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AG35 (ag35-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AG35 (ag35-il)
Reynolds number: 200,000
Max Cl/Cd: 65.34 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag35-il-200000-n5.txt
Download as CSV file: xf-ag35-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG35                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5159   0.11195   0.10834   0.0022   1.0000   0.0180
 -11.000  -0.5248   0.09848   0.09495  -0.0054   1.0000   0.0154
 -10.500  -0.5235   0.08983   0.08637  -0.0100   1.0000   0.0158
 -10.250  -0.5150   0.08815   0.08470  -0.0106   1.0000   0.0166
 -10.000  -0.5133   0.08416   0.08074  -0.0132   1.0000   0.0170
  -9.750  -0.5141   0.07958   0.07620  -0.0166   1.0000   0.0173
  -9.500  -0.5151   0.07375   0.07041  -0.0226   1.0000   0.0173
  -9.250  -0.5133   0.06611   0.06274  -0.0307   1.0000   0.0171
  -9.000  -0.5318   0.04434   0.04037  -0.0449   1.0000   0.0157
  -8.750  -0.5267   0.03761   0.03312  -0.0463   1.0000   0.0157
  -8.500  -0.5148   0.03342   0.02852  -0.0463   1.0000   0.0159
  -8.250  -0.4994   0.03041   0.02515  -0.0457   1.0000   0.0163
  -8.000  -0.4825   0.02788   0.02228  -0.0448   1.0000   0.0167
  -7.750  -0.4644   0.02568   0.01974  -0.0438   1.0000   0.0172
  -7.500  -0.4452   0.02393   0.01768  -0.0427   1.0000   0.0180
  -7.250  -0.4254   0.02239   0.01580  -0.0414   1.0000   0.0193
  -7.000  -0.3938   0.02055   0.01351  -0.0424   0.9960   0.0203
  -6.750  -0.3606   0.01869   0.01137  -0.0437   0.9910   0.0211
  -6.500  -0.3269   0.01745   0.01002  -0.0451   0.9858   0.0222
  -6.250  -0.2930   0.01649   0.00895  -0.0464   0.9799   0.0236
  -6.000  -0.2592   0.01575   0.00809  -0.0476   0.9727   0.0260
  -5.750  -0.2266   0.01486   0.00711  -0.0486   0.9653   0.0282
  -5.500  -0.1938   0.01411   0.00631  -0.0496   0.9577   0.0307
  -5.250  -0.1620   0.01354   0.00568  -0.0503   0.9482   0.0341
  -5.000  -0.1298   0.01297   0.00508  -0.0512   0.9393   0.0396
  -4.750  -0.0992   0.01255   0.00457  -0.0516   0.9289   0.0459
  -4.500  -0.0696   0.01211   0.00414  -0.0517   0.9168   0.0580
  -4.250  -0.0409   0.01167   0.00377  -0.0518   0.9044   0.0793
  -4.000  -0.0130   0.01123   0.00349  -0.0517   0.8917   0.1234
  -3.750   0.0140   0.01078   0.00326  -0.0515   0.8785   0.1918
  -3.250   0.0662   0.00995   0.00296  -0.0507   0.8494   0.3631
  -3.000   0.0910   0.00945   0.00283  -0.0500   0.8331   0.4794
  -2.750   0.1131   0.00883   0.00277  -0.0485   0.8163   0.6422
  -2.500   0.1324   0.00832   0.00276  -0.0456   0.7998   0.8176
  -2.250   0.1721   0.00817   0.00266  -0.0470   0.7823   0.9553
  -2.000   0.2137   0.00818   0.00251  -0.0497   0.7625   1.0000
  -1.750   0.2394   0.00826   0.00242  -0.0491   0.7414   1.0000
  -1.500   0.2652   0.00835   0.00234  -0.0485   0.7190   1.0000
  -1.250   0.2912   0.00845   0.00228  -0.0480   0.6934   1.0000
  -1.000   0.3172   0.00855   0.00223  -0.0475   0.6610   1.0000
  -0.750   0.3427   0.00871   0.00216  -0.0469   0.6290   1.0000
  -0.500   0.3684   0.00891   0.00214  -0.0463   0.6068   1.0000
  -0.250   0.3946   0.00911   0.00218  -0.0459   0.5877   1.0000
   0.000   0.4210   0.00931   0.00224  -0.0456   0.5711   1.0000
   0.250   0.4476   0.00950   0.00233  -0.0454   0.5567   1.0000
   0.500   0.4744   0.00968   0.00243  -0.0452   0.5436   1.0000
   0.750   0.5012   0.00987   0.00254  -0.0450   0.5313   1.0000
   1.000   0.5281   0.01005   0.00266  -0.0448   0.5188   1.0000
   1.250   0.5551   0.01021   0.00280  -0.0447   0.5060   1.0000
   1.500   0.5821   0.01038   0.00294  -0.0446   0.4931   1.0000
   1.750   0.6091   0.01055   0.00309  -0.0444   0.4795   1.0000
   2.000   0.6360   0.01071   0.00325  -0.0443   0.4648   1.0000
   2.250   0.6629   0.01088   0.00342  -0.0442   0.4485   1.0000
   2.500   0.6894   0.01108   0.00358  -0.0440   0.4305   1.0000
   2.750   0.7159   0.01128   0.00376  -0.0439   0.4097   1.0000
   3.000   0.7420   0.01154   0.00397  -0.0437   0.3865   1.0000
   3.250   0.7678   0.01183   0.00420  -0.0434   0.3607   1.0000
   3.500   0.7934   0.01216   0.00446  -0.0432   0.3342   1.0000
   3.750   0.8187   0.01253   0.00475  -0.0430   0.3074   1.0000
   4.000   0.8438   0.01294   0.00510  -0.0427   0.2812   1.0000
   4.250   0.8687   0.01338   0.00547  -0.0425   0.2567   1.0000
   4.500   0.8934   0.01384   0.00588  -0.0423   0.2334   1.0000
   4.750   0.9181   0.01431   0.00631  -0.0420   0.2123   1.0000
   5.000   0.9425   0.01482   0.00679  -0.0417   0.1915   1.0000
   5.250   0.9667   0.01534   0.00728  -0.0415   0.1721   1.0000
   5.500   0.9906   0.01587   0.00779  -0.0412   0.1521   1.0000
   5.750   1.0140   0.01648   0.00835  -0.0408   0.1324   1.0000
   6.000   1.0372   0.01710   0.00896  -0.0405   0.1125   1.0000
   6.250   1.0595   0.01782   0.00961  -0.0400   0.0940   1.0000
   6.500   1.0818   0.01853   0.01031  -0.0396   0.0775   1.0000
   6.750   1.1034   0.01931   0.01107  -0.0391   0.0629   1.0000
   7.000   1.1243   0.02015   0.01190  -0.0385   0.0503   1.0000
   7.250   1.1445   0.02105   0.01284  -0.0378   0.0403   1.0000
   7.500   1.1639   0.02202   0.01384  -0.0370   0.0325   1.0000
   7.750   1.1818   0.02312   0.01498  -0.0361   0.0273   1.0000
   8.000   1.1998   0.02415   0.01614  -0.0351   0.0237   1.0000
   8.250   1.2148   0.02546   0.01751  -0.0339   0.0209   1.0000
   8.500   1.2311   0.02654   0.01874  -0.0327   0.0187   1.0000
   8.750   1.2452   0.02776   0.02010  -0.0315   0.0171   1.0000
   9.000   1.2544   0.02935   0.02180  -0.0298   0.0160   1.0000
   9.250   1.2632   0.03087   0.02348  -0.0279   0.0152   1.0000
   9.500   1.2688   0.03238   0.02515  -0.0257   0.0146   1.0000
   9.750   1.2730   0.03408   0.02700  -0.0236   0.0140   1.0000
  10.000   1.2765   0.03591   0.02898  -0.0220   0.0134   1.0000
  10.250   1.2794   0.03788   0.03109  -0.0207   0.0128   1.0000
  10.500   1.2809   0.04011   0.03345  -0.0197   0.0123   1.0000
  10.750   1.2798   0.04276   0.03621  -0.0192   0.0119   1.0000
  11.000   1.2748   0.04604   0.03963  -0.0189   0.0115   1.0000
  11.250   1.2745   0.04902   0.04283  -0.0190   0.0112   1.0000
  11.500   1.2718   0.05245   0.04646  -0.0195   0.0110   1.0000
  11.750   1.2672   0.05630   0.05050  -0.0204   0.0107   1.0000
  12.000   1.2612   0.06054   0.05494  -0.0216   0.0106   1.0000
  12.250   1.2540   0.06515   0.05974  -0.0232   0.0104   1.0000
  12.500   1.2450   0.07012   0.06489  -0.0251   0.0103   1.0000
  12.750   1.2346   0.07546   0.07041  -0.0273   0.0102   1.0000
  13.000   1.2226   0.08118   0.07631  -0.0298   0.0101   1.0000
  13.250   1.2092   0.08732   0.08263  -0.0326   0.0100   1.0000
  13.500   1.1949   0.09393   0.08941  -0.0358   0.0100   1.0000
  13.750   1.1795   0.10101   0.09666  -0.0394   0.0100   1.0000
  14.000   1.1631   0.10864   0.10446  -0.0433   0.0100   1.0000
  14.250   1.1458   0.11682   0.11281  -0.0476   0.0100   1.0000
  14.500   1.1276   0.12559   0.12174  -0.0523   0.0101   1.0000
  14.750   1.1078   0.13521   0.13151  -0.0576   0.0102   1.0000
  15.000   1.0852   0.14612   0.14257  -0.0635   0.0103   1.0000
  15.250   1.0565   0.15959   0.15615  -0.0708   0.0106   1.0000
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