# Stability analysis of confined V-flames. I. Analytical treatment

of the high-velocity limit

###### Abstract

The problem of linear stability of confined V-flames with arbitrary gas expansion is addressed. Using the on-shell description of flame dynamics, a general equation governing propagation of disturbances of an anchored flame is obtained. This equation is solved analytically for V-flames in high-velocity channel streams. It is demonstrated that dynamics of flame disturbances in this case is controlled by the memory effects associated with vorticity generated by the curved front. The perturbation growth rate spectrum is determined, and explicit analytic expressions for the eigenfunctions are given. It is found that the piecewise linear V-structure is unstable for all values of the gas expansion coefficient.

###### pacs:

47.20.-k, 47.32.-y, 82.33.Vx## I Introduction

Among the various types of premixed flame propagation problems, anchored flames hold a special place. On the one hand, such flames are relatively easy to realize experimentally; on the other, they look simple enough for theoretical investigation, because they admit several important simplifications. For instance, open flames anchored by means of a thin rod are often observed to have rectilinear wings (unconfined V-flames). Homogeneity of the upstream flow, adopted usually as the natural approximation compatible with this piecewise linear flame-front structure, often conveys the impression that the problem is easily solvable analytically. It thus represents an excellent laboratory for testing our understanding of premixed flame dynamics.

Despite these promising circumstances there is an apparent lack of theoretical results on V-flame properties. The reason is that these flames are not as simple as they seem. A closer inspection of the flow structure of the idealized V-configuration reveals that this pattern is singular: the pressure field turns out to diverge logarithmically near the tip of the flame-front (and also at infinity along the front, in the case of unconfined V-flames). This is a sign of incompleteness of the idealized picture, which means that the system anchoring the flame must be explicitly included into consideration. This essential complication necessitates the introduction of a specific inner scale in the problem (in addition to the cutoff wavelength and the channel width), thereby raising the question as to the influence of this new scale on the whole basic pattern. The initial problem is thus naturally divided into two parts: 1) modeling of the anchoring system; this primarily is a stationary analysis, aimed at inferring properties of the system needed to generate a presumed flame pattern, and 2) investigation of the flame dynamics, which first and foremost is a stability analysis of the anchored flame; an important issue in this analysis is its model-dependence, i.e., the extent to which its results depend on particularities of the anchoring system.

The purpose of the present paper is to carry out an analysis of the above-mentioned issues, in the case of a confined V-flame anchored in a high-velocity gas stream. It will be shown that the problem admits a full theoretical investigation in this important particular case, and that its results are model-independent in the above sense. It should be mentioned that in contrast to unconfined anchored flames, flames anchored in channels do not exhibit an acute linear structure, although the piecewise linear front with a uniform upstream flow is still a solution of the governing equations. Experiments show that deviations from linearity occur not only in the small regions near the anchor and the channel walls, but all along the front (Scurlock, 1948; pro, 1949; Zel’dovich et al., 1985). This suggests that the simplest configuration is possibly unstable in the confined case. The results of our work fully confirm this conjecture.

In our investigation, we use the on-shell description of flames developed in Refs. (Kazakov, 2005a, b; El-Rabii et al., 2008; Joulin et al., 2008). The integro-differential equations derived therein provide a non-perturbative description of spontaneous flame dynamics in the most general form, i.e., they apply to flames with arbitrary gas expansion and arbitrary jump conditions across the flame front. The main advantage of using these equations is that they are closed, in the sense that they involve only quantities defined at the flame front. This allows one to avoid explicit solving of the flow equations in the bulk, which is the stumbling block of conventional analysis. This approach will be shown to be extendable to the case of anchored flames in a simple and natural way.

The paper is organized as follows. Section II serves to set up the general framework of the on-shell flame description. In Sec. II.1, we formulate the problem and recall the main results of Refs. (Kazakov, 2005a, b; El-Rabii et al., 2008; Joulin et al., 2008). Extension of these results to the case of anchored flames is described in Sec. II.2. An analysis of the anchoring system impact on the flame structure, carried out in Sec. II.3, is used in Sec. II.4.1 to identify boundary conditions for the linearized equation describing the propagation of disturbances. This equation is derived, in a form suitable for the subsequent analysis, in Sec. II.4, then solved in Sec. III. An important step here is the evaluation of rotational contribution, presented in Sec. III.1. The resulting equation is analyzed in the high-velocity limit in Sec. III.2, which allows considerable simplifications. In particular, an asymptotic expansion of the main integral operator is constructed in Sec. III.2.1. Finally, analytic solutions of the linearized problem are found in Sec. III.3, and studied in detail in Sec. III.4. Section IV contains concluding remarks and prospects for future work. The paper has two appendices, one of which contains a consistency check for the calculations performed, and the other describes in detail transition to the case of vanishingly small anchor dimensions within the large-slope expansion.

## Ii Preliminaries

### ii.1 Spontaneous flame dynamics on-shell

Consider a 2D-flame propagating in a channel of constant width
filled with an initially quiescent uniform ideal gas. Let
the Cartesian coordinates be chosen so that the channel
walls are at and is in the fresh gas. These
coordinates will be measured in units of the channel
width^{1}^{1}1However, we keep track of throughout
Sec. II., while fluid velocity, in
units of the velocity of a plane flame front relative to the fresh
gas, Finally, the fluid density will be normalized by the
fresh gas density, denoting its ratio to that of burnt
gas. We assume that the flame pattern is continued to the whole
-axis in the usual way using the ideal boundary conditions at the
channel walls:

(1) |

Then the on-shell value, , of fresh-gas velocity (i.e., its value at the flame front considered as a gasdynamic discontinuity), and the flame front position, satisfy the following complex integro-differential equation (El-Rabii et al., 2008; Joulin et al., 2008)

(2) |

where is the complex gas velocity, its jump across the flame front, and the prime denotes differentiation with respect to (in the last term on the left, the argument is understood to be set equal to after partial spatial differentiation, but before the -differentiation denoted by the prime; we recall that the improper -integral in this term is understood as an analytic continuation of the corresponding regularized expression, see Ref. (Joulin et al., 2008) for details). The memory kernel has the form where is the normal burnt gas velocity relative to the flame front, denoting the unit vector normal to the front ( points towards the burnt gas), and is the on-shell value of vorticity produced by the curved front. The memory kernel is integrated over any path in the complex time-plane, connecting the points

where

is the on-shell burnt gas velocity relative to the front, and is the radius-vector drawn from the point at the front to the observation point Finally, the action of the operator on an arbitrary function is defined by

(3) |

where the slash denotes the principal value of the integral. For a -periodic function [i.e., ], summing explicitly the integrand with the help of the formula

the right hand side of (3) can be rewritten as an integral over the channel width

(4) |

We recall also that the value of vorticity at the front and the normal velocity of the burnt gas, entering the function as well as the velocity jumps at the front, are all known functionals of on-shell fresh gas velocity (Matalon and Matkowsky, 1982; Pelce and Clavin, 1982). For zero-thickness flame fronts one has

(5) | |||||

(6) |

where

Together with the evolution equation

(7) |

the complex Eq. (2) constitutes a closed system of three equations for the three functions and

### ii.2 On-shell description of anchored flames

As derived, Eq. (2) describes only spontaneous flame evolutions. However, the anchoring system is not difficult to incorporate into the framework of the on-shell description. This can be done as follows. Consider the simplest and most commonly used in practice type of the anchoring system – a metal rod placed somewhere within the channel. From the mathematical point of view, the presence of the rod can be described as a singularity of the complex velocity, considered as an analytical function of the complex variable Namely, suppose that the original field, is superimposed with the complex velocity, describing a dipole located at the point :

(8) |

where and is a complex constant determining strength of the dipole as well as its orientation. For sufficiently small perturbation of the main flow is noticeable only in a small vicinity of the dipole. Since is analytical at one has

and hence, the complex velocity near the dipole can be written approximately as

(9) |

The form of the stream lines is given by

or

where are the real and imaginary parts of It is seen that if we choose with arbitrary real, then the stream-line family contains a circle of radius centered at the point Thus, adding the term to the velocity field describes perturbation of the given flow by a cylindrical rod of radius centered at To take into account non-uniformity of the main flow near the rod, and to describe more general rod profiles, it will be necessary to superpose several dipoles located within the rod area, and to include higher-order multipoles into consideration.

To obtain generalization of Eq. (2) to the case of anchored flames, we recall that this equation is a consequence of the following relations:

(10) | |||

(11) | |||

(12) | |||

(13) |

where denotes the jump of the complex velocity across the flame front, Equations (10), (11) express analyticity and boundedness of the complex velocity upstream, and its potential component downstream (Kazakov, 2005a, b), Eq. (12) is the on-shell expression of the rotational component (Joulin et al., 2008), while Eq. (13) is an obvious identity. As we have just seen, the presence of the rod violates analyticity of the complex velocity, so that either of Eqs. (10), (11) is no longer valid, depending on whether the rod is placed up- or downstream. In the former case, Eq. (10) is satisfied by because it is analytical upstream and bounded. On the other hand, since does not have singularities downstream and is bounded there, it satisfies Eq. (11). Thus,

Since we see that Eq. (10) is replaced in this case by

(14) |

Accordingly, acting on Eq. (13) by the operator we obtain the following equation

(15) |

which is the sought extension of Eq. (2) to the case of anchored flames. In the case of the rod located downstream, similar considerations show that Eq. (11) must be replaced by the following

(16) |

It is not difficult to verify that the resulting equation for in this case has exactly the same form (15).

### ii.3 Influence of anchoring system on V-flame structure

As was mentioned in introduction, the necessity of explicit inclusion of the anchoring system into consideration raises the question as to what extent this system affects global properties of V-flames. Let us now show that as long as linear dimensions of the rod are small compared to the channel width, so that the flame front can be considered piecewise linear, influence of the rod on the flame structure is local, in the sense that it is confined to a small region near the rod. We recall, first of all, that the relative value of the velocity disturbance caused by a dipole modeling the rod is proportional to (for simplicity, the dipole is assumed to be at the origin). Hence, under the assumption this disturbance is indeed negligible for the most part of the channel, except a small region near the rod. This simple reasoning is not yet sufficient to prove our statement, because it only demonstrates the locality of, so to speak, direct rod influence on the flow structure. In such an essentially nonlocal problem as deflagration, we also have to look for possible indirect consequences of this influence, related to the fact that the presence of the rod ultimately determines the basic flame pattern. The on-shell description is particularly convenient for this purpose, as it explicitly reveals the nonlocal structure of the governing equations.

For the rest of the paper, flames will be considered in the reference frame attached to the rod (the above-given formulation is invariant under transitions between different reference frames). Accordingly, the fresh-gas velocity at infinity will be denoted :

We will assume in what follows that the anchoring system is stationary, i.e., its properties do not change with time. This means that these properties can be inferred from the steady-state V-flame structure. To this end, we note that the stationary version of Eq. (15) reads (here we are in the rest frame of the flame-front, so the over-bar in the notation of velocity is omitted)

(17) |

which follows directly from the fact that Eq. (2) reduces in this case to the stationary equation derived in (Kazakov, 2005a, b). In regions where the flame-front slope is constant and the upstream flow is homogeneous, the first term on the left as well as the expression in the curly brackets vanish, because velocity jumps are constant there, and vorticity is not produced. This expression is only non-zero in a vicinity of the rod where all the quantities involved vary rapidly. It is this rapid variation that is a possible source of indirect influence of the rod on the global flame structure. Indeed, for both terms in the curly brackets have a -functional character. If the -singularity were not canceled in their sum, then upon the action of the -operator it would give rise to an expression which is non-zero everywhere in the channel. However, we have just seen that the right hand side of Eq. (17) vanishes outside of small region around the rod. Therefore, in order that this equation be satisfied, the -contributions must cancel. To be more specific, let us assume that the rod is located downstream (which is normally the case in actual experiments), as shown in Fig. 1. Then, using Eqs. (10), (16), and the identity Eq. (17) can be conveniently rewritten as

(18) |

There are two types of -like contributions on the left hand side of this equation, corresponding to the real and imaginary parts of the expression in the curly brackets. Since the real part is even under its -derivative is odd. Hence, the corresponding singularity is generally proportional to and can be compensated by appropriately choosing the coefficient in the dipole term on the right hand side. Indeed, the on-shell value of a dipole considered in the limit possesses all characteristic properties of the -function: for and the integral taken over a region around has a finite value (because is an even function).

Things are different, however, for the imaginary part which is odd
in In this case, the singularity is proportional to
for zero-thickness flames, for instance, contribution
of the first term in the curly brackets to the singularity is equal
to where is the value
of the front slope far from as is seen from
Eq. (5). Singularities of this kind^{2}^{2}2In fact, it is
the singularities with undifferentiated
-functions, which are only important. Indeed, on dimensional
grounds, a differentiated should be accompanied by an extra
factor with the dimension of length; since this an “inner”
contribution, the factor is and hence the
-terms can be neglected in comparison with
in the limit Another way to see this is to recall that the
parameter in the dipole is
while the strength of the dipole modeling the rod,
as we saw in Sec. II.2. Hence, must be
accompanied by a factor cannot be compensated by any local
field Thus, we arrive at the conclusion that the
assumption of piecewise linear front structure implies the absence
of terms proportional to on the left hand side of
Eq. (18), i.e., that the contribution of the
first term in the curly brackets is canceled by that of the second
term. This requirement can be written in the following integral form

(19) |

where : is the length scale where “inner” solutions () are to be matched with the “outer” ones (). Indeed, by virtue of Eq. (19), the contribution of the small region near the rod to the left hand side of Eq. (18) is also small outside that region, which is just the required absence of the -terms. Equation (19) thus represents a condition that selects inner solutions compatible with the prescribed global flame structure.

### ii.4 Linearized equation for flame perturbations

In the present paper, we for are looking for possible genuine V-flame instabilities, which would be inherent to the V-configuration itself, and unrelated to the properties of a specific anchoring system. We thus assume, as was already mentioned, that this system is stationary, and the condition (19) is fulfilled. Then the equation for flame perturbation is obtained by linearizing Eq. (15) around the stationary solution, with the right hand side kept fixed. This linearized equation thus coincides formally with that derived in Ref. (El-Rabii et al., 2008; Joulin et al., 2008), but for our present purposes another form of this equation will be more appropriate, which avoids explicit differentiation of the memory kernel.

First of all, since the basic pattern is stationary, time-dependence of perturbations factorizes:

(20) |

where is a complex constant to be found as part of the solution. Not to mix the imaginary unit entering with that appearing in Eq. (15), we will denote the former by :

where are real numbers. Accordingly, the amplitudes are to be understood complex with respect to (until Sec. III.4, will not appear in formulas explicitly; an example illustrating the use of this “double imaginary unit” formalism is given in Appendix A). Next, taking into account that the basic solution is piecewise constant, we obtain the following equation for the -dependent parts of the perturbations

(21) |

where is the differential operator obtained by linearizing the function around the stationary solution, and setting afterwards; is the angle between the vectors defined positive if the rotation from to is clockwise, and is the sign function,

In the form written, Eq. (21) applies to flames with arbitrary jump conditions at the front and arbitrary local propagation law. However, to investigate the problem as stated in the beginning of this paragraph, we do not need to remain at such a general level. As mentioned earlier, we are concerned with instabilities specific to the presumed V-pattern, so the characteristic perturbation wavelength of interest is of the order of the channel width which is normally much larger than the cutoff wavelength. Hence, the curvature effects can be completely neglected in our investigation, and the consideration be limited to the case of zero-thickness flames. Then the linearized velocity jumps, appearing in Eq. (21), take the form

(22) |

To linearize the memory kernel, another form of the expression (6) will be more suitable, which avoids appearance of the second spatial derivatives of the flame-front position. The point is that linearizing Eq. (6) directly is readily seen to lead to expressions of the type which are not well-defined in the sense of distributions. To resolve this ambiguity, we first rewrite Eq. (7) as

differentiate it with respect to and use the resulting equation to eliminate from the right hand side of Eq. (6). The memory kernel thus becomes

(23) |

The right hand side of this expression now involves only first derivatives of continuous functions. It should be emphasized that this trick works only in the outer region where effects due to the finite flame-front thickness are negligible. If they are not, appears already in the undifferentiated evolution equation. Linearization of Eq. (23) yields

(24) |

Finally, the linearized evolution equation reads

(25) |

#### ii.4.1 Boundary conditions

We consider symmetrical basic V-patterns, so that the flame-anchoring rod is located in the middle of the channel. For simplicity, flame disturbances also will be assumed symmetrical under reflection with respect to the -axis. In these circumstances, it is convenient, without changing notation, to consider a double-width channel occupying the strip with the rod being at the origin and the -axis playing the role of the symmetry plane of the flame. Accordingly, boundary conditions of the exact problem, i.e., the problem we started with, read for They are used, in particular, for the periodic continuation of the flame pattern, mentioned in Sec. II.1. After the initial problem is divided into the inner and outer ones, these conditions naturally remain pertaining to the former. A question thus arises as to the boundary conditions relevant to the outer problem.

Evidently, the requirement of a vanishing front slope at the walls is now irrelevant. Indeed, it is not satisfied already by the basic steady V-configuration defined to have the constant slope, everywhere. The front flattening takes place in a thin boundary layer near the walls, characterized by large values of On the other hand, the -derivative of the -component does not have to be large in this region, as can be seen from the fact that the condition being the universal boundary condition for the ideal fluid, is compatible with any prescribed front configuration. Indeed, the linearized Euler equations for the fresh-gas read

(26) | |||||

(27) |

where it is taken into account that for the steady-state V-flame, Using the continuity equation in Eq. (27), multiplying it by subtracting from Eq. (26), and going over on shell one obtains an equation for :

or

(28) |

where is the front length counted off from the channel wall, and is, as usual, the unit vector normal to the front. As was already mentioned, the front flattens in a thin boundary layer near the walls. From the standpoint of the outer problem we are concerned with, a finite change of an on-shell variable across the layer is seen as a finite jump of that quantity at the channel wall. Accordingly, its derivative with respect to contains a term proportional to Now suppose that this is the case for Then it follows from Eq. (28) that

where is a constant, and “” denote regular terms. Since the velocity jump is finite, this means that

This relation can be integrated by noting that differentiation of pressure in the direction normal to the front cannot produce a -singularity along the front, and hence,

where is such that But pressure is only allowed to have a finite jump at the wall, therefore, must vanish upstream. Meanwhile, in the absence of obstacles at the wall, the outer solution is regular on-shell, and hence the function is differentiable not only in the near upstream region (as required by its definition), but also at the flame front. Under such circumstances, the requirement upstream entails vanishing of its derivative at the front, i.e., Thus, is in fact continuous at the wall, so its vanishing remains a boundary condition of the outer problem: or

(29) |

The reasoning just given does not apply at because of the presence of the rod. Nevertheless, must also vanish, as a consequence of our assumption that the anchoring system is stationary. To see this, let us consider the procedure of matching the inner and outer solutions in more detail. Take the -component of the fresh-gas velocity. For gas elements moving near the -axis, this component is zero everywhere except a small vicinity of the rod. More precisely, induced by the rod is for and rapidly decreases with distance. At distances where the inner solution describing the flow near the rod is matched with the outer solution we are interested in. In the steady case, matching at the flame front assigns a definite value, say which is generally nonzero. This value plays the role of a boundary condition for the steady flow, defining thereby the basic pattern. Now, since the properties of the rod are assumed stationary, in particular, unaffected by perturbations of the outer solution, so is the flow near the rod. Therefore, matching of the inner solution with the outer one will give the same value In other words, which in the limit yields

(30) |

By the same reasoning,

(31) |

Finally, the remaining condition replacing is

(32) |

It follows directly from the fact that we consider the rod dimension as vanishingly small compared to the channel width. Indeed, the linear dimension of the flame tip as well as its separation from the rod are both Hence, which in the limit gives Eq. (32). This condition means that the flame is not torn off from the rod by the perturbation.

## Iii On-shell dynamics of V-flame perturbations

### iii.1 Evaluation of the rotational contribution

In order to study evolution of the V-flame disturbances using Eq. (21), we have to evaluate the improper -integral appearing in the curly brackets. We recall that this integral is understood as an analytic continuation of the regularized integral

(33) |

to the limit To simplify the calculation, we note that

Indeed, one has while according to the definition of the angle it is equal to the phase difference of the complex functions and We need to consider two different situations corresponding to the integration variable running over the negative- or positive-slope part of the flame front (see Fig. 2). Assuming that the observation point one has, in the case

where Similarly, in the case

where In effect, the exponent in the integrand of (33) takes the form

where

Furthermore, the regularizing factor may be replaced by because is finite. Next, the -integral taken over can be represented as an integral over of the integrand summed over all Since the functions are periodic by construction, we need to sum the following series

where

Taking into account that one has

(34) | |||||

Since the initial improper -integral is reduced to an integral over a finite domain, its analytic continuation to amounts to that of the function which is

All these formulas were derived for From these, the corresponding expressions for can readily be obtained by noting that the integral (33) is invariant under the combined operations of inversion and complex conjugation. This rule can be deduced directly from the explicit formulas (22), (24), taking the various parity properties of the flow variables into account, yet it is in fact a general property of the formalism, unrelated to the specific approximations made. In what follows, we will denote this combined operation as It should be kept in mind that the complex conjugation here is understood with respect to the imaginary unit but not to :

Putting all these results into Eq. (21), we thus arrive at the following linearized equation governing evolution of the flame disturbances

(35) |

where the symbol refers to the whole expression written out explicitly in the curly brackets. As a useful check of the calculations performed, it is verified in Appendix A that in the particular case this equation reproduces the well-known Darrieus-Landau dispersion relation (Darrieus, 1938; Landau, 1944) for the perturbation growth rate.

### iii.2 The high-velocity limit

In its general form, Eq. (III.1) can presumably be solved only numerically. It turns out, however, that it is amenable to a full theoretical analysis in the case when the velocity of the incoming fresh-gas flow is high:

Being opposite to that of classical analysis (Darrieus, 1938; Landau, 1944; Sivashinsky, 1977; Sivashinsky and Clavin, 1987), this limit is of considerable interest both from practical and theoretical points of view, as it represents the situation where propagation of the flame disturbances is strongly affected by the basic flow. We will see that the nonlocal interaction of flame perturbations with the background takes a new form which is principally different from that encountered in the conventional weak-nonlinearity analysis. Also, dependence of solutions on the gas expansion coefficient becomes quite intricate, having nothing in common with that found in the small-gas-expansion approximation.

#### iii.2.1 Large- expansion of the -operator

We start discussion of the high-velocity limit by deriving an approximate expression for the -operator appearing in Eq. (III.1). There, it is defined at the unperturbed front,

(36) |

By virtue of the relation

large values of imply that the front slope is also large, so the argument of cotangent in Eq. (36) has a large imaginary part for almost all values of the integration variable, in which case one has

(37) |

This approximation is valid for all except two small regions near More precisely, taking into account that, for real

we see that Eq. (37) holds true, with an exponential accuracy, everywhere except

where

To develop an asymptotic expansion of in powers of for let us choose a real satisfying

(38) |

Then the integral in Eq. (36) can be rewritten as

(39) |

where we assumed that for definiteness. Notice that in the last term on the right hand side of Eq. (III.2.1), only one of the two integrals is defined in the principal value sense. As such, it is proportional to the derivative of It is not difficult to verify that contributions of this kind give rise to terms of the order Below, we will need expanded up to -terms, so the principal-sense integral can be neglected. The other integral can be evaluated as follows, within this accuracy,

(40) |

By virtue of the conditions (38), the -integral can be calculated, with exponential accuracy, using the contour deformation shown in Fig. 3

On the other hand, replacing cotangent by the sign function gives zero within the same accuracy

Using these results in Eq. (III.2.1), and then substituting it in Eq. (36) gives finally

(41) |

where the symmetry of the operator under was taken into account to dismiss the condition As a special case of this formula, let us consider the action of on a derivative. If satisfies then integrating by parts in Eq. (41) readily gives

(42) |

where the prime now denotes the derivative of the function with respect to its argument, It turns out that this formula holds true even if the function does not satisfy the above conditions of periodicity and continuity at the origin. This is proved in Appendix B.

To conclude this section, some comments concerning the structure of the expression (41) are in order. First of all, it is seen that the result of the action of depends essentially on parity properties of the function namely, if is even, and if it is odd. Next, the appearance of a term proportional to encodes a peculiar interaction between the points and which is natural taking into account that the front wings get close to each other in the limit Finally, it should be noted that although the identity is valid whatever the shape of the flame-front, in particular, in the large- limit, it cannot be verified using the expression on the right of Eq. (41), already because of the composition of its leading term with the undetermined remainder

#### iii.2.2 Equation for the -component of velocity. Relative order of the flow perturbations

The results of the previous section allow us to a obtain a simple relation between components of the perturbed on-shell velocity. We use the following equation

(43) |

which is obtained acting by on Eq. (III.1), and using the identity ; it can be derived also directly by linearizing Eq. (10). Applying the formula (42) yields

(44) |

We see that the boundary condition (29) is met explicitly, while setting and using (30) leads to a new condition

(45) |

It will be shown in the next section that this condition is also satisfied automatically by the solutions of Eq. (III.1).

Next, we use Eq. (44) to determine the relative order of the flow perturbations within the large- expansion. It is convenient to assume that It follows then from Eq. (44) that while using these in the linearized evolution equation (25) tells us that Applying these estimates to Eq. (III.1) shows immediately that the term in the curly brackets can be omitted. Since the -integral is explicitly continuous at so is the expression in the curly brackets, as was to be shown.

In connection with this result, it is worth mentioning that the term represents the linearized velocity jumps which define the Frankel potential-flow equation (Frankel, 1990). That this contribution is negligible means the evolution of disturbances in the case under consideration is essentially rotational, and cannot be described within the potential-flow model.

### iii.3 Analytical solution of the linearized equation in the high-velocity limit

We are now in position to proceed to analytical solving of Eq. (III.1) in the case of high stream-velocity. Although the following calculation is a straightforward application of the formulas derived in the preceding section, it is somewhat lengthy. We give it in considerable detail because some of its points are definitely worth to be mentioned.

#### iii.3.1 Derivation of the integro-differential equation

To begin with, it is convenient to rewrite Eq. (III.1) as

(46) | |||||

(47) | |||||

The order of the leading contribution to the left hand side of Eq. (46) can be read off from its first term, According to the estimates of the previous section, it is and is contained in the real part of the equation. To extract the relevant contribution from the integral term, we recall that the action of on odd and even functions gives rise to terms of the order and respectively. Furthermore, taking into account that and hence one sees that Therefore, according to the naive power counting the integral term is formally However, there is actually no discrepancy in the orders of the two terms, because the -contribution to turns out to be imaginary even, and thus cancels with its counterpart from Yet, the formal estimate means that expanding imaginary part of one must generally keep terms up to the second relative order in With this in mind, we write

(48) |

and then

(49) | |||||

On the other hand, since in the factor all terms are real, it can be replaced by with no risk of mixing orders. Similarly, one can replace by because the imaginary correction is Also, before expanding, it is convenient to integrate by parts the term proportional to Taking into account the boundary condition (31), we thus find