Numerical Study of Supersonic Boundary-Layer Transition due to Sonic Wall Injection

AIAA Journal ◽  
2017 ◽  
Vol 55 (5) ◽  
pp. 1530-1547 ◽  
Author(s):  
T. André ◽  
A. Durant ◽  
I. Fedioun
Keyword(s):  
Boundary Layer ◽  
Numerical Study ◽  
Supersonic Boundary Layer ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Wall Injection

Numerical Study of Wall Influence on Boundary-Layer Transition for Two-Dimensional NACA 16-012 and 4412 Hydrofoil Sections

1990 ◽  
Vol 34 (01) ◽  
pp. 38-47
Author(s):  
R. Latorre ◽  
R. Baubeau
Keyword(s):  
Boundary Layer ◽  
Test Section ◽  
Numerical Study ◽  
Suction Side ◽  
Boundary Layer Separation ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Turbulent Separation ◽  
Side Pressure ◽  
Effective Angle

One of the difficulties in hydrofoil model tests is the relatively low Reynolds number of the test piece and the presence of the test section walls. This paper presents the results of systematic calculations of the potential flow field of NA 4412 and NACA 16-012 hydrofoil in a test section with wall-to-chord ratios h/c -1.0. The corresponding boundary-layer calculations using the CERT calculation scheme are presented to show the influence of the nearby walls on shifting the location of the boundary-layer laminar-turbulent separation as well as turbulent separation. By introducing an effective angle of attack, it is possible to obtain close agreement in the calculated and measured suction side pressure distortion as well as the locations of the boundary-layer separation and transition.

Experimental Investigation of Single Roughness Element Effects on Supersonic Boundary Layer Transition

2014 ◽  
Author(s):  
Henny Bottini ◽  
Bayindir H. Saracoglu ◽  
Guillermo Paniagua
Keyword(s):  
Boundary Layer ◽  
Wall Temperature ◽  
Roughness Element ◽  
Pressure Fluctuations ◽  
Supersonic Boundary Layer ◽  
Boundary Layer Transition ◽  
Adiabatic Wall ◽  
Layer Transition ◽  
Temperature And Pressure ◽  
Unsteady Effects

Predicting the characteristics of a transitional boundary layer remains an open challenge in supersonic flow fields. An experimental campaign to understand the effects of a single roughness element on a supersonic laminar boundary layer was designed. Two Mach numbers were tested, 1.6 and 2.3, including two roughness heights, 0.1 mm and 1 mm, over a flat plate. Steady and unsteady wall temperature and pressure levels were recorded to interpret the influence of the wake of the roughness. Heat flux and adiabatic wall temperature trends, temperature and pressure fluctuations RMS trends and time evolution of spectral content were reported. The initial wall temperature was varied during the wall temperature measurements and the resulting steady and unsteady effects on the roughness wake were investigated.

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