Aerodynamics of a half-wing in supersonic flow

Experimental results of the aerodynamic normal forces and moments of the semispan wing models are presented. All tests have been conducted at free stream Mach numbers M[infinity] = 1,5... 2,5, the angles of attack alpha= -4o ... 26° and the angles of sideslip beta= 0°...20°. Mounting effects on the model aerodynamic properties are considered. The test results of the semispan models can be used for a prediction of aerodynamic properties of sideslipping half-wings in a supersonic flow.