Peculiarities of Subsonic Detached Flow Around Blunt Flying Vehicles with Stabilizing Disc Devices

Results of experimental investigations of subsonic incompressible flow around a flying vehicle having the stabilizing disc devices are given. Two principal flow modes are revealed in which one or two detached regions are formed. Basic integral aerodynamical characteristics of the layout are found depending on angle of attack and the vehicle geometry. The results agree with both data obtained by other investigators and calculation results.