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SA7035 (sa7035-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 100,000
Max Cl/Cd: 52.78 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7035-il-100000.txt
Download as CSV file: xf-sa7035-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3972   0.09599   0.09120  -0.0262   1.0000   0.0946
  -8.250  -0.4030   0.09326   0.08856  -0.0290   1.0000   0.0975
  -8.000  -0.4246   0.09107   0.08652  -0.0336   1.0000   0.0988
  -7.750  -0.4116   0.08646   0.08195  -0.0311   1.0000   0.1016
  -7.500  -0.4027   0.08365   0.07917  -0.0294   1.0000   0.1055
  -7.250  -0.4105   0.08115   0.07676  -0.0296   1.0000   0.1087
  -7.000  -0.4404   0.07777   0.07341  -0.0394   1.0000   0.1128
  -6.750  -0.4335   0.07383   0.06959  -0.0360   1.0000   0.1150
  -6.500  -0.3987   0.06171   0.05787  -0.0326   1.0000   0.1265
  -6.250  -0.4485   0.06861   0.06414  -0.0399   1.0000   0.1273
  -6.000  -0.4356   0.06476   0.06056  -0.0345   1.0000   0.1298
  -5.750  -0.4356   0.06228   0.05793  -0.0358   1.0000   0.1403
  -5.500  -0.4309   0.05875   0.05449  -0.0337   1.0000   0.1441
  -5.000  -0.4177   0.05317   0.04883  -0.0319   1.0000   0.1612
  -4.750  -0.4092   0.05026   0.04584  -0.0318   1.0000   0.1740
  -4.500  -0.3677   0.03579   0.02957  -0.0393   1.0000   0.0688
  -4.250  -0.3437   0.03131   0.02426  -0.0386   1.0000   0.0567
  -4.000  -0.3215   0.02825   0.02079  -0.0381   1.0000   0.0538
  -3.750  -0.2971   0.02573   0.01776  -0.0373   1.0000   0.0518
  -3.500  -0.2727   0.02393   0.01559  -0.0366   1.0000   0.0525
  -3.250  -0.2491   0.02274   0.01410  -0.0357   1.0000   0.0566
  -3.000  -0.2254   0.02162   0.01272  -0.0348   1.0000   0.0591
  -2.750  -0.2024   0.02000   0.01118  -0.0341   1.0000   0.0643
  -2.500  -0.1799   0.01899   0.01014  -0.0332   1.0000   0.0749
  -2.250  -0.1570   0.01786   0.00920  -0.0326   1.0000   0.1127
  -2.000  -0.1273   0.01503   0.00886  -0.0336   0.9965   0.5655
  -1.750  -0.0977   0.01449   0.00926  -0.0316   0.9882   0.8807
  -1.500  -0.0334   0.01466   0.00899  -0.0392   0.9793   1.0000
  -1.250   0.0180   0.01507   0.00902  -0.0444   0.9702   1.0000
  -1.000   0.0628   0.01532   0.00899  -0.0482   0.9587   1.0000
  -0.750   0.1066   0.01554   0.00896  -0.0516   0.9471   1.0000
  -0.500   0.1510   0.01572   0.00895  -0.0551   0.9357   1.0000
  -0.250   0.1978   0.01583   0.00890  -0.0588   0.9251   1.0000
   0.000   0.2482   0.01583   0.00875  -0.0631   0.9154   1.0000
   0.250   0.2909   0.01579   0.00862  -0.0659   0.9031   1.0000
   0.500   0.3315   0.01571   0.00846  -0.0680   0.8906   1.0000
   0.750   0.3703   0.01558   0.00827  -0.0696   0.8779   1.0000
   1.000   0.4069   0.01542   0.00806  -0.0707   0.8648   1.0000
   1.250   0.4412   0.01523   0.00785  -0.0712   0.8511   1.0000
   1.500   0.4731   0.01504   0.00762  -0.0712   0.8365   1.0000
   1.750   0.5035   0.01484   0.00739  -0.0708   0.8211   1.0000
   2.000   0.5326   0.01465   0.00717  -0.0701   0.8051   1.0000
   2.250   0.5612   0.01448   0.00698  -0.0693   0.7888   1.0000
   2.500   0.5870   0.01443   0.00690  -0.0682   0.7697   1.0000
   2.750   0.6131   0.01440   0.00682  -0.0671   0.7502   1.0000
   3.000   0.6403   0.01435   0.00670  -0.0661   0.7314   1.0000
   3.250   0.6648   0.01445   0.00681  -0.0649   0.7087   1.0000
   3.500   0.6908   0.01452   0.00681  -0.0638   0.6874   1.0000
   3.750   0.7154   0.01468   0.00692  -0.0627   0.6637   1.0000
   4.000   0.7401   0.01488   0.00707  -0.0617   0.6397   1.0000
   4.250   0.7651   0.01509   0.00724  -0.0606   0.6163   1.0000
   4.500   0.7895   0.01536   0.00745  -0.0596   0.5916   1.0000
   4.750   0.8134   0.01567   0.00773  -0.0586   0.5662   1.0000
   5.000   0.8373   0.01600   0.00802  -0.0575   0.5407   1.0000
   5.250   0.8611   0.01637   0.00835  -0.0565   0.5151   1.0000
   5.500   0.8846   0.01676   0.00868  -0.0555   0.4893   1.0000
   5.750   0.9076   0.01720   0.00907  -0.0544   0.4629   1.0000
   6.000   0.9301   0.01767   0.00952  -0.0534   0.4360   1.0000
   6.250   0.9523   0.01818   0.01004  -0.0523   0.4092   1.0000
   6.500   0.9742   0.01874   0.01058  -0.0512   0.3824   1.0000
   6.750   0.9955   0.01933   0.01116  -0.0500   0.3555   1.0000
   7.000   1.0162   0.01996   0.01175  -0.0488   0.3283   1.0000
   7.250   1.0361   0.02063   0.01240  -0.0475   0.3011   1.0000
   7.500   1.0554   0.02137   0.01314  -0.0462   0.2741   1.0000
   7.750   1.0737   0.02217   0.01391  -0.0449   0.2473   1.0000
   8.000   1.0913   0.02308   0.01477  -0.0434   0.2210   1.0000
   8.250   1.1078   0.02411   0.01573  -0.0419   0.1950   1.0000
   8.500   1.1230   0.02527   0.01683  -0.0402   0.1693   1.0000
   8.750   1.1369   0.02656   0.01813  -0.0384   0.1444   1.0000
   9.000   1.1504   0.02812   0.01968  -0.0365   0.1228   1.0000
   9.250   1.1631   0.02967   0.02117  -0.0347   0.1046   1.0000
   9.500   1.1763   0.03163   0.02303  -0.0332   0.0892   1.0000
   9.750   1.1898   0.03369   0.02512  -0.0315   0.0767   1.0000
  10.000   1.2007   0.03537   0.02702  -0.0294   0.0669   1.0000
  10.250   1.2156   0.03819   0.03009  -0.0279   0.0594   1.0000
  10.500   1.2308   0.04118   0.03298  -0.0271   0.0527   1.0000
  10.750   1.2380   0.04374   0.03605  -0.0246   0.0492   1.0000
  11.000   1.2454   0.04676   0.03940  -0.0226   0.0464   1.0000
  11.250   1.2524   0.04952   0.04223  -0.0211   0.0434   1.0000
  11.500   1.2490   0.05391   0.04689  -0.0190   0.0416   1.0000
  11.750   1.2363   0.05652   0.04987  -0.0157   0.0408   1.0000
  12.000   1.2221   0.05982   0.05351  -0.0134   0.0403   1.0000
  12.250   1.2053   0.06360   0.05761  -0.0119   0.0400   1.0000
  12.500   1.1874   0.06792   0.06222  -0.0114   0.0399   1.0000
  12.750   1.1672   0.07284   0.06741  -0.0119   0.0399   1.0000
  13.000   1.1463   0.07835   0.07315  -0.0136   0.0401   1.0000
  13.250   1.1252   0.08446   0.07946  -0.0163   0.0405   1.0000
  13.500   1.1024   0.09144   0.08661  -0.0201   0.0408   1.0000
  13.750   1.0800   0.09913   0.09445  -0.0247   0.0412   1.0000
  14.000   1.0594   0.10733   0.10274  -0.0294   0.0417   1.0000
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