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SA7035 (sa7035-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 50,000
Max Cl/Cd: 37.82 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7035-il-50000-n5.txt
Download as CSV file: xf-sa7035-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7035                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4146   0.11566   0.10857  -0.0202   1.0000   0.0921
  -9.500  -0.4127   0.11212   0.10509  -0.0219   1.0000   0.0904
  -9.250  -0.4166   0.10426   0.09722  -0.0280   1.0000   0.0455
  -9.000  -0.4098   0.10057   0.09357  -0.0278   1.0000   0.0439
  -8.750  -0.4068   0.09701   0.09007  -0.0288   1.0000   0.0426
  -8.500  -0.4058   0.09328   0.08641  -0.0301   1.0000   0.0413
  -8.250  -0.4066   0.08948   0.08270  -0.0317   1.0000   0.0401
  -8.000  -0.4099   0.08556   0.07889  -0.0334   1.0000   0.0390
  -7.750  -0.4164   0.08156   0.07501  -0.0354   1.0000   0.0379
  -7.250  -0.4327   0.06993   0.06336  -0.0447   1.0000   0.0346
  -7.000  -0.4333   0.06643   0.05987  -0.0449   1.0000   0.0343
  -6.750  -0.4342   0.06270   0.05609  -0.0451   1.0000   0.0340
  -6.500  -0.4336   0.05898   0.05227  -0.0451   1.0000   0.0338
  -6.250  -0.4310   0.05527   0.04839  -0.0451   1.0000   0.0337
  -6.000  -0.4262   0.05146   0.04432  -0.0449   1.0000   0.0339
  -5.750  -0.4183   0.04785   0.04037  -0.0446   1.0000   0.0341
  -5.500  -0.4072   0.04438   0.03642  -0.0441   1.0000   0.0346
  -5.250  -0.3952   0.04112   0.03293  -0.0435   1.0000   0.0358
  -5.000  -0.3803   0.03861   0.03020  -0.0428   1.0000   0.0372
  -4.750  -0.3629   0.03599   0.02721  -0.0420   1.0000   0.0381
  -4.500  -0.3433   0.03345   0.02424  -0.0412   1.0000   0.0388
  -4.250  -0.3224   0.03116   0.02150  -0.0403   1.0000   0.0400
  -4.000  -0.3005   0.02919   0.01914  -0.0392   1.0000   0.0416
  -3.750  -0.2781   0.02757   0.01713  -0.0381   1.0000   0.0452
  -3.500  -0.2572   0.02620   0.01567  -0.0371   1.0000   0.0506
  -3.250  -0.2352   0.02497   0.01420  -0.0359   1.0000   0.0572
  -3.000  -0.2131   0.02385   0.01301  -0.0350   1.0000   0.0689
  -2.750  -0.1903   0.02274   0.01187  -0.0343   1.0000   0.0897
  -2.500  -0.1640   0.02129   0.01082  -0.0348   0.9990   0.1653
  -2.250  -0.1296   0.01952   0.01039  -0.0371   0.9921   0.4193
  -2.000  -0.1031   0.01871   0.01052  -0.0358   0.9837   0.6684
  -1.750  -0.0581   0.01818   0.01033  -0.0368   0.9763   0.9446
  -1.500  -0.0108   0.01832   0.00991  -0.0414   0.9661   1.0000
  -1.250   0.0315   0.01856   0.00971  -0.0447   0.9560   1.0000
  -1.000   0.0707   0.01876   0.00955  -0.0474   0.9445   1.0000
  -0.750   0.1085   0.01894   0.00941  -0.0498   0.9324   1.0000
  -0.500   0.1463   0.01910   0.00932  -0.0520   0.9202   1.0000
  -0.250   0.1843   0.01925   0.00926  -0.0542   0.9081   1.0000
   0.000   0.2229   0.01938   0.00919  -0.0563   0.8961   1.0000
   0.250   0.2603   0.01947   0.00914  -0.0581   0.8840   1.0000
   0.500   0.2960   0.01954   0.00908  -0.0595   0.8713   1.0000
   0.750   0.3299   0.01959   0.00902  -0.0605   0.8578   1.0000
   1.000   0.3616   0.01963   0.00899  -0.0610   0.8433   1.0000
   1.250   0.3919   0.01968   0.00898  -0.0611   0.8279   1.0000
   1.500   0.4215   0.01972   0.00899  -0.0611   0.8122   1.0000
   1.750   0.4510   0.01975   0.00898  -0.0610   0.7961   1.0000
   2.000   0.4806   0.01977   0.00898  -0.0609   0.7798   1.0000
   2.250   0.5102   0.01978   0.00897  -0.0606   0.7632   1.0000
   2.500   0.5398   0.01978   0.00897  -0.0603   0.7466   1.0000
   2.750   0.5668   0.01986   0.00904  -0.0597   0.7278   1.0000
   3.000   0.5940   0.01994   0.00912  -0.0590   0.7086   1.0000
   3.250   0.6222   0.01999   0.00916  -0.0584   0.6900   1.0000
   3.500   0.6477   0.02017   0.00939  -0.0575   0.6689   1.0000
   3.750   0.6744   0.02031   0.00953  -0.0567   0.6485   1.0000
   4.000   0.6996   0.02054   0.00978  -0.0558   0.6267   1.0000
   4.250   0.7256   0.02075   0.01003  -0.0549   0.6054   1.0000
   4.500   0.7498   0.02106   0.01037  -0.0540   0.5822   1.0000
   4.750   0.7747   0.02135   0.01067  -0.0530   0.5597   1.0000
   5.000   0.7985   0.02171   0.01106  -0.0520   0.5359   1.0000
   5.250   0.8219   0.02212   0.01155  -0.0510   0.5117   1.0000
   5.500   0.8455   0.02254   0.01199  -0.0499   0.4883   1.0000
   5.750   0.8684   0.02302   0.01251  -0.0489   0.4644   1.0000
   6.000   0.8906   0.02356   0.01311  -0.0478   0.4399   1.0000
   6.250   0.9126   0.02413   0.01372  -0.0467   0.4157   1.0000
   6.500   0.9343   0.02473   0.01438  -0.0456   0.3920   1.0000
   6.750   0.9547   0.02541   0.01516  -0.0444   0.3669   1.0000
   7.000   0.9748   0.02613   0.01596  -0.0432   0.3425   1.0000
   7.250   0.9943   0.02691   0.01678  -0.0419   0.3187   1.0000
   7.500   1.0130   0.02776   0.01769  -0.0406   0.2952   1.0000
   7.750   1.0307   0.02869   0.01872  -0.0393   0.2712   1.0000
   8.000   1.0471   0.02968   0.01981  -0.0378   0.2478   1.0000
   8.250   1.0624   0.03076   0.02092  -0.0363   0.2250   1.0000
   8.500   1.0761   0.03194   0.02221  -0.0347   0.2017   1.0000
   8.750   1.0885   0.03324   0.02352  -0.0330   0.1808   1.0000
   9.000   1.1000   0.03468   0.02507  -0.0313   0.1605   1.0000
   9.250   1.1091   0.03623   0.02661  -0.0295   0.1429   1.0000
   9.500   1.1184   0.03800   0.02846  -0.0277   0.1268   1.0000
   9.750   1.1255   0.03987   0.03050  -0.0258   0.1122   1.0000
  10.000   1.1298   0.04178   0.03246  -0.0237   0.1007   1.0000
  10.250   1.1348   0.04389   0.03464  -0.0218   0.0909   1.0000
  10.500   1.1382   0.04619   0.03717  -0.0200   0.0816   1.0000
  10.750   1.1409   0.04865   0.03972  -0.0185   0.0745   1.0000
  11.000   1.1429   0.05127   0.04254  -0.0171   0.0682   1.0000
  11.250   1.1431   0.05412   0.04552  -0.0160   0.0631   1.0000
  11.500   1.1409   0.05732   0.04902  -0.0151   0.0584   1.0000
  11.750   1.1408   0.06036   0.05213  -0.0145   0.0551   1.0000
  12.000   1.1376   0.06415   0.05612  -0.0142   0.0524   1.0000
  12.250   1.1279   0.06870   0.06104  -0.0147   0.0505   1.0000
  12.500   1.1156   0.07368   0.06632  -0.0160   0.0487   1.0000
  12.750   1.1025   0.07906   0.07194  -0.0178   0.0475   1.0000
  13.000   1.0876   0.08508   0.07817  -0.0205   0.0466   1.0000
  13.250   1.0685   0.09238   0.08570  -0.0243   0.0467   1.0000
  13.500   1.0424   0.10192   0.09549  -0.0299   0.0482   1.0000
  13.750   1.0140   0.11293   0.10666  -0.0366   0.0500   1.0000
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