Airfoil: SG6042 Builder: M. Allen Comment: Re = 300,000: clean & plain trip @ x/c = 35% (h = 0.006", 0.012", 0.018", 0.024") Number of Reynolds #'s: 5 Average Reynolds #: 298038 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.15 0.913 0.0103 0.0104 0.0106 0.0103 0.0098 4.65 0.962 0.0106 0.0106 0.0109 0.0106 0.0103 Tabulated from data in file pg02687.dat & reduced using program C06.01 Average Reynolds #: 298582 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.18 0.912 0.0101 0.0099 0.0102 0.0104 0.0097 4.65 0.957 0.0107 0.0106 0.0109 0.0108 0.0104 Tabulated from data in file pg02690.dat & reduced using program C06.01 Average Reynolds #: 297125 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.18 0.904 0.0105 0.0105 0.0109 0.0103 0.0103 Tabulated from data in file pg02718.dat & reduced using program C06.01 Average Reynolds #: 296406 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.12 0.885 0.0114 0.0111 0.0117 0.0113 0.0112 Tabulated from data in file pg02717.dat & reduced using program C06.01 Average Reynolds #: 297588 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 4.17 0.882 0.0121 0.0120 0.0125 0.0120 0.0118 Tabulated from data in file pg02716.dat & reduced using program C06.01 File sg6042t5.drg created using program C06.01 on Mon Feb 02 15:11:43 1998