423   0.01173   0.00429  -0.0822   0.8068   0.4578
  -1.750   0.1700   0.01153   0.00423  -0.0824   0.8014   0.5036
  -1.500   0.1969   0.01125   0.00418  -0.0822   0.7970   0.5693
  -1.250   0.2215   0.01084   0.00418  -0.0814   0.7932   0.6766
  -0.750   0.2690   0.01030   0.00426  -0.0781   0.7828   0.9194
  -0.500   0.3063   0.01026   0.00414  -0.0800   0.7791   0.9595
  -0.250   0.3444   0.01029   0.00411  -0.0824   0.7734   0.9893
   0.000   0.3775   0.01028   0.00403  -0.0837   0.7682   1.0000
   0.250   0.4043   0.01031   0.00395  -0.0836   0.7637   1.0000
   0.500   0.4313   0.01037   0.00398  -0.0836   0.7573   1.0000
   0.750   0.4586   0.01041   0.00395  -0.0836   0.7522   1.0000
   1.000   0.4861   0.01047   0.00396  -0.0836   0.7470   1.0000
   1.250   0.5136   0.01054   0.00401  -0.0837   0.7409   1.0000
   1.500   0.5414   0.01059   0.00400  -0.0838   0.7359   1.0000
   1.750   0.5690   0.01068   0.00408  -0.0839   0.7294   1.0000
   2.000   0.5968   0.01074   0.00412  -0.0840   0.7231   1.0000
   2.250   0.6245   0.01082   0.00419  -0.0840   0.7163   1.0000
   2.500   0.6522   0.01089   0.00425  -0.0841   0.7088   1.0000
   2.750   0.6799   0.01097   0.00433  -0.0842   0.7013   1.0000
   3.000   0.7076   0.01104   0.00440  -0.0842   0.6930   1.0000
   3.250   0.7351   0.01113   0.00451  -0.0842   0.6834   1.0000
   3.500   0.7626   0.01121   0.00458  -0.0842   0.6741   1.0000
   3.750   0.7900   0.01130   0.00469  -0.0841   0.6633   1.0000
   4.000   0.8171   0.01140   0.00481  -0.0841   0.6512   1.0000
   4.250   0.8441   0.01151   0.00493  -0.0840   0.6383   1.0000
   4.500   0.8709   0.01163   0.00508  -0.0838   0.6240   1.0000
   4.750   0.8973   0.01177   0.00521  -0.0836   0.6073   1.0000
   5.000   0.9232   0.01194   0.00536  -0.0833   0.5884   1.0000
   5.250   0.9487   0.01214   0.00555  -0.0829   0.5650   1.0000
   5.500   0.9730   0.01241   0.00576  -0.0823   0.5355   1.0000
   5.750   0.9960   0.01278   0.00601  -0.0815   0.4999   1.0000
   6.000   1.0173   0.01327   0.00633  -0.0804   0.4567   1.0000
   6.250   1.0357   0.01396   0.00679  -0.0790   0.4030   1.0000
   6.500   1.0508   0.01489   0.00739  -0.0771   0.3412   1.0000
   6.750   1.0648   0.01588   0.00809  -0.0751   0.2834   1.0000
   7.000   1.0791   0.01685   0.00882  -0.0733   0.2355   1.0000
   7.250   1.0938   0.01777   0.00955  -0.0715   0.1954   1.0000
   7.500   1.1084   0.01867   0.01032  -0.0697   0.1623   1.0000
   7.750   1.1220   0.01958   0.01110  -0.0677   0.1329   1.0000
   8.000   1.1346   0.02051   0.01192  -0.0656   0.1085   1.0000
   8.250   1.1461   0.02140   0.01275  -0.0633   0.0899   1.0000
   8.500   1.1567   0.02231   0.01364  -0.0609   0.0761   1.0000
   8.750   1.1677   0.02328   0.01462  -0.0586   0.0652   1.0000
   9.000   1.1787   0.02431   0.01565  -0.0565   0.0568   1.0000
   9.250   1.1890   0.02543   0.01678  -0.0545   0.0499   1.0000
   9.500   1.2011   0.02647   0.01789  -0.0527   0.0445   1.0000
   9.750   1.2109   0.02771   0.01913  -0.0509   0.0397   1.0000
  10.000   1.2226   0.02883   0.02035  -0.0492   0.0360   1.0000
  10.250   1.2332   0.03006   0.02166  -0.0476   0.0327   1.0000
  10.500   1.2412   0.03154   0.02319  -0.0459   0.0300   1.0000
  10.750   1.2516   0.03285   0.02463  -0.0444   0.0277   1.0000
  11.000   1.2605   0.03432   0.02619  -0.0428   0.0258   1.0000
  11.250   1.2660   0.03610   0.02802  -0.0412   0.0240   1.0000
  11.500   1.2727   0.03783   0.02987  -0.0396   0.0225   1.0000
  11.750   1.2804   0.03950   0.03167  -0.0382   0.0209   1.0000
  12.000   1.2874   0.04125   0.03352  -0.0370   0.0195   1.0000
  12.250   1.2913   0.04332   0.03567  -0.0357   0.0184   1.0000
  12.500   1.2943   0.04555   0.03801  -0.0343   0.0176   1.0000
  12.750   1.2988   0.04769   0.04031  -0.0331   0.0168   1.0000
  13.000   1.3025   0.04994   0.04271  -0.0319   0.0160   1.0000
  13.250   1.3055   0.05229   0.04519  -0.0309   0.0154   1.0000
  13.500   1.3079   0.05474   0.04777  -0.0300   0.0148   1.0000
  13.750   1.3094   0.05733   0.05047  -0.0293   0.0144   1.0000
  14.000   1.3092   0.06018   0.05341  -0.0287   0.0139   1.0000
  14.250   1.3081   0.06324   0.05660  -0.0281   0.0135   1.0000
  14.500   1.3084   0.06627   0.05984  -0.0277   0.0130   1.0000
  14.750   1.3076   0.06952   0.06331  -0.0275   0.0126   1.0000
  15.000   1.3054   0.07300   0.06697  -0.0275   0.0121   1.0000
  15.250   1.3022   0.07673   0.07087  -0.0278   0.0118   1.0000
  15.500   1.2977   0.08074   0.07506  -0.0283   0.0115   1.0000
  15.750   1.2923   0.08502   0.07951  -0.0291   0.0113   1.0000
  16.000   1.2859   0.08957   0.08423  -0.0302   0.0111   1.0000
  16.250   1.2786   0.09439   0.08920  -0.0316   0.0110   1.0000
  16.500   1.2705   0.09950   0.09447  -0.0334   0.0108   1.0000
  16.750   1.2615   0.10494   0.10007  -0.0355   0.0107   1.0000
  17.000   1.2516   0.11074   0.10603  -0.0380   0.0106   1.0000
  17.250   1.2406   0.11690   0.11235  -0.0409   0.0105   1.0000
  17.500   1.2287   0.12348   0.11910  -0.0442   0.0104   1.0000
  17.750   1.2156   0.13061   0.12640  -0.0481   0.0104   1.0000
  18.000   1.2014   0.13834   0.13431  -0.0526   0.0104   1.0000
  18.250   1.1851   0.14708   0.14324  -0.0580   0.0104   1.0000
  18.500   1.1649   0.15738   0.15376  -0.0646   0.0104   1.0000
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