Disturbances Propagation in Supersonic Boundary Layers ()

Igor Lipatov^{*}, Tu Aung Cho^{2}

Theoretical Department, Central Aerohydrodynamic Institute, Zhukovsky, Moscow Region, Russia.

Department of Aeronautics, Moscow Institute of Physics and Techology, Zhukovsky, Moscow Region, Russia.

**DOI: **10.4236/apm.2014.412072
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Theoretical Department, Central Aerohydrodynamic Institute, Zhukovsky, Moscow Region, Russia.

Department of Aeronautics, Moscow Institute of Physics and Techology, Zhukovsky, Moscow Region, Russia.

Disturbances propagation processes are investigated in two-dimensional boundary layers for the case of strong viscous-inviscid interaction. The speed of upstream disturbances propagation as a function of specific heat ratio and Prandtl number is determined. Formula for speed propagation is developed on the basis of characteristics and subcharacteristics analysis corresponding to the gasdynamic wave processes and processes of convection and diffusion.

Keywords

Boundary Layer, Strong Viscous-Inviscid Interaction, Waves Propagation, Asymptotic Analysis

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Lipatov, I. and Cho, T. (2014) Disturbances Propagation in Supersonic Boundary Layers. *Advances in Pure Mathematics*, **4**, 635-640. doi: 10.4236/apm.2014.412072.

1. Introduction

Disturbances propagation in the boundary layers is associated with the processes of convection and diffusion [1] . Analysis of three-dimensional boundary layer equations [2] showed that the characteristics of this system of equations are lines normal to the streamlined surface. The appearance of these characteristics corresponds to the disturbances propagation with infinite velocity normal to the surface. These effects are associated with the pro- cesses of diffusion, which in reduced boundary layer equations take place in one direction. To describe the pro- cesses of disturbances propagation associated with convection, we should analyze the characteristics of the boundary layer equations without oldest derivatives (subcharacteristics). The equations of 2D unsteady boundary layer also allow the analysis of the characteristics and subcharacteristics [2] . However, because of the no slip condition on the surface, the flow near wall is subsonic, so there is a physical possibility for disturbances spread upstream. The results of experimental investigation of an upstream disturbances propagation are presented in [3] . Mathematical model describing disturbances propagation, implies that the pressure distribution is determined by viscous-inviscid interaction processes. At the same time, the classical theory of the boundary layer does not allow to describe such processes as the pressure distribution is prescribed. Effects of strong local viscous-inviscid interaction allow as well describing local separated flows [4] [5] , and flows with large local gradients [6] [7] .

Analysis of disturbances propagation in three-dimensional boundary layers for strong interaction led to determination of appropriate subcharacteristic surfaces [8] , separating the field of subcritical flow (subsonic in average) and supercritical flow (supersonic in average) in hypersonic boundary layer near the delta wing. Below unsteady flows in laminar boundary layers are investigated for the regime of strong viscous-inviscid interaction with the special emphasis on Prandtl number and specific heat ratio influence. Such results have not been obtained before.

2. Problem Formulation

It is supposed that flat plate is placed in hypersonic flow at zero angle of attack. It is supposed as well that strong viscous-inviscid interaction regime is realyzed [9] , for which next limits are valid:

(1)

where: Mach number of external glow, is the nondimensional boundary layer thickness

. For Cartesian coordinates directed along the surface and normally to the plate surface, time,

velocity vector components, density, pressure, full enthalpy, dynamic viscosity coefficient next definitions are intorduced:, correspondingly. Parameter is a characteristic plate length. Index corresponds to the dimensional external undisturbed flow values, index 0 corresponds to the dimensional value of dynamic viscosity coefficient at stagnation temperature. It is supposed that Reynolds number is large but doesn’t exceed critical value corresponding to the laminar-turbulent transition. It was shown that for large Mach numbers critical Reynolds number is large [10] .

Corresponding to the strong viscous-inviscid interaction theory disturbed flow region near the plate contains two-subregions: 1―inviscid flow between shock wave and boundary layer exteral edge, 2―viscous flow in the boundary layer.

In the subregion 1 next asymptotic expansions are valid:

(2)

Substitution of (2) expansions into the Navier-Stokes equations and limiting procedure (1) leads to the next system of equations

With the next boundary conditions on the shock wave:

And on external edge of the boundary layer

For subsequent analysis it is needed to get expression connecting boundary layer thickness or vertical velocity and induced pressure. Approximate formula is used

(3)

which is the tangent wedge formula generalization for unsteady regime.

For subregion 2 next expansions are valid:

(4)

Substitution (4) into the Navier-Stokes equations and limiting procedure (1) give unsteady boundary layer equations. Next transformation

leads corresponding mathematical problem to the next form

(5)

,

where is supposed that dynamic viscosity coefficient linearly depends on the temperature.

The last boundary condition corresponds to the prescribed base pressure value.

3. Subcharacteristics Determination

Let us determine characteristic (subcharacteristic) surfaces, associated with the induced pressure, which is not prescribed and should be determined as a result of solution.

After transformation

(6)

Boundary problem (5) takes the form

(7)

where

Interaction condition connecting pressure distribution and boundary layer thickness may be transformed to get next relation

(8)

Derivative in the left part of (8) may be expressed in accordance with the boundary layer thickness

The problem formulation (5) may be used to determine derivatives on the variable

After some transformations using (7)-(8) relations, the next expression may be obtained

(9)

where

Relation determining subcharacteristic surface has then the form

(10)

where a is an average speed of sound or velocity of subcharacteristic surface

Expression (10) is in fact known integral Pearson generalization [11] .

(11)

The sign of depends on average Mach number value in the boundary layer. Supersonic (in average ) flow is characterized by the negative L value, at the same time positive L value corresponds to the subsonic (in average) flow.

Relation (10) has simple physical explanation. In hypersonic boundary layer exists average velocity value. If average speed of sound is larger than this average velocity than the flow inside boundary layer is subcritical and disturbances can propagate upstream, otherwise the flow will be supercritical.

Relataion (10) may be deduced from (11) by easy way. If we will use moving coordinate system instead of steady system

In the moving coordinate system velocity in the boundary layer equals, while difference is proportional to the temperature and doesn’t change. Introducing expressions for иto the (11) we can arrive at (10) expression.

4. Solution Examples

As an example we can get dependence of an upstream disturbances propagation on specific heat ratio and on

Figure 1. Upstream disturbances propagation velocity a as a specific heat ratio and Prandtl number Pr function.

Prandtl number for self similar boundary layer equations solution.

Velocity and full enthalpy profiles were obtained as a result of the next boundary problem solution

(12)

These profiles have been used to obtain upstream disturbances propagation velocity.

Dependences of an upstream disturbances propagation velocity on specific heat ratio are presented on the Figure 1. Three curves correspond to different values of the Prandtl number. One curve corresponds to small Prandtl number value. Second curve corresponds to the and the third one corresponds to large Prandtl value.

We may conclude that Prandtl number influence on parameter is small. In fact Prandtl number influences on average velocity and full enthalpy profiles in the boundary layer.

It was supposed that specific heat ratio changes from unity (for polyatomic gas) up to the value 5/3 (for monoatomic gas). It may be concluded that speed of upstream disturbances propagation is larger for larger values. It may be shown that parameter tends to zero if specific heat ratio tends to unity.

Acknowledgements

This work was partially supported by the Russian Foundation for Basic Research (project № 13-01-06249).

Conflicts of Interest

The authors declare no conflicts of interest.

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[8] | Crocco, L. (1955) Consideration on the Shock-Boundary Layer Interactions. Proceedings of Conference of the High Speed Aeronautics, Brooklin Polytechn. Inst., New York, 75-112. |

[9] | Hayes, U.D. and Probstein, R.F. (1969) Hypersonic Flows Theory. Academic Press. |

[10] | Chapman, D.R., Kuehn, D. and Larson, H. (1958) Investigation of Separated Flows with Emphasis on the Effect of Transition. NACA Reports, N. 1356. |

[11] | Pearson, H., Holliday, J.B. and Smith, S.F. (1958) A Theory of the Cylindrical Ejector Propelling Nozzle. Journal of the Royal Aeronautical Society, 62, 746-751. |

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