Supersonic flow past axisymmetric flared cones

Abstract

Systematic data on the determination of the aerodynamic characteristics of axisymmetric bodies with a break in the generating line (Fig. 1a, b) in supersonic flow at zero angle of attack are presented in [1, 2, and others]. A characteristic feature of the flow past such bodies is the appearance of an extensive separation zone dec in the region of the break in the generator when the break angle exceeds some minimum value δ∘≥δ_min, which for a turbulent boundary layer depends basically on the Mach number M at the body surface ahead of the separation zone. In this case, compression waves which change into the oblique compression shocks dc′ and cc′, emanate both from the beginning of the separation zone (point c) and from the end of it (point d). These shocks, intersecting at the point c′, form the triple shock configuration ac′d and ac′c for which we introduce the notationac′[c, d]. The maximum value (δ_max) of the generator break angle is limited by the possibility of the existence of an attached compression shock, dc′. According to these data a change in the generator break angle for the range δ_min≤δ∘≤δ_max of the angle does not disrupt the nature of the flow in the separation zone, but only alters the size of this zone.

We shall examine the flow past cones with values of the generator break angles (δ∘≥δ_max) for which the attached shock dc′ cannot exist.