scholarly journals Unit Reynolds number, Mach number and pressure gradient effects on laminar–turbulent transition in two-dimensional boundary layers

2018 ◽  
Vol 59 (5) ◽  
Author(s):  
Steffen Risius ◽  
Marco Costantini ◽  
Stefan Koch ◽  
Stefan Hein ◽  
Christian Klein
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Pressure Gradient ◽  
Boundary Layers ◽  
Two Dimensional ◽  
Unit Reynolds Number ◽  
Turbulent Transition ◽  
Dimensional Boundary ◽  
Gradient Effects ◽  
Laminar Turbulent Transition

Coupling PSE and FLUENT to Predict Laminar-Turbulent Transition in Boundary Layers

2013 ◽  
Vol 432 ◽  
pp. 168-172
Author(s):  
Y. Zhou ◽  
Y.H. Fang
Keyword(s):  
Flat Plate ◽  
Boundary Layers ◽  
Three Dimensional ◽  
Basic Flow ◽  
Two Dimensional ◽  
S Wave ◽  
S Waves ◽  
Turbulent Transition ◽  
Transition Criterion ◽  
Laminar Turbulent Transition

In this paper, the coupling method of PSE and FLUENT was experimented for predicting the laminar-turbulent transition. The software FLUENT was used to get the basic flow over a flat plate. A two-dimensional T-S wave and a pair of three-dimensional T-S waves were fed in at the entrance. The transition criterion was verified by DNS results. The availability of the coupling methodology has been evaluated.

Reynolds Number and Pressure Gradient Effects on Compressible Turbulent Boundary Layers

AIAA Journal ◽  
1978 ◽  
Vol 16 (12) ◽  
pp. 1217-1218 ◽  
Author(s):  
M. Acharya ◽  
M. I. Kussoy ◽  
C. C. Horstman
Keyword(s):  
Reynolds Number ◽  
Pressure Gradient ◽  
Boundary Layers ◽  
Turbulent Boundary Layers ◽  
Gradient Effects

Effect of Suction on the Stability of Supersonic Boundary Layers. Part I—Second-Mode Waves

1991 ◽  
Vol 113 (4) ◽  
pp. 591-597 ◽  
Author(s):  
A. A. Al-Maaitah ◽  
A. H. Nayfeh ◽  
J. A. Masad
Keyword(s):  
Mach Number ◽  
Boundary Layers ◽  
Mass Flux ◽  
Two Dimensional ◽  
Second Mode ◽  
Wave Numbers ◽  
Stabilizing Effect ◽  
Dimensional Boundary ◽  
The Stability ◽  
And Shifts

The effect of suction on the second (Mack) mode of instability in supersonic and hypersonic two-dimensional boundary layers is investigated. The results show that suction has a stabilizing effect on these waves; it reduces the peak amplification and shifts it toward a higher frequency. In the presence of suction, the most amplified Mack mode remains two-dimensional. The effectiveness of suction in stabilizing Mack waves decreases as the Mach number increases. Variations of the growth rates of the most amplified Mack mode and the corresponding frequencies and wave numbers with mass flux are found to be almost linear. The frequencies and wave numbers corresponding to the most amplified Mack mode increase by increasing the suction level.

scholarly journals Experimental Study of the Influence of Unit Reynolds Number on the Laminar-Turbulent Transition on the Model Swept Wing with a Subsonic Leading Edge at M = 2

2021 ◽  
Vol 16 (1) ◽  
pp. 44-52
Author(s):  
Vasilii L. Kocharin ◽  
Nikolai V. Semionov ◽  
Alexander D. Kosinov ◽  
Aleksey A. Yatskikh ◽  
Sofia A. Shipul ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Experimental Studies ◽  
Leading Edge ◽  
Supersonic Boundary Layer ◽  
Swept Wing ◽  
Unit Reynolds Number ◽  
Flow Parameters ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Experimental studies of the influence of unit Reynolds number on the laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge at Mach number 2 are performed. The experiments were performed on a model of a swept wing with a swept angle of the leading edge of 72 degrees and with a 3% profile with a variable chord length in span. The hot-wire measurements showed that a laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge occurs earlier (~25-30%) than on a model with a supersonic leading edge with the same oncoming flow parameters. It is shown that a change unit Reynolds number insignificant influence the laminar-turbulent transition in the boundary layer of a swept wing with a subsonic leading edge.

Sign in / Sign up

Export Citation Format

Share Document