XFOIL         Version 6.94
  
 Calculated polar for: agora17                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.035 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000  -0.1682   0.04636   0.03526   0.0342  0.4760  0.3050
  -2.750  -0.1413   0.04749   0.03659   0.0347  0.4334  0.3242
  -2.500  -0.0839   0.04682   0.03676   0.0267  0.3712  0.3552
  -2.250  -0.0524   0.04717   0.03722   0.0261  0.3585  0.3843
  -2.000  -0.0249   0.04738   0.03755   0.0266  0.3522  0.4192
  -1.750   0.0041   0.04794   0.03837   0.0262  0.3474  0.4650
  -1.500   0.0351   0.04844   0.03888   0.0256  0.3447  0.4835
  -1.250   0.0741   0.04993   0.04025   0.0222  0.3432  0.4861
  -1.000   0.1148   0.05203   0.04224   0.0178  0.3436  0.4900
  -0.750   0.1629   0.05575   0.04619   0.0093  0.3474  0.4961
  -0.500   0.2118   0.06014   0.05085  -0.0007  0.3549  0.5059
  -0.250   0.2581   0.06485   0.05577  -0.0111  0.3649  0.5198
   0.000   0.2925   0.06739   0.05861  -0.0162  0.3655  0.5393
   0.250   0.3184   0.06750   0.05903  -0.0159  0.3539  0.5767
   0.500   0.3375   0.06588   0.05857  -0.0124  0.3402  1.0008
   0.750   0.3647   0.06631   0.05839  -0.0106  0.3285  1.0008
   1.000   0.4062   0.07350   0.06549  -0.0246  0.3401  1.0008