CN114441134A - Method for inhibiting Mack mode by adopting steady crossflow vortex - Google Patents
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Abstract
The invention provides a method for inhibiting a Mack mode by adopting a steady cross flow vortex, which comprises the following steps: for the standard mode shape of a cone with a large attack angle of a hypersonic aircraft, a plurality of coarse units are arranged near the front edge of the cone. The method for inhibiting the Mack mode by adopting the constant cross flow vortex is realized by arranging the plurality of rough units near the front edge of the cone, and the method for inhibiting the Mack mode by adopting the constant cross flow vortex is a passive transition delay technology, so that the growth of the Mack mode can be weakened, the transition delay and resistance reduction effects can be realized, and the active energy consumption is not needed.
Description
Technical Field
The invention relates to the technical field of laminar flow control in a hypersonic aircraft, in particular to a method for inhibiting a Mack mode by adopting constant cross flow vortex.
Background
The transition from laminar flow to turbulent flow has great influence on the friction resistance and the thermal load of the hypersonic aircraft. Therefore, it is important to understand the transition phenomenon and mechanism from laminar flow to turbulent flow for aircraft design. A great deal of research is carried out on the stability and transition characteristics of the hypersonic velocity boundary layer, such as flat plate and conical flow, through experiment and theoretical analysis, and clear understanding is obtained. As shown in fig. 1, after the turbulent transition occurs, the friction coefficient of the hypersonic conical surface rises sharply, and the heat flow of the conical surface increases sharply.
For hypersonic aircraft, a cone is a typical nominal mode profile, while a cone with an angle of attack is a typical hypersonic three-dimensional boundary layer flow. Under the condition of a large attack angle, wind tunnel experiments find that a large area region on the side surface of the cone is mainly formed by the transition of saturated steady cross flow vortex and Mack mode dominant turbulence, fig. 1 shows the heat flow distribution of the wall surface, and it can be seen that the heat flow at the front part is in strip-shaped distribution, namely the steady cross flow vortex is generated. Meanwhile, the development of a Mack mode is enhanced by a saturated steady crossflow vortex found by a wind tunnel experiment and numerical calculation result, so that the disturbance energy of the Mack mode is rapidly increased to trigger the transition of turbulence.
For hypersonic three-dimensional boundary layer flow, numerical calculation and wind tunnel experiments find that incoming flow noise in a wind tunnel excites Mack disturbance, and roughness of a model surface excites a steady crossflow vortex mode. Meanwhile, the current wind tunnel experiment proves that the micro-scale rough units arranged on the surface of the model in the circumferential direction can develop into constant cross flow vortexes of wavelengths correspondingly. However, for the side surface region of the hypersonic large-attack-angle cone, the perturbation is dominated by the Mack mode and the constant cross flow vortex, and the current research result also shows that the constant cross flow vortex can make the Mack mode grow faster, so as to promote the transition position to advance.
Disclosure of Invention
The invention aims to provide a method for inhibiting a Mack mode by adopting a steady transverse flow vortex so as to solve the problem of flow transition of a high-supersonic-speed large-attack-angle conical side surface region.
The invention provides a method for inhibiting a Mack mode by adopting a steady crossflow vortex, which comprises the following steps:
for the standard mode shape of a cone with a large attack angle of a hypersonic aircraft, a plurality of coarse units are arranged near the front edge of the cone.
Further, the number of coarse cells is arranged 1 turn circumferentially near the leading edge of the cone.
Further, the plurality of coarse cells are arranged for 1 circle at equal intervals in the circumferential direction near the leading edge of the cone.
Further, the plurality of coarse cells are arranged at equal intervals in the circumferential direction near the leading edge of the cone for 1 turn, and the circumferential interval is 4 times of the disturbance wavelength of the Mack mode to be suppressed.
Further, the height of the roughness elements is of the order of 10 μm.
Further, the method for suppressing the Mack mode by using the steady cross flow vortex further includes:
process for verifying said method by numerical simulation
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the method for restraining the Mack mode by adopting the constant cross flow vortex is realized by arranging the plurality of coarse units near the front edge of the large attack angle cone, and is a passive delayed turbulence transition technology, so that the growth of the Mack mode can be weakened, the effect of delaying the transition of turbulence to reduce resistance is realized, and the active energy consumption is not needed.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and it is obvious for those skilled in the art that other related drawings can be obtained according to these drawings without inventive efforts.
Fig. 1 is a heat flow distribution diagram of the whole conical surface caused by the transition process of the hypersonic conical surface.
Fig. 2 is a flowchart of a method for suppressing the Mack mode by using constant cross flow vortices according to an embodiment of the present invention.
Fig. 3 is a graph showing the effect of the constant transverse flow vortices at the circumferential spacing of 48mm and 64mm near the leading edge of the cone on the Mack mode of a 16mm disturbance wavelength in the embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Examples
As shown in fig. 1, the present embodiment proposes a method for suppressing a Mack mode by using a constant cross flow vortex, where the method includes:
for the standard mode shape of a large attack angle cone of a hypersonic aircraft, a plurality of coarse units are arranged near the front edge of the cone. The method is a passive turbulence transition delaying technology, which can weaken the growth of a Mack mode, play a role in delaying the transition of turbulence and reducing resistance, and do not need to actively consume energy.
The method for suppressing the Mack mode using the steady cross flow vortex will be described in detail below with reference to specific examples.
Firstly, the rough units are arranged for 1 circle in the circumferential direction near the front edge of the cone, and preferably the rough units are arranged for 1 circle at equal intervals in the circumferential direction near the front edge of the cone. The specific limitations are as follows:
(1) the circumferential spacing of the rough units arranged in the circumferential direction near the front edge of the cone at equal intervals of 1 turn is 4 times of the disturbance wavelength of the Mack mode to be suppressed.
(2) The height of the roughness elements is of the order of 10 μm.
The method was then validated using numerical simulations. Specifically, for the hypersonic three-dimensional boundary layer flow under the hypersonic Mach6 condition, the method for inhibiting the Mack mode by adopting the steady crossflow vortex is verified by adopting numerical simulation. Taking a Mack mode with a disturbance wavelength of 16mm in a hypersonic three-dimensional boundary layer flow as an example, when a plurality of coarse units are respectively adopted to arrange 1 circle of circumferential equal interval near the front edge of a cone, wherein the circumferential interval is 3 times (namely 48mm) of the disturbance wavelength of the Mack mode to be suppressed, and a plurality of coarse units are respectively adopted to arrange 1 circle of circumferential equal interval near the front edge of the cone, wherein the circumferential interval is 4 times (namely 64mm) of the disturbance wavelength of the Mack mode to be suppressed, the Mack mode is suppressed, and fig. 3 shows a Mack mode disturbance amplitude curve under three conditions, wherein the abscissa is a flow direction position, and the ordinate is the influence of Mack modes with different spanwise wavelengths on a constant transverse flow vortex amplitude. As can be seen from fig. 3, the steady cross flow vortex when a plurality of coarse cells are arranged at equal intervals in the circumferential direction near the leading edge of the cone for 1 turn, and the circumferential interval is 3 times (i.e. 48mm) of the perturbation wavelength of the Mack mode to be suppressed suppresses the Mack mode in the early stage, and plays a role in enhancing the Mack mode in the later stage; and when the circumferential spacing of 1 circle of the plurality of coarse units which are arranged in the circumferential direction at equal intervals near the conical front edge is 4 times (namely 64mm) of the disturbance wavelength of the Mack mode to be suppressed, the development of the Mack mode can be effectively suppressed.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A method for suppressing Mack mode by adopting constant cross flow vortex is characterized by comprising the following steps:
for the standard mode shape of a cone with a large attack angle of a hypersonic aircraft, a plurality of coarse units are arranged near the front edge of the cone.
2. A method of suppressing Mack modes with steady cross-flow vortices according to claim 1, wherein the number of coarse cells are arranged 1 turn circumferentially near the leading edge of the cone.
3. A method of suppressing Mack modes using steady cross-flow vortices according to claim 2 wherein the number of coarse cells are arranged 1 turn circumferentially equidistant near the leading edge of the cone.
4. A method of suppressing a Mack mode using steady cross-flow vortices as claimed in claim 3 wherein the number of coarse cells are arranged circumferentially equally spaced around the leading edge of the cone for 1 turn with a circumferential spacing of 4 times the perturbation wavelength of the Mack mode to be suppressed.
5. A method of suppressing Mack modes using steady cross-flow vortices according to claim 4 wherein the height of the coarse cells is of the order of 10 μm.
6. A method of suppressing Mack modes using steady cross flow vortices as claimed in claim 1, further comprising:
and (3) adopting a numerical simulation to verify the method.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210016821.9A CN114441134A (en) | 2022-01-07 | 2022-01-07 | Method for inhibiting Mack mode by adopting steady crossflow vortex |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116534246A (en) * | 2023-07-05 | 2023-08-04 | 中国空气动力研究与发展中心计算空气动力研究所 | Flow direction vortex modulation device |
| CN117871014A (en) * | 2024-03-12 | 2024-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device and storage medium for inhibiting secondary instability of Grtler vortex |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014120328A2 (en) * | 2012-11-19 | 2014-08-07 | The Regents Of The University Of California | Hypersonic laminar flow control |
| US20170240271A1 (en) * | 2015-11-11 | 2017-08-24 | The Arizona Board Of Regents On Behalf Of The University Of Arizona | Control of hypersonic boundary layer transition |
| US20180105258A1 (en) * | 2016-10-14 | 2018-04-19 | U.S.A. as represented by the Administrator of NASA | Method and System for Delaying Laminar-To-Turbulent Transition in High-Speed Boundary Layer Flow |
| CN112733278A (en) * | 2021-03-31 | 2021-04-30 | 中国空气动力研究与发展中心计算空气动力研究所 | Passive delay turbulence transition control device and method |
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- 2022-01-07 CN CN202210016821.9A patent/CN114441134A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014120328A2 (en) * | 2012-11-19 | 2014-08-07 | The Regents Of The University Of California | Hypersonic laminar flow control |
| US20170240271A1 (en) * | 2015-11-11 | 2017-08-24 | The Arizona Board Of Regents On Behalf Of The University Of Arizona | Control of hypersonic boundary layer transition |
| US20180105258A1 (en) * | 2016-10-14 | 2018-04-19 | U.S.A. as represented by the Administrator of NASA | Method and System for Delaying Laminar-To-Turbulent Transition in High-Speed Boundary Layer Flow |
| CN112733278A (en) * | 2021-03-31 | 2021-04-30 | 中国空气动力研究与发展中心计算空气动力研究所 | Passive delay turbulence transition control device and method |
Non-Patent Citations (5)
| Title |
|---|
| SARIC ET AL: "leading-roughness as a transition control mechanism", AIAA PAPER * |
| 段志伟: "直接数值模拟粗糙单元诱导的高超声速边界层转捩", 中国博士学位论文全文数据库 (工程科技II辑) * |
| 董昊 等: "离散式粗糙元诱导翼型边界层转捩的数值和实验研究", 南京航空航天大学学报, vol. 50, no. 6 * |
| 董昊 等: "粗糙元对高超声速边界层转捩影响的研究进展", 实验流体力学, vol. 32, no. 6 * |
| 陈坚强;涂国华;张毅锋;徐国亮;袁先旭;陈诚;: "高超声速边界层转捩研究现状与发展趋势", no. 03 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116534246A (en) * | 2023-07-05 | 2023-08-04 | 中国空气动力研究与发展中心计算空气动力研究所 | Flow direction vortex modulation device |
| CN116534246B (en) * | 2023-07-05 | 2023-09-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Flow direction vortex modulation device |
| CN117871014A (en) * | 2024-03-12 | 2024-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Method, device and storage medium for inhibiting secondary instability of Grtler vortex |
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