# Spatial-Temporal Instability of an Inviscid Shear Layer

Authors: Qing-fei Fu; Li-zi Qin; Li-jun Yang
Journal: International Journal of Aerospace Engineering
 (2017)

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## Abstract

In this work, we explore the transition of absolute instability and convective instability in a compressible inviscid shear layer, through a linear spatial-temporal instability analysis. From linearized governing equations of the shear layer and the ideal-gas equation of state, the dispersion relation for the pressure perturbation was obtained. The eigenvalue problem for the evolution of two-dimensional perturbation was solved by means of shooting method. The zero group velocity is obtained by a saddle point method. The absolute/convective instability characteristics of the flow are determined by the temporal growth rate at the saddle point. The absolute/convective nature of the flow instability has strong dependence on the values of the temperature ratio, the velocity ratio, the oblique angle, andM number. A parametric study indicates that, for a great value of velocity ratio, the inviscid shear layer can transit to absolute instability. The increase of temperature ratio decreases the absolute growth rate when the temperature ratio is large; the effect of temperature ratio is opposite when the temperature ratio is relatively small. The obliquity of the perturbations would cause the increase of the absolute growth rate. The effect of M number is different when the oblique angle is great and small. Besides, the absolute instability boundary is found in the velocity ratio, temperature ratio, and M number space.


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## Body

## 1. Introduction

A high mixing rate of the fuel and air is desired in scramjet engine for the propulsion of hypersonic aircraft, because the residence time of the fuel and air in the combustion chamber is very short. In the interest of the projected use of the scramjet engine, it is fundamental and also extremely important to understand the stability characteristics of compressible shear/mixing layers. Many experimental studies [1–3] suggested that the mixing rates of shear layers decrease as the Mach number increases from zero. Hence, a major concern in the development of scramjet is the mixing enhancement techniques. Imparting disturbances on the shear layer, which pulsate at some prescribed frequency, is a choice of mixing enhancement techniques. The prescribed frequency can be obtained through linear stability analysis of the compressible shear layer.There have been numerous literatures on the topic of linear stability analysis of the compressible shear layer, including the earlier studies conducted by Lessen et al. [4, 5] Drazin and Davey [6] performed a temporal stability analysis of a compressible mixing layer, which has a hyperbolic tangent velocity profile and uniform temperature throughout the layer. Jackson and Grosch [7] reported the results of the inviscid spatial stability of a parallel compressible mixing layer. All these studies found multiple stability modes. Zhuang et al. [8] and Ragab [9] both found a strong stabilization effect on the flow when increasing Mach number. Ho and Huerre [10] summarized the studies on linear stability analysis of incompressible shear layer. For the studies on linear stability analysis of compressible shear layer, the reader can refer to the relevant literature in the monograph by Criminale et al. [11].The studies above are all confined in the scope of temporal or spatial mode. When we study the stability characteristics of shear layers in spatial-temporal mode, which treat both spatial and temporal eigenvalue complex [12, 13], there are two distinct instabilities for spatial-temporal evolving disturbances: convective and absolute instabilities. The concept of absolute and convective instabilities was first put forward by Briggs [14] in the study of plasma instability and then introduced to classical hydrodynamic stability [15]. A flow is convectively unstable if the unsteady response to an impulsive perturbation grows along some rays that pass away from the forcing location but decays at the forcing location itself. A flow is absolutely unstable if the impulse response grows at the forcing location [16].An absolutely unstable flow is not sensitive to external disturbances and initial conditions; consequently, the “flow management” techniques such as forcing the shear layer at some prescribed frequency could be useless. [17]. Thus, if we want to control the downstream evolution of the flow, it is essential to determine whether the shear/mixing layer is convectively or absolutely unstable. Kulikovskii and Shikina [18–20] studied the asymptotic behavior of localized perturbations on the surface of a shear discontinuity separating two homogeneous steady flows of ideal incompressible fluid in the linear approximation. The effect of surface tension, gravity forces, and viscosity is taken into account. Pavithran and Redekopp [21] investigated the absolute and convective instabilities for a subsonic mixing layer with the hyperbolic-tangent-like profiles in velocity and temperature fields. The study on transition of absolute and convective instability for compressible shear layer is rare. Caillol [22] analyzed the transition of absolute and convective instabilities for an inviscid mixing layer. The Mach number in his work attained high supersonic values. However, he did not consider the density stratification within the mixing layer. Large density stratification is possible for binary mixing layers at high pressures, which is usually encountered in power and propulsion system.The aim of this paper is to track the transition between the absolute instability and convective instability in a compressible shear layer. The density stratification is taken into account. The effects of flow parameters on the spatial-temporal stability of a compressible shear layer are examined by observing whether an increase of the value of parameter tends to increase or decrease the value of absolute growth rate.


## 2. Theoretical Framework

The base flow is a shear layer between two streams with its far-stream condition denoted by the subscripts∞ and -∞, as shown in Figure 1. The thickness of shear layer increases with increasing distance downstream, denoting that the base flow is nonparallel. Here, we made a locally parallel flow assumption, implying that the present results yield the instability characteristics of individual profiles to leading order when the shear layer thickness grows slowly with downstream distance [23]. The streamwise direction is defined as x and the cross stream is defined as y. In the present study, U denotes the velocity, ρ the density, and T the temperature. Taking the momentum thickness θ and average mean velocity U-=(U∞+U-∞)/2 as the characteristic length and velocity scale, respectively, the flow properties can be normalized. Superscript ∗ denotes a nondimensional quantity.Figure 1
Schematic of a shear layer between two streams.The linear stability analysis, the features of which are standard and, hence, are not presented in detail here, is performed for a flow governed by the conservation equations of continuity, momentum, and energy. The thermodynamic condition of the layer is assumed far above the critical point, so the ideal-gas equation of state is used to close the formulation. Linearization of these equations starts by splitting the dependent variables into base and perturbation components. A base flow is assumed that is described by the normalized velocity profileu-∗(y∗) and temperature profile T-∗(y∗) specified as (1)-(2) and by a constant thermodynamic pressure [24]:(1)u-∗=1+Λtanh⁡y∗2(2)T-∗=ST+12+ST-12tanh⁡y∗2,where the velocity ratio is defined as Λ=(U∞-U-∞)/(U∞+U-∞) and the temperature ratio is defined as ST=T∞/T-∞. The density distributions are obtained by employing the ideal-gas equation of state on the shear layer with the temperature distribution defined in (2).We perturbed the steady-state solution of the flow with a small-amplitude wave in normal modes:(3)q′x,y,z,t=q^yexp⁡ikxcos⁡ϕ+zsin⁡ϕ-ct=q^yexp⁡ikxcos⁡ϕ+kzsin⁡ϕ-ωt,where q′ denotes the perturbation components, q^ denotes the perturbation wave amplitude, k, c, and ω(ω=kc) are the wave number, phase speed, and frequency, respectively. ϕ denotes the angle between the wave propagation direction and the streamwise direction of the mean flow. When the disturbance wave propagates in the axial direction, ϕ equals zero, and the resultant system is a two-dimensional problem.To derive the governing equation forp^∗(y∗), the governing equations and equation of state are linearized by considering small perturbations to the mean flow whose velocity and temperature profiles are u-∗(y∗) and T-∗(y∗), respectively. By employing a process of elimination, a single equation can be derived for the radial component of the pressure perturbation p^∗ [25–28]:(4)d2p^∗dy∗2-2u-y∗cos⁡ϕu-∗cos⁡ϕ-c∗+ρ-y∗ρ-∗dp^∗dy∗-k∗21-M2p^∗=0,where M=(u-cos⁡ϕ-c)/a-, a- denotes the speed of sound. For simplicity of notation, the subscript y stands for the spatial derivative with respect to the y coordinate. The governing equation of the two-dimensional incompressible shear layer can be found by setting ϕ=0 and M=0.Solution of (4) poses an eigenvalue problem due to the presence of the wave parameters, k∗, and frequency, ω∗=k∗c∗. The boundary conditions are obtained by considering that (i) at far stream the base flow derivatives are zero and that (ii) the solution must be bounded. The solution is obtained by treating the frequency as the eigenvalue for an externally specified wavenumber and by using a shooting iterative procedure. ODE45 in MATLAB is employed to perform the numerical integration of the ordinary differential equation, and the Newton-Raphson shooting method is utilized to perform the iterative shooting to find the eigenvalue. Convergence is found to be strongly dependent on a good starting guess for ω∗. The detailed process is as follows: to obtain the ω∗(k∗) relations, we begin from an intermediate k∗ (e.g., k∗=0.4) and make an initial guess for ω∗. Then, the Newton-Raphson shooting method is used, assuming the initial guess for ω∗ is good enough to obtain the exact ω∗. Then we decrease or increase k∗ by Δk∗ and use ω∗ calculated with the old k∗ as the initial guess for the new shooting iteration. If the shooting iteration converges again, we will move to the smaller or larger k∗. With this computing process, the ω∗-k∗ curve extends from the middle to both low and high k∗ regimes. If, at some point, the shooting method diverges or can not obtain a physical solution, or the resultant ω∗-k∗ curve is not smooth enough, we conclude that the initial guess for ω∗ at k∗=0.4 is incorrect and we provide a new guess and start over again. It is by this process that the ω∗-k∗ contours presented in this article are obtained.This study focuses on the transition between absolute instability (AI) and convective instability (CI) for a compressible inviscid shear layer, which are dominated by modes with zero group velocity. These correspond to complex pairs,(k0∗,ω0∗), which satisfy (4) and also the further property that ∂ω∗/∂k∗=0.The saddle point method is used to determine the solution with zero group velocity. In general, there are two distinct spatial branches of solutions of (4) on the complex k∗ plane. The two branches will approach each other as the growth rate ωi∗ is decreased from large positive values, and a saddle point on the complex k∗ plane will occur at point k∗=k0∗. It is necessary to identify the physical and nonphysical saddle points. The physical saddle point must satisfy the Briggs-Bers collision criterion [14, 29]. According to the Briggs-Bers collision criterion, the only relevant complex pair (k0∗,ω0∗) is the physical pair, if the two branches come, respectively, from the downstream-propagating branch k∗+(ω∗) and upstream-propagating branch k∗-(ω∗) on the complex k plane. Then if ω0i∗<0 the flow is said to be convectively unstable, while if ω0i∗>0, the flow is said to be absolutely unstable. Normally, k0∗ is referred to as the absolute wave number and ω0i∗ the absolute growth rate.


## 3. Results and Discussion

In this section, the effects of dimensionless parameters on the spatial-temporal instability of an inviscid shear layer will be checked by taking a parametric study. The complex frequencyω∗ is solved as function of the wave number k∗ and the parameter set (Λ, ST,M, and ϕ).The typical contour plots of the imaginary part of the complex frequencyωi∗ in the complex wave number k∗ plane for an inviscid compressible shear layer are shown in Figure 2. Apparently, there is a saddle point in the plot, which is marked with“S.” The location of the saddle point is k0∗=(0.458,-0.742) and the value of real part of complex frequency at the saddle point is ω0i∗=-0.245. The saddle point satisfies the Briggs pinching criterion. In Figure 2, the absolute growth rates are negative, indicating that the inviscid shear layer is convectively unstable with the given dimensionless parameters.Figure 2
Contours ofωi∗ = constant in the complex k∗ plane (Λ=1, ϕ=0, M=0, ST=5).The effect of velocity ratio Λ on the absolute instability of an inviscid shear layer is illustrated in Figure3. It appears in Figure 3 that the absolute growth rate increases with the increases of velocity ratio Λ. In particular, when the velocity ratio is larger than 1.47, the absolute growth rate becomes positive. The transition velocity ratio 1.47 was close to the value obtained by Huerre and Monkewitz [12], which was 1.315. Huerre and Monkewitz [12] stated that the mixing layer is absolutely unstable when velocity ratio is larger than 1.315. That is because Huerre and Monkewitz considered shear layer in incompressible fluid, whereas the present paper deals with perfect gas. The velocity ratio represents the shear force imparted on the shear layer; therefore, it can be said that, for a two-dimensional inviscid shear layer, it is absolutely unstable when the shear force imparted on it is relatively large. Manoharan and Hemchandra [23] proposed a mechanism through which absolute instability can cause combustion instability in combustor of power generation and propulsion system. Hence, avoiding the occurrence of absolutely unstable flows in combustors, at least at desired operating conditions, represents a possible passive control strategy to mitigate the occurrence of combustion instability. According to Figure 3, to depress absolute instability, a possible smallest velocity ratio is recommended. However, small velocity ratio, denoting weak shear force imparted on the shear layer, shows no advantage on mixing. Thus the velocity ratio should be designed specially in a combustor.Figure 3
The variation of absolute growth rate with velocity ratioΛ (ϕ=0, M=0, ST=3).Figure4 gives the effects of the temperature ratio, ST, on the absolute growth rate of a two-dimensional inviscid shear layer, by increasing ST and keeping other parameters constant for every plot. Figure 4 shows that, for different cases, as the temperature ratio increases, the absolute growth rate decreases. Hence the strategy for suppressing absolute instability is to increase temperature ratio.Figure 4
The variation of absolute growth rate with temperature ratioST.However, the temperature effects do not always tend to depress the absolute instability. When the temperature ratio is relatively small (ST<1), the absolute growth rates shows minor increase with increase of ST for every case. That is to say when ST is relatively large, the effect of ST on absolute growth rate is more remarkable; when ST is small, ST has minor promotion effect on absolute instability of the shear layer.Now, we check the effect of obliquity of the disturbance wave on the absolute instability by varying the oblique angle,ϕ. Figure 5 shows the variation of absolute growth rate ω0i∗ with oblique angle ϕ. It shows in Figure 5 that when the flow is two-dimensional (ϕ=0), the absolute growth rate is the smallest. When the oblique angle increases, the absolute growth rate increases. The increasing rate becomes larger when the oblique angle is greater. However, the absolute growth rate is always negative when ϕ varies from 0 to π/2. Hence, it can be concluded that the increase of oblique angle can increase the absolute growth rate, and the effect is more remarkable when the oblique angle is greater, or we can say that the three-dimensional disturbance waves are more dominant in inviscid shear layer than two-dimensional wave. But the increasing of ϕ would never change the flow into absolute instability.Figure 5
The variation of absolute growth rate with oblique angleϕ (Λ=1, M=0, ST=2).The parameterM is naturally supposed to be parameter influencing the absolute instability behavior of flow. Here we check the effect of M and oblique angle comprehensively. Figure 6 gives the variation of absolute growth rate with M and oblique angle. It shows that, for a constantM, the increase of oblique angle would increase the absolute growth rate, which can also be seen from Figure 5. For a given oblique angle, the effect of M number on absolute growth rate differs when oblique angle is larger or relatively small. When the oblique angle is small, the increase of M would decrease the absolute growth rate; while the oblique angle is greater (close to π/2), the effect of increasing M is minor. That means the effect of M number is opposite when the disturbances propagate upstream and downstream.Figure 6
The variation of absolute growth rate with oblique angle andM number (Λ=1, ST=2).Figure7 shows the critical value of Λ at which the flow transits into absolute instability at different M and ST. It can be seen from Figure 7 that the increase of ST would cause the critical value of Λ decrease; that is, the increase of ST would expand the absolute instability region in ST-Λ-M space. However, the variation of M has no influence on the absolute instability boundary, although the increase of M can decrease the absolute instability growth rate.Figure 7
The boundary of transition between AI and CI in the parameter space ofΛ, M, and ST (ϕ=0).


## 4. Conclusions

In this work, we explore the transition of absolute instability and convective instability in a compressible inviscid shear layer, through a linear spatial-temporal instability analysis. From linearized governing equations of the shear layer and the ideal-gas equation of state, the dispersion relation for the pressure perturbation was obtained. The dispersion relation was solved using a shooting iterative procedure. The numerical results show that the increasing velocity ratio can make the inviscid shear layer transition to absolute instability. The increase of temperature ratio decreases the absolute growth rate when the temperature ratio is large; the effect of temperature ratio is opposite when the temperature ratio is relatively small. The obliquity of the perturbations would cause the increase of absolute growth rate. The effect ofM number is different when the oblique angle is large or small: when the oblique angle is relatively smaller, the increase of M number would decrease the absolute growth rate; while the oblique angle is relatively large (close to π/2), the variation of M number has no influence on the absolute growth rate. The absolute instability boundary has been given in the ST -M-Λ space. The increase of ST would expand the absolute instability region in the ST -M-Λ space, but the variation of M has no influence on the absolute instability boundary.



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*Source: 8532507-2017-04-09.xml*