Theoretical Investigation Of 3 D Shock Wave Turbulent Boundary Layer Interactions

Theoretical Investigation of 3-D Shock Wave-turbulent Boundary Layer Interactions

Theoretical Investigation of 3-D Shock Wave-Turbulent Boundary Layer Interactions

This research describes continuing efforts in the analysis of 3-D shock wave turbulent boundary layer interactions. A significant research activity in 3-D hypersonic shock turbulent interactions is initiated to further develop and validate the theoretical model. The quasiconical free interaction principle is examined by simulation of two geometries -17.5 deg sharp fin and (30,60) swept compression corner (Mach 3) - selected to obtain similar shock strengths. The comparison with experimental data is good. It is confirmed that the differences caused by the particular geometry of the model appear only behind the inviscid shock wave. Continuing research on 3-D turbulent interaction control is focused on the effect of bleed and the simulation of flows past the double-fin configuration. The effect of suction is examined on a strong (fin angle=20 deg, Mach 3) and a weak interaction (8 deg, Mach 3). The overall effect of bleed is remarkably modest. Two double-fin configurations (4 x 4 and 8 x 8, Mach 3) are simulated. A study of the computed flowfield indicates that the first is a weak interaction. In contrast, the 8 x 8 configuration displays an interesting separated flowfield. An analysis of viscous and inviscid effects in a sharp fin and a swept corner flow indicates that the physics of both geometries are governed primarily by inviscid (pressure) effects. Viscous effects are of lower magnitude but are not restricted to the sublayer region. High speed flows; Viscous inviscid interactions; Boundary layer interactions; Computational fluid dynamics; Navier stokes equations; Turbulence.(mjm).

Theoretical Investigation of 3-D Shock Wave Turbulent Boundary Layer Interactions

This report summarizes the research project Theoretical Investigation of 3-D Shock Wave - Turbulent Boundary Layer Interactions during the period 1 October 1992 to 31 July 1996. The principal objectives of the research are the investigation of 3-D shock wave-turbulent boundary layer interactions (3-D turbulent interactions) for complex configurations (e.g., asymmetric shock), and the investigation of the accuracy of Chien's k - epsilon turbulence model, a newly developed Reynolds Stress Equation turbulence model and a k - epsilon model with a new low Reynolds number correction for 3-D turbulent interactions, with specific focus on the ability to predict surface heat transfer and skin friction. Accomplishments during the project include the development of a Reynolds Stress Equation (RSE) model (including determination of all constants), and computation of 3-D asymmetric and symmetric shock interactions at Mach 4 using Chien's k - epsilon turbulence model, the RSE model and the k - epsilon model with the new low Reynolds number correction. The report also provides a list of publications, scientific interactions and personnel.