The problem of unsteady coupled heat and mass transfer in the course of motion of a spherically blunted conical body fabricated with the use of thermal protection materials is considered. Numerical integration is applied to study the characteristics of heat and mass transfer at constant stagnation parameters (Mach number 6, altitude 15 km, and flight time 600 s), which impose severe constraints on the choice of materials for thermal protection. It is demonstrated that the use of advanced ceramic materials ensures an admissible temperature regime and maintaining the initial geometry of the body, including its motion at an angle of attack.

Investigations of Heat and Mass Transfer for Thermal Protection Materials in a Long Flight

The influence of flow parameters and nose radius on the location of laminar–turbulent transition is investigated. The model is an ogive-conical body of revolution having half angle about 9°. Experi...

https://journals.sagepub.com/doi/pdf/10.1177/0954410018788737

Laminar–turbulent transition reversal on blunt ogive body of revolution at hypersonic speeds:

The effect of the entropy layer generated by a small bluntness of the leading edge of a flat plate on laminar-turbulent transition of the supersonic boundary layer in the wake of an isolated roughness element (straight cylinder, 1 mm in diameter and 1 mm in height) situated on the plate surface is experimentally investigated. The bluntness radius varies. The experiments are performed at the Mach number 6 in the Reynolds number range (0.46–2.33) × 106, where the Reynolds number is based on the roughness location and the oncoming flow parameters. The reversal behavior of the roughness-induced turbulent wedges with increase in the bluntness is first revealed.

Entropy Effect in Laminar-Turbulent Transition of the Supersonic Boundary Layer in the Wake of an Isolated Roughness

Boundary-layer transition on slender blunt cone in hypersonic flow at zero incidence is under investigation. Main attention is paid to relatively large nose radius values when so-called transition reversal phenomenon is observed. Analysis of published experimental data shows that two regimes of reversal exist. The first one is relatively severe and is probably due to nosetip roughness. The second one is less pronounced and further increase of bluntness breaks reversal tendency. It turns out that flight transition location on pre-reversal regime is fairly good predicted by correlation based on ground tests.

Scenarios of laminar-turbulent transition reversal on blunt cone in hypersonic flow

The influence of the flat-plate leading-edge shape on laminar–turbulent transition is investigated. Experiments were carried out at a Mach number of M∞=5; a unit Reynolds number Re1∞ from 1.5×107 t...

Laminar–Turbulent Transition Reversal on a Blunted Plate with Various Leading-Edge Shapes

http://www.dl.begellhouse.com/download/article/2c2b59c57f7ad696/TsAGI4003 (309-319).pdf

A. V. Vaganov

Papers

Experimental and numerical investigations of boundary layer transition on blunted cones at supersonic flow