Abstract
The aerodynamic force and characteristics to the body in fluid are related to have close connection to the flow around the body and are one of most fundamental subjects in fluid dynamics. At First the result of the water channel experiments are report. The surface flow patterns have been studied using the visualization techniques [1,2]. In aerodynamic studies, the separation and vortex shedding or asymmetry are affected by asymmetry of surface roughness. These are reviewed on the base of aerodynamical viewpoint by Ericsson [3,4]. The vorticalstructure over symmetric body is analyzed by advanced CFD techniques [5], Kandil [5], Suzuki [6], with directly solving Navier-Stokes equations. A series of the expression of variables in N. S. equation [7] and topological study has been attempted by Dallman [8] and Suzuki [6] which was extended to an experimental visualization by Kubota et al [9] or Shirayama [10]. The fuselage of an aircraft or orbiters is slender which has the section to be nearly circle. However the flow around them as described above varies complicatedly by angle of incidence, and exerts a great influence to the aerodynamic characteristics. In the existing studies various separation patterns are known for the ranges of incidence, and these patterns are complicatedly combined with others. In this study, the separation of boundary layer and the structure of vortex around three dimensional body at an angle of incidence are clarified experimentally. For this purpose, a parabolic body of revolution in wind tunnel test is fixed to an angle of incidence, the surface pressure distribution at the leeside of the body of revolution is measured. The pressure date is dealt with the same power spectrum as that of Agui and Andreopoulis [13] for the circular cylinder on a flat plate.
