Nozzle Wall Boundary-Layer Transition and Freestream Disturbances at Mach 5

AIAA Journal ◽  
1975 ◽  
Vol 13 (3) ◽  
pp. 307-314 ◽  
Author(s):  
W. D. HARVEY ◽  
P. C. STAINBACK ◽  
J. B. ANDERS ◽  
A. M. CARY
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Transition ◽  
Nozzle Wall ◽  
Layer Transition ◽  
Wall Boundary Layer ◽  
Wall Boundary

Further Experiments on Shock Tube Wall Boundary-Layer Transition

AIAA Journal ◽  
1983 ◽  
Vol 21 (7) ◽  
pp. 1046-1048 ◽  
Author(s):  
Michael J. Chaney ◽  
William J. Cook
Keyword(s):  
Boundary Layer ◽  
Shock Tube ◽  
Tube Wall ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Wall Boundary Layer ◽  
Wall Boundary

Further experiments on shock tube wall boundary-layer transition

AIAA Journal ◽  
1985 ◽  
Vol 23 (8) ◽  
pp. 1298-1299
Author(s):  
William J. Cook ◽  
Michael J. Chancy
Keyword(s):  
Boundary Layer ◽  
Shock Tube ◽  
Tube Wall ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Wall Boundary Layer ◽  
Wall Boundary

Modeling of Rough-Wall Boundary Layer Transition and Heat Transfer on Turbine Airfoils

2008 ◽  
Vol 130 (2) ◽  
Author(s):  
M. Stripf ◽  
A. Schulz ◽  
H.-J. Bauer
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Boundary Layer Transition ◽  
Rough Wall ◽  
Layer Transition ◽  
New Model ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Turbine Airfoils

A new model for predicting heat transfer in the transitional boundary layer of rough turbine airfoils is presented. The new model makes use of extensive experimental work recently published by the current authors. For the computation of the turbulent boundary layer, a discrete element roughness model is combined with a two-layer model of turbulence. The transition region is modeled using an intermittency equation that blends between the laminar and turbulent boundary layer. Several intermittency functions are evaluated in respect of their applicability to rough-wall transition. To predict the onset of transition, a new correlation is presented, accounting for the influence of freestream turbulence and surface roughness. Finally, the new model is tested against transitional rough-wall boundary layer flows on high-pressure and low-pressure turbine airfoils.

Role of three-dimensional instabilities in compliant wall boundary-layer transition

AIAA Journal ◽  
1991 ◽  
Vol 29 (10) ◽  
pp. 1603-1610 ◽  
Author(s):  
Ronald D. Joslin ◽  
Philip J. Morris ◽  
Peter W. Carpenter
Keyword(s):  
Boundary Layer ◽  
Three Dimensional ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Compliant Wall

Modeling of Rough Wall Boundary Layer Transition and Heat Transfer on Turbine Airfoils

2006 ◽  
Author(s):  
M. Stripf ◽  
A. Schulz ◽  
H.-J. Bauer
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Boundary Layer Transition ◽  
Rough Wall ◽  
New Model ◽  
Free Stream Turbulence ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Turbine Airfoils

A new model for predicting heat transfer in the transitional boundary layer of rough turbine airfoils is presented. The new model makes use of extensive experimental work recently published by the current authors. For the computation of the turbulent boundary layer a discrete element roughness model is combined with a two-layer model of turbulence. The transition region is modeled using an intermittency equation that blends between the laminar and turbulent boundary layer. Several intermittency functions are evaluated in respect of their applicability to rough-wall transition. To predict the onset of transition a new correlation is presented, accounting for the influence of free-stream turbulence and surface roughness. Finally the new model is tested against transitional rough-wall boundary layer flows on high-pressure and low-pressure turbine airfoils.

An Investigation Into the Performance of Two Inlet Nozzles for Flow Measurement

1981 ◽  
Vol 103 (1) ◽  
pp. 67-72 ◽  
Author(s):  
H. Ito¯ ◽  
Y. Watanabe ◽  
H. Ishimaru ◽  
Y. Abe
Keyword(s):  
Boundary Layer ◽  
Flow Measurement ◽  
Separation Bubble ◽  
Boundary Layer Transition ◽  
Nozzle Wall ◽  
Layer Transition ◽  
Effect Of Pressure ◽  
Discharge Coefficients ◽  
Satisfactory Performance

The discharge coefficients for two inlet nozzles with different contraction shapes were studied experimentally together with the behavior of the boundary layer on the nozzle wall. For the inlet nozzle which has the same contraction shape as the ISA 1932 nozzle, it was found that boundary-layer transition with an intermediary separation bubble is responsible for the occurrence of a large hump in the discharge coefficients. The well-rounded inlet nozzle showed a satisfactory performance. The effect of pressure tap size and that of the proximity of a wall to the inlet on discharge coefficients were quantified experimentally.

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