Airfoil: SG6042 Builder: M. Allen Comment: Re = 300,000: clean & plain trip (h = 0.006") @ x/c = 5%, 15%, 25%, 35%, 45% Number of Reynolds #'s: 7 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 #: 298744 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.22 0.903 0.0109 0.0108 0.0114 0.0109 0.0105 4.64 0.938 0.0117 0.0116 0.0121 0.0118 0.0115 Tabulated from data in file pg02693.dat & reduced using program C06.01 Average Reynolds #: 298687 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.14 0.898 0.0107 0.0104 0.0111 0.0108 0.0108 4.65 0.945 0.0114 0.0113 0.0116 0.0112 0.0113 Tabulated from data in file pg02692.dat & reduced using program C06.01 Average Reynolds #: 298864 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.13 0.905 0.0103 0.0100 0.0108 0.0102 0.0101 4.67 0.958 0.0109 0.0108 0.0111 0.0109 0.0106 Tabulated from data in file pg02691.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 #: 298660 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.16 0.914 0.0102 0.0100 0.0103 0.0106 0.0098 4.64 0.959 0.0107 0.0107 0.0109 0.0108 0.0104 Tabulated from data in file pg02689.dat & reduced using program C06.01 Average Reynolds #: 298876 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 4.18 0.910 0.0101 0.0101 0.0102 0.0103 0.0097 4.66 0.957 0.0106 0.0105 0.0110 0.0105 0.0103 Tabulated from data in file pg02688.dat & reduced using program C06.01 File sg6042t4.drg created using program C06.01 on Mon Feb 02 15:11:43 1998