Distinctive features of the transonic flow past a cone-cylinder body at large angles of the bend in the body generator at the leading corner edge

Abstract

The results of an experimental investigation of the flow past cone-cylinder bodies with small angles of the bend in the body generator at the leading corner edge (θ s ≤ 20 • ) and the available data on the flow past cone-cylinder and segment-cylinder bodies with large angles of the bend in the generator (θ s, c ≥ 30 • ) are generalized. On the basis of these data, the distinctive features of the transonic flow past these bodies and, primarily, the flow restructuring downstream of the leading corner edge at θ s ≥ 30 • are established and the characteristic gasdynamic parameters are determined. Emphasis is placed on the critical stage of flow restructuring, the nature of the stationary aerodynamic hysteresis, and the effect of the Reynolds number and wave disturbances.

Distinctive features of the transonic flow past a cone-cylinder body at small angles of the bend in the body generator at the leading corner edge

“…This paper continues review [1,2] of research on the transonic flow past oversized cone-cylinder bodies. The distinctive features of flow restructuring downstream of the leading corner edges of these bodies with increase in the Mach number are considered for the case of small angles of the bend in the body generator at the edge (θ s ≤ 20 • [2]).…”

“…After a weak, near-normal terminating shock 1 has been formed near the corner edge at a certain freestream Mach number M ∞ [2], with further increase in the Mach number ahead of this shock an oblique shock proceeding from the separation point of the separation zone 2 is formed at the same place (Fig. 2).…”

“…For large angles θ s and θ k , when the boundary layer separates behind the trailing corner edge of the cone-cylinder body [2], the effect of disturbances propagating from the downstream part of the flow on the restructuring process becomes appreciable for cylinder lengths l ≤ 1.5 [3,4]. In this case, convective mass transfer from the base to the lateral separation zone becomes possible.…”

“…The two shocks form a λ -shaped shock system. The separation zone is developed [2]. However, the pressure distribution is nonuniform and has a minimum near the corner edge and a maximum downstream of the reattachment region (Fig.…”

“…The distinctive features of flow restructuring downstream of the leading corner edges of these bodies with increase in the Mach number are considered for the case of small angles of the bend in the body generator at the edge (θ s ≤ 20 • [2]). The results of the experimental investigation of models with different geometric parameters (see Fig.…”