Laminar heat transfer to a two-dimensional backward facing step from the high-enthalpy supersonic flow in the shock tube

AIAA Journal ◽  
1964 ◽  
Vol 2 (2) ◽  
pp. 251-255 ◽  
Author(s):  
JOSEF ROM ◽  
ARNAN SEGINER
Keyword(s):  
Heat Transfer ◽  
Supersonic Flow ◽  
Shock Tube ◽  
Two Dimensional ◽  
Backward Facing Step ◽  
High Enthalpy

Conjugate Heat Transfer Study of a Two-Dimensional Laminar Incompressible Wall Jet Over a Backward-Facing Step

2006 ◽  
Vol 129 (2) ◽  
pp. 220-231 ◽  
Author(s):  
P. Rajesh Kanna ◽  
Manab Kumar Das
Keyword(s):  
Heat Transfer ◽  
Nusselt Number ◽  
Average Nusselt Number ◽  
Conjugate Heat Transfer ◽  
Flow Property ◽  
Wall Jet ◽  
Two Dimensional ◽  
Interface Boundary ◽  
Backward Facing Step ◽  
Transfer Study

Steady-state conjugate heat transfer study of a slab and a fluid is carried out for a two-dimensional laminar incompressible wall jet over a backward-facing step. Unsteady stream function-vorticity formulation is used to solve the governing equation in the fluid region. An explicit expression has been derived for the conjugate interface boundary. The energy equation in the fluid, interface boundary and the conduction equation in the solid are solved simultaneously. The conjugate heat transfer characteristics, Nusselt number are studied with flow property (Re), fluid property (Pr), and solid to fluid conductivity ratio (k). Average Nusselt number is compared with that of the nonconjugate case. As k is increased, average Nusselt number is increased, asymptotically approaching the non-conjugate value.

The development of weak waves in the steady two-dimensional flow of a gas with vibrational relaxation past a thin wedge

1975 ◽  
Vol 69 (1) ◽  
pp. 109-128 ◽  
Author(s):  
R. P. Hornby ◽  
N. H. Johannesen
Keyword(s):  
Supersonic Flow ◽  
Shock Tube ◽  
Small Angle ◽  
Vibrational Relaxation ◽  
Method Of Characteristics ◽  
Numerical Solutions ◽  
Two Dimensional ◽  
Wave Decay ◽  
Two Dimensional Flow ◽  
Thin Wedge

The method of characteristics is used to calculate the supersonic flow past a wedge of small angle with non-equilibrium effects. The wave decay and development distances are presented in a concise similarity form which permits accurate extrapolation to very weak waves. The numerical solutions are compared with shock-tube flows of CO2 and N2O.

Heat-Transfer Measurements in an Inexpensive Supersonic Wind Tunnel: 2—Results for a Laminar Boundary Layer Based on a Two-Dimensional Flow Model

1955 ◽  
Vol 22 (3) ◽  
pp. 297-304
Author(s):  
Joseph Kaye ◽  
G. A. Brown
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Supersonic Flow ◽  
Laminar Boundary Layer ◽  
Flow Model ◽  
Two Dimensional ◽  
Round Tube ◽  
One Dimensional ◽  
Dimensional Flow ◽  
Two Dimensional Flow

Abstract Reliable experimental data on local heat-transfer coefficients for supersonic flow of air in a round tube are reanalyzed in detail with the aid of an approximate two-dimensional flow model. The results are compared with similar results based on a one-dimensional flow model and with the theoretical predictions for supersonic flow over a flat plate and for flow in the entrance region of a tube when a laminar boundary layer is present. The two-dimensional flow model yields a better understanding of the phenomena which occur for diabatic supersonic flow of air in a round tube than that obtained with the aid of the one-dimensional flow model. The two-dimensional flow model shows that the core Mach number is nearly constant along the length of test section for a range of values of the inlet diameter Reynolds number. For a laminar boundary layer the values of the local Stanton number agree within a few per cent with the theoretical values for plate flow at the largest values of the inlet diameter Reynolds number.

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