Outgoing Acoustic Waves in an Unstable Supersonic Laminar Boundary Layer Over a Flexible Surface

1992 ◽  
pp. 337-343 ◽  
Author(s):  
Abdelkader Frendi ◽  
Lucio Maestrello ◽  
Alvin Bayliss
Keyword(s):  
Boundary Layer ◽  
Laminar Boundary Layer ◽  
Acoustic Waves ◽  
Flexible Surface ◽  
Supersonic Laminar

Oblique slot blowing into a supersonic laminar boundary layer

1976 ◽  
Vol 80 (3) ◽  
pp. 541-554 ◽  
Author(s):  
N. Riley
Keyword(s):  
Boundary Layer ◽  
Laminar Boundary Layer ◽  
Free Stream ◽  
Length Scales ◽  
Supersonic Laminar

The response of a supersonic laminar boundary layer is considered when fluid is blown obliquely into it from a slot in the boundary. The velocity and length scales associated with the slot blowing are chosen in such a way that the triple-deck theory of Stewartson (9) may be exploited. It is shown that, depending upon the blowing angle, there can be either a compressive or expansive interaction between the boundary layer and free stream upstream from the slot.

THEORETICAL INVESTIGATIONS OF A SUPERSONIC LAMINAR BOUNDARY LAYER WITH FOREIGN-GAS INJECTION

AIAA Journal ◽  
1963 ◽  
Vol 1 (1) ◽  
pp. 148-158 ◽  
Author(s):  
STEVEN I. FREEDMAN ◽  
JOHN R. RADBILL ◽  
JOSEPH KAYE
Keyword(s):  
Boundary Layer ◽  
Laminar Boundary Layer ◽  
Gas Injection ◽  
Theoretical Investigations ◽  
Supersonic Laminar

On slot injection into a supersonic laminar boundary layer

1973 ◽  
Vol 332 (1588) ◽  
pp. 1-22 ◽  
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Boundary Conditions ◽  
Pressure Gradient ◽  
Laminar Boundary Layer ◽  
Extreme Conditions ◽  
Numerical Work ◽  
Plate Length ◽  
Injection Region ◽  
Supersonic Laminar

The structure of a supersonic laminar boundary layer near a flat plate is examined when fluid is injected into it, normal to the surface, with velocity O (∊ 3 U * ∞ ) over a distance O (∊ 3 L). Here U * ∞ is the undisturbed velocity of the fluid, L is the plate length and ∊ -8 is a representative Reynolds number of the flow. It is found that the pressure rises upstream of the injection region and that in all the cases fully computed the blowing takes place in a favourable pressure gradient. Afterwards the pressure rises to its undisturbed value. Further incomplete studies suggest that in more extreme conditions, e. g. longer slots, the pressure gradient can be adverse just downstream of the start of the blow and that separation can even occur there. The analytical discussion rests heavily on the notion of the triple-deck, a subdivision of the boundary layer suitable for investigating its response to sudden changes in boundary conditions. Extensive numerical work is also required and the methods devised fail when the boundary layer separates at the onset of the blow. The relation between this type of injection and weak plate injection where the blowing velocity is O (∊ 4 U * ∞ ) and extends over a distance O ( L ) is also considered.

Supersonic laminar boundary layer near the plane of symmetry of a cone at incidence

1972 ◽  
Vol 51 (1) ◽  
pp. 1-14 ◽  
Author(s):  
Bernard Roux
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Laminar Boundary Layer ◽  
External Flow ◽  
Leeward Side ◽  
Detailed Consideration ◽  
Boundary Layer Equations ◽  
Similarity Method ◽  
Supersonic Laminar ◽  
Critical Incidence

Supersonic laminar boundary-layer equations near the plane of symmetry of a cone at incidence are treated by the similarity method. Numerical integration of differential equations governing such a flow is performed, taking into consideration the temperature dependence of the Prandtl numberPrand viscosity μ throughout the boundary layer. On the leeward side, a detailed consideration of the solutions shows the existence of two solutions up to a critical incidence beyond which it appears that no solution may be found. Calculations carried out for a set of values of the external flow Mach number show up a significant effect of this parameter on the behaviour of the boundary layer.

Supersonic laminar boundary layer along a two- dimensional adiabaticcurved ramp.

AIAA Journal ◽  
1969 ◽  
Vol 7 (2) ◽  
pp. 298-304 ◽  
Author(s):  
DENNY R. S. KO ◽  
TOSHI KUBOTA
Keyword(s):  
Boundary Layer ◽  
Laminar Boundary Layer ◽  
Two Dimensional ◽  
Supersonic Laminar
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