The Prediction of Axisymmetric Turbulent Boundary Layer in Conical Nozzles

1974 ◽  
Vol 41 (1) ◽  
pp. 20-24
Author(s):  
S. B. Au
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Pressure Gradient ◽  
Digital Computer ◽  
Computation Method ◽  
State Equations ◽  
Favorable Pressure Gradient ◽  
Theoretical Predictions ◽  
Flow Through ◽  
Throat Section

A theoretical axisymmetric model of flow through conical Venturimeters, capable of solution by digital computer, has been developed to predict the development of the turbulent boundary layer along the convergent and throat section where the flow is subjected to a favorable pressure gradient. A computation method was developed to solve the momentum, auxiliary, continuity, and state equations simultaneously step-by-step. For a given inlet condition the throat condition can be predicted. Theoretical predictions were compared with experimental results obtained from two 10-in-dia Venturimeters of area ratios 0.25 and 0.5. The agreement between the theory and detailed boundary-layer surveys is good.

Transonic Normal Shock-Turbulent Boundary Layer Interaction in Pressure Gradient Flows

1977 ◽  
Author(s):  
A. G. Panaras ◽  
G. R. Inger
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Pressure Gradient ◽  
Normal Shock ◽  
Pressure Gradients ◽  
Local Boundary ◽  
Boundary Layer Interaction ◽  
Theoretical Predictions ◽  
Disturbance Analysis ◽  
Separating Flows

A basic theoretical analysis of the interaction of a transonic normal shock wave with a non-separating turbulent boundary layer in a background pressure gradient is given. The method is based on an extension of Inger and Mason’s small disturbance analysis to account for both explicit pressure gradients upstream and downstream of the interaction and the implicit pressure gradient effects on the local boundary layer shape plus the back-effect of the interaction-induced boundary layer thickness growth (blockage) that is important in channel flows and turbomachinery applications. The theory predicts the detailed disturbance pressure and skin friction distributions, including lateral pressure gradients, and is readily imbedded locally in a global calculation scheme involving transonic inviscid and boundary layer prediction codes upstream and downstream of the shock. Good agreement is found between the resulting theoretical predictions and experimental results for non-separating flows.

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