CN111651897A - Large-size gap microstructure capable of inhibiting transition of hypersonic velocity boundary layer - Google Patents

Large-size gap microstructure capable of inhibiting transition of hypersonic velocity boundary layer Download PDF

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CN111651897A
CN111651897A CN202010560615.5A CN202010560615A CN111651897A CN 111651897 A CN111651897 A CN 111651897A CN 202010560615 A CN202010560615 A CN 202010560615A CN 111651897 A CN111651897 A CN 111651897A
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reflection
gap
angle
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CN111651897B (en
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赵瑞
董颖
张新昕
涂国华
郭启龙
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Beijing Institute of Technology BIT
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Abstract

The invention relates to a large-size gap microstructure capable of inhibiting transition of a hypersonic velocity boundary layer, and belongs to the field of aerospace. According to the invention, by establishing the relation between the hole depth and the disturbance wave reflection angle, the disturbance wave reflection direction can be manually controlled, and the traditional reflection rule is broken through. The gap s of the large-size gap microstructure is enlarged to be equal to the wavelength of the disturbance wave; the gap structure for restraining the transition of the hypersonic velocity boundary layer limits the gap s to be far smaller than the wavelength of the disturbance wave, and the expansion of the gap s enables the material to be easier to process in actual engineering. The invention can effectively inhibit the development of the Mack second mode in the wall surface boundary layer, thereby effectively inhibiting transition and expanding the laminar flow coverage area. The large-size gap microstructure is applied to the surface skin of the hypersonic aircraft, transition can be effectively inhibited, and the purposes of thermal protection and resistance reduction are finally achieved.

Description

Large-size gap microstructure capable of inhibiting transition of hypersonic velocity boundary layer
Technical Field
The invention relates to a large-size gap microstructure capable of inhibiting transition of a hypersonic velocity boundary layer, in particular to an optimal design method of a controllable reflection direction type large-size micro-gap structure capable of inhibiting unstable waves of a Mack second mode in the boundary layer, and belongs to the field of aerospace.
Background
The hypersonic aerocraft has the characteristics of global quick achievement, high detection difficulty, strong penetration capability, high combat efficiency and the like, and becomes one of the main focuses of international competition. The major reasons for the frustration of hypersonic aircraft in the development process, such as failure of two flight experiments in the U.S. HTV-2 project, failure of first flight of HIFIRE-5 jointly implemented in the U.S. and Australia, etc., are that hypersonic technology exists in a plurality of unknown fields, and transition of a boundary layer is an important and inevitable uncertain factor. The hypersonic aircraft is very easy to have boundary layer transition within the range of the flight altitude, the speed and the Reynolds number, and the friction resistance and the heat flow after transition can be increased by 3-5 times generally, thus seriously affecting the aerodynamic performance and the thermal protection system. Therefore, the hypersonic aircraft has urgent need for effectively inhibiting transition, and is a research hotspot in the hypersonic field at home and abroad at present.
The research on transition suppression of the hypersonic aircraft mainly focuses on how to effectively suppress the development of the second mode of the Mack in the boundary layer. The porous covering layer can effectively inhibit the development of the second mode through the design of the acoustic characteristics of the porous covering layer on the premise of not obviously influencing the main flow, and is one of the technologies which are most likely to be put into engineering practice. The porous covering layer is formed by processing a series of slits/holes on the wall surface, wherein the slits/holes are far smaller than the wavelength of a disturbance wave. The technology has been proved to be capable of remarkably delaying transition in high-speed wind tunnel experiments.
At present, two types of porous covering layers exist, one type is an acoustic absorption type porous covering layer, and the energy of disturbance waves is dissipated and absorbed through the viscosity in pores, so that the aim of inhibiting the development of a Mack second mode is fulfilled. The other type is an impedance type porous covering layer, when the impedance of the incident medium is smaller than the impedance of the space medium, the sound pressure of the reflected wave is equal in amplitude and opposite in phase to the sound pressure of the incident wave, and the pressure pulsation at the wall surface is in a mutually cancelled state. Both types of porous covers are uniformly porous, i.e. all pores have the same shape parameter, and the development of the second mode of Mack is suppressed by the sound absorption or impedance properties of the pores. The existing porous covering layer needs to limit the aperture and the distance between adjacent pores within a range far smaller than the wavelength of a disturbance wave, if the aperture or the distance between adjacent pores is larger than or equal to the wavelength, other unstable modes can be caused due to the resonance between pores, and the occurrence of transition is promoted, so that the material is not easy to process.
Disclosure of Invention
The invention aims to solve the problem that the existing porous covering layer is difficult to process due to the limitation of the size of a pore structure, and the invention discloses a large-size gap microstructure capable of inhibiting the transition of a hypersonic velocity boundary layer, which aims to solve the technical problems that: the characteristic that the reflection direction of sound waves can be controlled by utilizing the porous covering layer is utilized to inhibit the transition of the hypersonic velocity boundary layer, and the large-size gap microstructure can break through the size limitation on the aperture and the space between adjacent holes.
The purpose of the invention is realized by the following technical scheme.
The invention discloses a large-size gap microstructure capable of inhibiting transition of a hypersonic velocity boundary layer, which comprises the following steps:
step one, defining a shape parameter and an incident wave parameter of a slit structure.
The large-size gap microstructure capable of inhibiting transition of the hypersonic velocity boundary layer is composed of a plurality of spanwise gap groups which are periodically and regularly distributed on an xz plane, and each gap group is composed of N gaps (N is>1) Defining N as the number of periodic gaps, the side length of a single gap as 2b, and the hole depth as Ha(a is 1 to N) and the distance between adjacent slits is s. Defining the hole depth direction as a y direction, and defining a material surface plane vertical to the hole depth direction as an xz plane; the flow direction is defined as the x-direction and the span direction as the z-direction.The dimensionless geometric parameter porosity phi is expressed by the parameter phi of 2b/s, and the dimensionless geometric parameter aspect ratio Ar is expressed by the parameter Ar of 2 b/H. The incident wave frequency is f and the incident wave wavelength is lambda.
And secondly, determining the relation between the reflection angle and the shape parameters and incident wave parameters of the slit structure.
The generalized snell's law expression is:
Figure BDA0002545943470000021
wherein the wave number k of incident wave0＝2π/λ，θrTo angle of reflection, θiFor the incident angle, Φ (x) is the reflected wave phase angle, and the reflected wave phase angle expression is obtained by integrating equation (1):
Figure BDA0002545943470000022
when the phase angle of the reflected wave changes in the linear law of equation (2) along the flow direction x, the reflected wave is made to be thetarThe reflection angle of (a) is reflected, so the gap spacing s should satisfy:
Figure BDA0002545943470000023
substituting the wavelength λ ═ c/f, where c is the speed of sound, into equation (3) yields:
Figure BDA0002545943470000024
finally, a relational expression of the reflection angle, the incident wave frequency f, the gap distance s and the number N of the periodic gaps is obtained:
Figure BDA0002545943470000025
when the incident wave frequency and the slit pitch are determined, the relation between the reflection angle and the number N of periodic slits is obtained, and therefore the reflection angle of the target can be obtained by changing the value of N.
Step three: and determining the relation between the phase angle of the reflected wave and the depth of the slit hole.
The reflection coefficient R is the reflection wave pressure/incident wave pressure, and the specific expression of the reflection coefficient R is as follows:
Figure BDA0002545943470000031
wherein
Figure BDA0002545943470000032
khIs the wave number in the hole, ρ is the incoming flow density, ρhThe reflection coefficient × is obtained from the reflection wave pressure, i.e., the incident wave pressure, and when the phase of the incident wave is 0, the phase angle of the reflection wave is equal to the phase angle of the reflection coefficient, which is obtained from equation (6), and the phase angle of the reflection coefficient R is the hole depth HaA function of the gap s and the porosity phi. And (3) determining the relation between the reflection angle and the number N of the periodic gaps according to the formula (6) and the formula (5) in the step two, and enabling the phase angle of the reflected wave to change according to the rule in the step two through the combination of the gaps with different depths, so that the disturbance wave is reflected at the target reflection angle.
Step four: and (4) applying the large-size gap microstructure which is obtained by optimization in the third step and can control the reflection direction of the disturbance wave to the field of hypersonic flight vehicles so as to delay the transition of a hypersonic boundary layer and improve the aerodynamic performance and the thermal protection performance of the hypersonic flight vehicles.
Has the advantages that:
1. the large-size gap microstructure capable of inhibiting transition of the hypersonic velocity boundary layer disclosed by the invention has the advantages that the disturbing wave reflection direction can be artificially controlled by establishing the relation between the hole depth and the disturbing wave reflection angle, and the conventional reflection rule that the reflection angle is equal to the incident angle is broken through.
2. The large-size gap microstructure capable of inhibiting transition of the hypersonic velocity boundary layer disclosed by the invention enables the gap s of the large-size gap to be enlarged to be equal to the wavelength of a disturbance wave; the gap structure for restraining the transition of the hypersonic velocity boundary layer limits the gap s to be far smaller than the wavelength of the disturbance wave, and the expansion of the gap s enables the material to be easier to process in actual engineering.
3. Compared with the traditional porous covering layer structure, the large-size gap microstructure capable of inhibiting the transition of the hypersonic velocity boundary layer disclosed by the invention can effectively inhibit the development of the Mack second mode in the wall surface boundary layer, further effectively inhibit the transition and expand a laminar flow covering region. The porous covering layer with the large-size gap microstructure is applied to the surface skin of the hypersonic aircraft, transition can be effectively inhibited, and the purposes of thermal protection and resistance reduction are finally achieved.
Drawings
FIG. 1 is a flow chart of the present invention;
fig. 2 is a physical model diagram of a large-sized slit microstructure capable of inhibiting transition of a hypersonic velocity boundary layer, wherein: (a) overall structure, (b) partial enlarged view;
FIG. 3 is θi＝0，θrA curve graph of the relation between the phase of the reflected wave and the depth of the hole when the angle is 90 degrees;
FIG. 4 is a graph of reflected wave phase angle versus hole depth for a slot structure;
FIG. 5 is a cloud graph of the distribution of the pulsating pressure amplitude of a reflected sound field;
fig. 6 is a graph comparing the pulsating pressure amplitude of the flow field of a flat plate, wherein: (a) the structure designed by the patent, (b) a uniform pore structure;
FIG. 7 is a graph of the amplitude of the pulsating pressure at the flat wall, where: (a) wall pulsating pressure: x is 0 to 1, and (b) wall pulsating pressure: x is 0.6-1;
FIG. 8 is a graph of the maximum pulse pressure amplitude at the flat plate wall, where: (a) maximum pulsating pressure of wall surface: x is 0 to 1, and (b) wall maximum pulsating pressure: x is 0.6 to 1.
Detailed Description
For a better understanding of the objects and advantages of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
Example 1:
this example discloses example 1:
as shown in fig. 1, the large-sized gap microstructure capable of inhibiting transition of the hypersonic velocity boundary layer disclosed in this embodiment includes the following specific implementation steps:
the method comprises the following steps: and defining the shape parameter and incident wave parameter of the slit structure.
The large-size gap microstructure capable of inhibiting transition of the hypersonic velocity boundary layer as shown in fig. 2 is composed of a plurality of spanwise gap groups which are periodically and regularly distributed on an xz plane, and each gap group is composed of N gaps (N is>1) Defining N as the number of periodic gaps, the side length of a single gap as 2b, and the hole depth as Ha(a is 1 to N) and the distance between adjacent slits is s. Defining the hole depth direction as a y direction, and defining a material surface plane vertical to the hole depth direction as an xz plane; the flow direction is defined as the x-direction and the span direction as the z-direction. The dimensionless geometric parameter porosity phi is expressed by the parameter phi of 2b/s, and the dimensionless geometric parameter aspect ratio Ar is expressed by the parameter Ar of 2 b/H. The frequency of the incident wave being taken as f0138.74kHz, the incident wave wavelength is λ02.473e-3 m. Defining a spacing s0＝λ02.473e-3m, the porosity phi is 0.764, and the length b of the gap 1/2 is 9.448e-4 m.
Step two: and determining the relation between the reflection angle and the shape parameters and incident wave parameters of the slit structure.
The generalized snell's law expression is:
Figure BDA0002545943470000041
wherein k is02 pi/lambda, in incident wavenumber, thetarTo angle of reflection, θiFor the incident angle, Φ (x) is the reflected wave phase angle, and the reflected wave phase angle expression is obtained by integrating equation (7):
Figure BDA0002545943470000051
when the phase angle of the reflected wave varies in the flow direction x with the linear law of equation (8), as shown in fig. 3, the reflected wave is made to vary by θrThe reflection angle of (b) is reflected, so the gap s of the slit should satisfy:
Figure BDA0002545943470000052
substituting the wavelength λ c/f, c being the speed of sound, into equation (9) yields:
Figure BDA0002545943470000053
suppose an incident angle θ026 ° and the period s is obtained by step one0＝λ02.473e-3m, yielding:
Figure BDA0002545943470000054
the expression of the reflection angle:
Figure BDA0002545943470000055
selecting different N and calculating to obtain the reflection angle when the frequency of the incident wave is 138.74kHz, obtaining the following table 1, wherein the data in the table can show that the reflection angle is gradually reduced when N is increased, and finally selecting N which is 2 corresponding to the maximum reflection angle through comparative analysis.
TABLE 1 reflection angles corresponding to different N values
N Reflection angle of reflected wave corresponding to 138.74kHz incident
2 θr＝70°
3 θr＝51°
Step three: determining the relation between the phase angle of the reflected wave and the depth of the slot hole
The reflection coefficient R is the reflected wave pressure/incident wave pressure, and the specific expression of the reflection coefficient R is
Figure BDA0002545943470000056
Wherein
Figure BDA0002545943470000057
khIs the wave number in the hole, ρ is the incoming flow density, ρhThe reflection coefficient × is obtained from the reflection wave pressure, i.e., the incident wave pressure, and when the phase of the incident wave is 0, the phase angle of the reflection wave is equal to the phase angle of the reflection coefficient, and as can be seen from equation (13), the phase angle of the reflection coefficient R is the hole depth HaThe functions of the gap s and the porosity phi, the specific values of the gap s and the porosity phi are determined in the step one, the phase angle of the reflection coefficient R is a function of the hole depth H, and the relation curve of the phase angle of the reflection coefficient R and the hole depth H is calculated and obtained and is shown in FIG. 4:
in step two, it is determined that N is 2, so the hole depths corresponding to the phase angles of 180 ° and 360 ° should be selected, and it can be known from fig. 4 that each specific phase angle corresponds to a plurality of hole depths, that is, on the premise of ensuring the phase continuity of the reflected wave, a plurality of sets of hole depth combinations can be selected, and the patent selects the hole depth corresponding to the larger reflection coefficient. The geometric parameters of the selected porous microstructure are shown in table 2. Through the periodic distribution of the gaps with the two hole depths, the reflected wave phase angle can be continuously changed according to the rule shown in figure 3, so that the purpose of controlling the reflection angle theta of the disturbance wave is achievedrThe purpose is 70 °.
TABLE 2 geometric parameters of the gap Structure
Numbering Depth of hole 1/2 wide seam Aspect ratio
Slit
1 0.6712e-3m 9.448e-4m Ar＝2.82
Slit 2 1.340e-3m 9.448e-4m Ar＝1.31
Step four: it was verified that the obtained porous structure changes the reflection direction of the acoustic wave
FIG. 5 is a finite element solver (COMSOL)
Figure BDA0002545943470000061
) And (5) simulating the obtained scattering pressure cloud picture of the reflected sound field. The sound wave is incident at 26 degrees and reflected at a reflection angle thetarReflection angle theta of 72 deg. reflection and obtained by theoretical analysisrThe difference of 70 degrees is not large, the correctness of the theoretical model is verified, and the purpose of changing the reflection direction of the sound wave is achieved.
Step five: and verifying the effect of the controllable reflection direction type large-size gap microstructure on inhibiting the second mode of the Mack.
The large-size gap microstructure material with controllable reflection direction, which is designed according to the geometric parameters in table 1, is mounted on a flat plate with a length L of 1m, wherein the mounting range is from 0.6m to 0.9m, and the material is not mounted on other parts of the flat plate, i.e., the flat plate is a smooth flat plate, and the material is taken as an example of the flat plate flow verification. Assuming a Mach 6.0 hypersonic incoming flow, a flow field pulsating pressure cloud chart of a flat plate is obtained by using direct numerical simulation, as shown in FIG. 6. Comparing fig. 6(a) and fig. 6(b), it can be found that the pulsating pressure amplitude of the model designed in this patent is much smaller than that of the uniform hole model, and the development of the Mack second mode in the wall boundary layer can be effectively inhibited, that is, the occurrence of transition is effectively inhibited. (fig. 6(a) the model designed by the patent is installed in the flat plate x-0.6 m-0.9 m, fig. 6(b) the traditional uniform hole model is installed in the flat plate x-0.6 m-0.9 m, the porosity, period and hole diameter and inflow conditions are the same as those of (a), and the hole depth is 1.340e-3 m).
Fig. 7 shows a pulsating pressure curve at a wall surface (y is 0), and it can be seen that in a region where a gap structure is installed (x is 0.6m to x is 0.9m), the pulsating pressure value of the model proposed by the present patent is much smaller than that of a uniform hole structure, and not only in the region after the gap structure is ended (x is 0.9m to x is 1m), the pulsating pressure value of a flat plate where the uniform hole structure is installed is rapidly increased and is restored to the amplitude of a flat plate where the gap structure is not installed, but also the pulsating pressure value of the model proposed by the present patent is maintained in a relatively stable range and rapid re-rise does not occur. Fig. 8 shows the maximum pulsating pressure curve at the wall (y is 0), and it can be clearly seen that the maximum pulsating pressure value of the proposed model is much smaller than that of the uniform pore structure.
As can be comprehensively judged by fig. 6 to 8, the controllable reflection direction type large-sized slit structure effectively inhibits the development of the Mack second mode in the wall boundary layer, that is, effectively inhibits the occurrence of transition.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims (1)

1. The utility model provides a can restrain jumbo size gap microstructure that hypersonic velocity boundary layer transition is twisted which characterized in that: the implementation method comprises the following steps:
step one, defining a shape parameter and an incident wave parameter of a slit structure;
the large-size gap microstructure capable of inhibiting transition of the hypersonic velocity boundary layer is composed of a plurality of spanwise gap groups which are periodically and regularly distributed on an xz plane, and each gap group is composed of N gaps (N is>1) Defining N as the number of periodic gaps, the side length of a single gap as 2b, and the hole depth as Ha(a is 1 to N), and the distance between adjacent slits is s; defining the hole depth direction as a y direction, and defining a material surface plane vertical to the hole depth direction as an xz plane; defining the flow direction as an x direction and the spread direction as a z direction; the dimensionless geometric parameter porosity phi is expressed as phi 2b/s by the parameter, and the dimensionless geometric parameter width-depth ratio Ar is expressed as Ar 2b/H by the parameter; the frequency of the incident wave is f, and the wavelength of the incident wave is lambda;
determining the relation between the reflection angle and the shape parameters and incident wave parameters of the slit structure;
the generalized snell's law expression is:
Figure FDA0002545943460000011
wherein the wave number k of incident wave0＝2π/λ，θrTo angle of reflection, θiFor the incident angle, Φ (x) is the reflected wave phase angle, and the reflected wave phase angle expression is obtained by integrating equation (1):
Figure FDA0002545943460000012
when the phase angle of the reflected wave changes in the linear law of equation (2) along the flow direction x, the reflected wave is made to be thetarThe reflection angle of (a) is reflected, so the gap spacing s should satisfy:
Figure FDA0002545943460000013
substituting the wavelength λ ═ c/f, where c is the speed of sound, into equation (3) yields:
Figure FDA0002545943460000014
finally, a relational expression of the reflection angle, the incident wave frequency f, the gap distance s and the number N of the periodic gaps is obtained:
Figure FDA0002545943460000015
when the incident wave frequency and the gap distance are determined, the relation between the reflection angle and the number N of the periodic gaps is obtained, so that the reflection angle of the target can be obtained by changing the value of N;
step three: determining the relation between the phase angle of the reflected wave and the depth of the slit hole;
the reflection coefficient R is the reflection wave pressure/incident wave pressure, and the specific expression of the reflection coefficient R is as follows:
Figure FDA0002545943460000021
wherein
Figure FDA0002545943460000022
khIs the wave number in the hole, ρ is the incoming flow density, ρhThe density of the fluid in the hole, the reflection coefficient ×, when the reflection wave pressure is equal to the incident wave pressure, the reflection wave phase angle is equal to the phase angle of the reflection coefficient when the incident wave phase is 0, as shown in equation (6), and the phase angle of the reflection coefficient R is the hole depth HaA function of the gap s and the porosity phi; determining the relation between the reflection angle and the number N of the periodic gaps according to the formula (6) and the formula (5) in the second step, and enabling the phase angle of the reflected wave to change according to the rule in the second step through the combination of the gaps with different depths, so that the disturbance wave is reflected at the target reflection angle;
step four: and (4) applying the large-size gap microstructure which is obtained by optimization in the third step and can control the reflection direction of the disturbance wave to the field of hypersonic flight vehicles so as to delay the transition of a hypersonic boundary layer and improve the aerodynamic performance and the thermal protection performance of the hypersonic flight vehicles.
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CN114476029A (en) * 2022-04-07 2022-05-13 中国空气动力研究与发展中心计算空气动力研究所 Surface structure and hypersonic aircraft attached with same
CN114476029B (en) * 2022-04-07 2022-06-14 中国空气动力研究与发展中心计算空气动力研究所 Surface structure and hypersonic aircraft attached with same
CN115081109A (en) * 2022-05-25 2022-09-20 北京理工大学 Hypersonic velocity boundary layer transition suppression method based on acoustic hypersurface and micro blow-suction
CN115081109B (en) * 2022-05-25 2023-04-11 北京理工大学 Hypersonic velocity boundary layer transition suppression method based on acoustic hypersurface and micro blow-suction
CN115783233A (en) * 2023-02-09 2023-03-14 中国空气动力研究与发展中心计算空气动力研究所 Combined transition control device based on corrugated wall and boundary layer suction
CN115783233B (en) * 2023-02-09 2023-04-21 中国空气动力研究与发展中心计算空气动力研究所 Combined transition control device based on corrugated wall and boundary layer suction

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