Experimental and computational studies have been made to obtain the flow field over a typical reusable launch vehicle configuration at subsonic speed. This study has the relevance to the landing phase of the vehicle. Experiments consisted of flow visualization and measurement of forces and moments at different angles of attack. Computation have been made using commercial software FLUENT. Oil and tuft flow visualisation indicate the presence of vortices. Experiments made at different angles of attack indicate asymmetry in the flow field at higher angles of attack. Nonlinear behaviour of normal force coefficient is observed with increase in angle of attack above 20 degree. Presence of small side force is observed at large angles of attack. Computations made using FLUENT indicate reasonably good comparison with experimental results and captures most of the features of flow field. The study made has relevance to the aerodynamics of reusable launch vehicle during landing phase, where it attains the subsonic speed.