A series of supersonic wind tunnel tests on an ogive-cylinder body were performed to investigate the pressure distribution, the boundary layer profiles, and the flow visualization at various angles of attack. All tests were conducted in the trisonic wind tunnel of the Imam Hossein University. The theoretical shock angle at different model positions compared well with those we obtained via Schilerian results. The static surface pressure results show that the circumferential pressure at different nose sections vary significantly with angle of attack. However, minor changes in the circumferential pressure signatures along the cylindrical part of the body were observed. The total pressure measurements in the radial direction, perpendicular to the incoming flow, vary significantly both radially and longitudinally (along body length). The boundary layer thickness increases along the body. At the beginnig and at the midle part of the cylinderical portion of the body, the boundary layer thickness increases uniformly with increasing angle of attack. However, this situation differs near the end of the body. Our measurements indicated a turbulent boundary layer along the model, which is probably due to the high turbulence level in the tunnel test section.

Keywords: Supersonic flow field, Pressure distribution, Long axisymmetric body, Three-dimentional boundary layer

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