Abstract:

This paper reports results from pressure tests on an ogive slender body in low-speed tunnel at 40°angle of attack, which are used to analyze the responses between perturbation of forebody and roughness of afterbody and asymmetric vortex in transcritical Reynolds number flow. The Reynolds number ranges from 1.0×10⁵ to 9.0×10⁵. The analysis of results reveales that in transcritical Reynolds number flow the response between natural perturbation of nose and asymmetric vortex is undeterminate.

Key words: slender , body,  , high , angle , of , attack , aerodynamics,  , transcritical , Reynolds , number,  , determination