flow5 v7.57

 Calculated polar for: AG35ish

 1 1 Reynolds number fixed          Mach number fixed         

 xtrf =   0.000 (top)        0.000 (bottom)
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000

  alpha     CL        CD       CDp       Cm    Top Xtr Bot Xtr   Cpmin    Chinge    XCp    
 ------- -------- --------- --------- -------- ------- ------- -------- --------- ---------
  -6.000  -0.5041   0.03342   0.02662  -0.0385  1.0000  -0.0000  -3.0339   0.0000   0.1692
  -5.500  -0.4714   0.02687   0.01900  -0.0359  1.0000  -0.0000  -3.0241   0.0000   0.1695
  -5.000  -0.4282   0.02202   0.01324  -0.0334  1.0000  -0.0000  -2.9120   0.0000   0.1675
  -4.500  -0.3821   0.01872   0.00930  -0.0310  1.0000  -0.0000  -2.7212   0.0000   0.1643
  -4.000  -0.3364   0.01745   0.00762  -0.0293  1.0000  -0.0000  -2.4426   0.0000   0.1587
  -3.500  -0.2899   0.01693   0.00678  -0.0279  1.0000  -0.0000  -2.1335   0.0000   0.1494
  -3.000  -0.2434   0.01669   0.00632  -0.0268  1.0000  -0.0000  -1.8210   0.0000   0.1359
  -2.500  -0.1975   0.01660   0.00604  -0.0257  1.0000  -0.0000  -1.5244   0.0000   0.1159
  -2.000  -0.1526   0.01666   0.00598  -0.0246  1.0000  -0.0000  -1.2797   0.0000   0.0844
  -1.500  -0.1088   0.01687   0.00611  -0.0236  1.0000  -0.0000  -1.0490   0.0000   0.0282
  -1.000  -0.0615   0.01728   0.00645  -0.0237  0.9985  -0.0000  -0.8465   0.0000  -0.1416
  -0.500   0.0349   0.01789   0.00704  -0.0330  0.9787  -0.0000  -0.5865   0.0000   1.2021
   1.000   0.3307   0.01535   0.00338  -0.0487  -0.0000  1.0000  -0.5447   0.0000   0.3955
   1.500   0.3796   0.01561   0.00354  -0.0474  -0.0000  1.0000  -0.6006   0.0000   0.3728
   2.000   0.4288   0.01591   0.00381  -0.0462  -0.0000  1.0000  -0.6892   0.0000   0.3553
   2.500   0.4783   0.01627   0.00412  -0.0450  -0.0000  1.0000  -0.8157   0.0000   0.3413
   3.000   0.5278   0.01667   0.00453  -0.0439  -0.0000  1.0000  -0.9870   0.0000   0.3299
   3.500   0.5772   0.01711   0.00505  -0.0427  -0.0000  1.0000  -1.1952   0.0000   0.3205
   4.000   0.6264   0.01762   0.00563  -0.0415  -0.0000  1.0000  -1.4348   0.0000   0.3124
   4.500   0.6754   0.01818   0.00630  -0.0404  -0.0000  1.0000  -1.7136   0.0000   0.3055
   5.000   0.7239   0.01879   0.00713  -0.0391  -0.0000  1.0000  -2.0109   0.0000   0.2994
   5.500   0.7719   0.01949   0.00803  -0.0378  -0.0000  1.0000  -2.3601   0.0000   0.2939
   6.000   0.8189   0.02030   0.00912  -0.0364  -0.0000  1.0000  -2.7196   0.0000   0.2889
   6.500   0.8648   0.02124   0.01035  -0.0349  -0.0000  1.0000  -3.0859   0.0000   0.2842
   7.000   0.9087   0.02241   0.01187  -0.0330  -0.0000  1.0000  -3.4679   0.0000   0.2797
   7.500   0.9485   0.02397   0.01344  -0.0311  -0.0000  1.0000  -3.9152   0.0000   0.2756
   8.000   0.9877   0.02556   0.01519  -0.0290  -0.0000  1.0000  -4.3689   0.0000   0.2716
   8.500   1.0252   0.02728   0.01718  -0.0267  -0.0000  1.0000  -4.8197   0.0000   0.2677
   9.000   1.0599   0.02922   0.01948  -0.0242  -0.0000  1.0000  -5.2645   0.0000   0.2639
   9.500   1.0909   0.03150   0.02213  -0.0214  -0.0000  1.0000  -5.6832   0.0000   0.2600
  10.000   1.1168   0.03423   0.02529  -0.0181  -0.0000  1.0000  -6.0594   0.0000   0.2560
  10.500   1.1351   0.03753   0.02909  -0.0141  -0.0000  1.0000  -6.3709   0.0000   0.2516
  11.000   1.1445   0.04189   0.03399  -0.0099  -0.0000  1.0000  -6.5762   0.0000   0.2472
  11.500   1.1405   0.04803   0.04081  -0.0059  -0.0000  1.0000  -6.6170   0.0000   0.2430
  12.000   1.1123   0.05731   0.05088  -0.0035  -0.0000  1.0000  -6.4312   0.0000   0.2404


