CN113701981A - Near-wall motion shock wave identification method - Google Patents
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Abstract
The invention relates to a near-wall motion shock wave identification method, which is characterized by comprising the following steps: acquiring wall dynamic pressure data; identifying a pressure ramping sub-curve of the wall dynamic pressure data; extracting shock wave information according to the pressure steep rising sub-curve; and judging the motion direction of the shock wave. The near-wall motion shock wave identification method can provide information such as the number, strength, appearance and departure time, motion direction and the like of shock waves passing through wall surface measuring points, and provides important data support for deeply analyzing the relation between noise and motion shock waves.
Description
Technical Field
The invention relates to the technical field of aerodynamics, in particular to a near-wall motion shock wave identification method.
Background
The moving shock waves are widely existed in supersonic cavity flow, shock wave buffeting, detonation wave propagation and other flows. These moving shocks often carry strong pressure disturbances, move at high speed along the wall, and are the main source of wall noise. Accurate identification of these shock waves moving along the wall is important to understanding the mechanism of generation and propagation of wall noise.
The Buning and Steger analysis finds the normal Mach number Ma before and after the shock wavenRespectively greater than and less than 1, by extracting ManA 1 isosurface results in a shock surface shape. Kanamori and Suzuki developed a three-dimensional stationary shock wave identification method based on the characteristic line theory. Akhlaghi and the like successfully extract a numerical value or a shock wave structure in a test schlieren by using an edge detection algorithm. Liu and the like apply deep learning to post-processing analysis of mass flow field data, so that the speed of shock wave identification is increased by 3 times. On the whole, most of the existing shock wave identification algorithms mainly process and analyze spatial flow field data, but lack shock waves identifying time sequence flow field data.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a near-wall motion shock wave identification method, aiming at the above-mentioned defects of the prior art, comprising:
acquiring wall dynamic pressure data;
identifying a pressure ramping sub-curve of the wall dynamic pressure data;
extracting shock wave information according to the pressure steep rising sub-curve;
and judging the motion direction of the shock wave.
Preferably, the acquiring wall surface dynamic pressure data includes:
and acquiring wall dynamic pressure data through numerical calculation or wind tunnel test.
Preferably, the shock wave information includes: the number, intensity, appearance and departure time and movement direction of the shock waves of the pressure measuring points.
Preferably, the identifying the pressure ramping sub-curve of the wall dynamic pressure data comprises: the characteristic of the pressure signal showing a sharp rise is identified.
Preferably at 10-7Second to 10-8Seconds are time steps to perform numerical calculations.
Preferably, a high-frequency dynamic pressure sensor is selected for the wind tunnel test.
Preferably, the identifying a characteristic of a sharp rise in the pressure signal comprises:
when the pressure rises, the slope of the curve is increased;
when the pressure increment is increased, the difference value at the two ends of the sub-curve is increased;
the slope and the height difference of the pressure steep rising sub-curve meet the condition:
wherein (t)m，p(tm) Starting point of the corresponding pressure ramp (t)n，p(tn) Corresponding to the end point of the pressure ramp-up sub-curve, alpha being the slope limiting factor, prmsIs the root mean square value of the pulsating pressure at the measuring point P, c∞And delta is the free incoming flow velocity, delta is the flow direction grid scale, and beta is the height difference limiting factor.
Preferably, the judging the motion direction of the shock wave includes: and utilizing the flow field information of the measuring point near the measuring point P.
Preferably, the measuring points near the measuring point P comprise the left side and the right side of the measuring point P.
The near-wall motion shock wave identification method has the following beneficial effects: identifying a pressure steep rise sub-curve of the wall surface dynamic pressure data by acquiring the wall surface dynamic pressure data, and extracting shock wave information according to the pressure steep rise sub-curve so as to judge the motion direction of the shock wave; the method can provide information such as the number, the strength, the appearance and departure time, the movement direction and the like of the shock waves passing through the wall surface measuring points, and provides important data support for deeply analyzing the relation between the noise and the movement shock waves.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
FIG. 1 is a schematic view of a pressure response curve of a single moving shock wave passing through a certain measuring point on a wall surface;
FIG. 2 is a flow chart of the method for identifying near-wall motion shock waves of the present invention;
FIG. 3 is a schematic view of a pressure response curve of a certain measuring point P on the wall surface of the supersonic cavity;
FIG. 4(a) is a pressure variation diagram of the measuring point when the shock wave is located at the right side of the point R in the shock wave movement process;
FIG. 4(b) is a pressure variation diagram of the measuring point when the shock wave is located between the point L and the point R in the shock wave movement process;
FIG. 4(c) is a pressure variation diagram of the measuring point when the shock wave is located at the left side of the point L in the shock wave movement process;
FIG. 5 is a schematic diagram of the effect of near-wall motion shock wave recognition algorithm on the recognition of forward-propagating shock wave type shock waves;
FIG. 6 is a schematic diagram of the effect of near-wall motion shock recognition algorithm on the identification of backward-propagating shock type shock;
FIG. 7 is a schematic diagram of the effect of near-wall motion shock wave recognition algorithm on the recognition of equidirectional motion shock wave pair type shock waves;
FIG. 8 is a schematic diagram of the effect of near-wall motion shock recognition algorithm on the recognition of equidirectional motion shock pair type shocks;
FIG. 9 is a schematic view of the pressure space-time distribution of the middle section of the cavity floor plotted using numerical water-gas ratio;
fig. 10 is a schematic diagram of the shock wave identification results of all monitoring points.
In the figure, 1-a slow ascending sub-curve, 2-a steep ascending sub-curve, and 3-a descending sub-curve.
Detailed Description
FIG. 1 is a schematic diagram of a pressure response curve of a single moving shock wave passing through a certain point on a wall surface. As shown in fig. 1, the pressure variation process is divided into two stages, i.e., an ascending stage and a descending stage. The pressure rise stage corresponds to the process of passing the shock wave through the monitoring point. At this stage, the monitor point pressure is derived from the wavefront pressure p1Sharply rising to the wave rear pressure p2. Due to the small thickness of the shock, the shock passes the monitoring point very quickly and the duration of the rise phase is short. Thereafter, as the shock wave gradually moves away from the monitoring point, the monitoring point pressure begins to drop and gradually returns to ambient. The falling phase is significantly longer in duration than the rising phase.
Example one
Based on the analysis of the pneumatic characteristics of the motion shock waves in the figure 1, the invention provides a near-wall motion shock wave identification method, which can be a near-wall motion shock wave identification algorithm based on wall surface pulsating pressure time sequence data in specific implementation. FIG. 2 is a flow chart of the near-wall motion shock wave identification method of the present invention. As shown in fig. 2, a near-wall motion shock wave identification method at least includes the steps of:
s1, acquiring wall dynamic pressure data;
and acquiring wall dynamic pressure data through numerical calculation or wind tunnel test. In order to obtain dynamic pressure time sequence data with high time resolution, the numerical calculation adopts smaller time step which can be 10-7Second to 10-8Seconds are time steps to perform numerical calculations. In order to obtain dynamic pressure time sequence data with high time resolution, a high-frequency dynamic pressure sensor is selected for wind tunnel test.
S2, identifying a pressure steep sub-curve of the wall surface dynamic pressure data;
the main feature of a moving shock wave in space is an extremely strong pressure gradient, while the main feature in time is a sudden rise in the pressure signal. The pressure time-series curve is observed, when the pressure signal is found to have a sharp rise, the shock wave passes through the pressure time-series curve. In order to obtain the pressure response information when the shock wave passes through, the sub-curve with the characteristic of 'pressure steep rise' in the pressure time sequence curve needs to be identified. Identifying a pressure ramping sub-curve of the wall dynamic pressure data comprises: the characteristic of the pressure signal showing a sharp rise is identified.
FIG. 3 is a schematic view of a pressure response curve of a certain point P on the wall surface of the supersonic cavity. As shown in fig. 3, it can be seen that the pressure response curve shows a random rise and fall under the action of various flow structures such as shock waves, vortices and the like. The pressure response curve is composed of a plurality of rising curve segments and falling curve segments with different slopes. The ascending curve segment contains the steep ascending sub-curve we are interested in.
The pressure rise at the monitoring point may be induced by the passage of the shock wave or other flow structures. Unlike other flow configurations, the shock wave induced pressure ramp has the following characteristics: (1) as the pressure increases, the slope of the curve increases. (2) As the pressure increase becomes larger, the difference at both ends of the sub-curve becomes larger.
Based on the two features, the slope and the height difference of the pressure steep rising sub-curve shown in fig. 2 satisfy the following conditions:
wherein (t)m，p(tm) Starting point of the corresponding steep ascending sub-curve, (t)n，p(tn) Corresponding to the end point of the steep ascending sub-curve, alpha being the slope limiting factor, prmsIs the root mean square value of the pulsating pressure at the measuring point P, c∞And delta is the free incoming flow velocity, delta is the flow direction grid scale, and beta is the height difference limiting factor.
S3, extracting shock wave information according to the pressure steep rising sub-curve;
the shock wave information includes: the number, intensity, appearance and departure time and movement direction of the shock waves of the pressure measuring points. And (3) counting the number of the pressure steep rise sub-curves identified in the step (1) to obtain the number of shock waves passing through the measuring point P. In addition, the starting point and the end point of the pressure-rising sub-curve correspond to the shock wave occurrence time tbAnd departure time te. The pressure at the starting point and the ending point is respectively the shock wave front pressure p1Pressure p after the wave of neutralization2. By utilizing the wave front and wave rear pressures, the pressure difference delta p before and after the shock wave and the pressure ratio k before and after the shock wave can be calculatedpShock wave motion Mach number MSAnd parameters for characterizing the intensity of the shock wave:
Δp＝p2-p1 #(2)
kp＝p2/p1 #(3)
and S4, judging the motion direction of the shock wave.
The change of the motion direction of the shock wave does not influence the pressure response of the measuring point. Therefore, it is difficult to identify the direction of motion of the shock from the pressure response data of a single station. In order to identify the motion direction of the shock wave, the flow field information of the measuring point near the point P is also required to be used. Taking numerical calculation as an example, it is necessary to add pressure timing data of two grid points adjacent to the point P to the input data of the algorithm.
Judging the motion direction of the shock wave comprises the following steps: and utilizing the flow field information of the measuring point near the measuring point P. The points near point P include the left and right sides of point P.
FIG. 4(a) is a pressure variation diagram of the measuring point when the shock wave is located at the right side of the point R in the shock wave movement process; FIG. 4(b) is a pressure variation diagram of the measuring point when the shock wave is located between the point L and the point R in the shock wave movement process; fig. 4(c) is a pressure change diagram of the measuring point when the shock wave is located at the left side of the point L in the shock wave movement process. As shown in FIGS. 4(a) to 4(c), the measurement point L and the measurement point R are located on the left and right sides of the measurement point P, respectively. When the shock wave approaches the measuring point R from the right side, the point L and the point R are both positioned in the shock wave front, and the pressure difference between the two is 0. The pressure difference between the shock wave entry point L and the shock wave entry point R gradually increases as the point L and the point R are located before and after the shock wave, respectively. When the shock wave continues to move to the left side of the point L, the pressure difference between the point L and the point R is restored to 0 again at the moment because the point L and the point R are both positioned after the shock wave. From the above analysis, it can be found that when the pressure difference between the points L and R is the greatest, the shock wave is located between the points L and R, and the corresponding time t is recordedn。tnThe following relationship is satisfied:
|Δp(tn)|＝max(|Δp(tb)|，|Δp(tb+Δt)|，…，|Δp(te)|)#(5)
where Δ p is the pressure difference between point L and point R. According to the aerodynamic characteristics of one-dimensional motion shock waves, the pressure after the shock waves is higher than the wavefront pressure, and the shock waves always move from a high-pressure side to a low-pressure side. The motion direction of the shock wave can be judged by comparing the pressures on the two sides of the shock wave. If p isL(tn)＞pR(tn) The shock wave moves to the right. If p isL(tn)＜pR(tn) The shock moves to the left.
Example two
FIG. 5 is a schematic diagram of the effect of near-wall motion shock wave recognition algorithm on the recognition of forward-propagating shock wave type shock waves; FIG. 6 is a schematic diagram of the effect of near-wall motion shock recognition algorithm on the identification of backward-propagating shock type shock; FIG. 7 is a schematic diagram of the effect of near-wall motion shock wave recognition algorithm on the recognition of equidirectional motion shock wave pair type shock waves; fig. 8 is a schematic diagram of the effect of a near-wall motion shock wave recognition algorithm on recognizing a type shock wave of a homodromous shock wave pair. As shown in fig. 5 to 8, the application effect of the near-wall motion shock wave algorithm is shown by taking the cavity flow with the mach number of 2.0 as an example. In order to identify the shock wave structure moving along the cavity bottom plate, 40 equally-spaced main monitoring points are arranged on the middle section of the bottom plate, and the spacing between every two main monitoring points is 0.025 times of the cavity width. Two auxiliary monitoring points are arranged near each main monitoring point and used for identifying the motion direction of the shock wave. The auxiliary monitoring point is about one grid unit length away from the main monitoring point. A slope limiting factor alpha and a height difference limiting factor beta in a near-wall motion shock wave identification algorithm are respectively set to be 0.1 and 0.2, and a flow direction grid scale delta is 0.005 times of the width of a cavity. The background flow field in the figure is drawn by numerical water-gas ratio. The abscissa is time and the ordinate is pressure. The ordinate of the bottom end of the line pillar corresponds to the shock wave front pressure, and the ordinate of the top end of the line pillar corresponds to the shock wave rear pressure. White indicates that the shock wave propagates forward (left), and black indicates that the shock wave propagates backward (right). As shown in fig. 5, a white line bar near the right side of the plot indicates that a forward propagating shock wave is about to pass through the monitoring point, which is exactly the same as the background flow field we observe. By comparison, it can be seen that the recognition results of the near-wall shock wave recognition algorithm on four types of shock waves shown in fig. 5 to 8 are completely consistent with the display results of the spatial flow field.
The motion shock wave identification effect of a single monitoring point is checked in the prior art, and the identification results of all 40 monitoring points are evaluated continuously in the following process. FIG. 9 is a schematic view of the pressure space-time distribution of the middle section of the cavity floor plotted using numerical water-gas ratio; fig. 10 is a schematic diagram of the shock wave identification results of all monitoring points. As shown in FIGS. 9 and 10, the white and black circles in the figures represent shock waves identified by different monitoring points, and the circles represent shock waves identified by different monitoring pointsThe ordinate of the center represents the flow direction position x/L of the detection point, and the abscissa of the center represents the occurrence moment t of the shock wavenU∞And L. White indicates that the shock wave propagates forward (left), and black indicates that the shock wave propagates backward (right). As can be seen by comparing fig. 9 and fig. 10, the recognition results of the near-wall motion shock wave recognition algorithm at different monitoring points are substantially consistent with the shock wave motion track presented by the space-time diagram of the cavity floor. The algorithm can accurately identify different types of shock wave structures such as small shock waves, feedback shock waves, cavity front wall reflection shock waves and the like moving along the wall surface of the cavity. Meanwhile, the algorithm accurately marks the backward movement characteristics of the small shock wave and the reflected shock wave of the front wall of the cavity, and also accurately marks the forward movement characteristics of the feedback shock wave. In addition, the algorithm can uniformly identify high-intensity shock waves near the rear wall of the cavity and low-intensity shock waves near the front wall of the cavity.
In summary, the identification result of the cavity flow motion shock waves shows that the near-wall motion shock wave identification algorithm has a good identification effect on shock waves of different types, different intensities and different motion directions.
Through the design of the above embodiment, the invention has the beneficial effects that: identifying a pressure steep rise sub-curve of the wall surface dynamic pressure data by acquiring the wall surface dynamic pressure data, and extracting shock wave information according to the pressure steep rise sub-curve so as to judge the motion direction of the shock wave; the method can provide information such as the number, the strength, the appearance and departure time, the movement direction and the like of the shock waves passing through the wall surface measuring points, and provides important data support for deeply analyzing the relation between the noise and the movement shock waves.
While the invention has been described with reference to specific embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation to the teachings of the invention without departing from its scope. Therefore, it is intended that the invention not be limited to the particular embodiments disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (9)
1. A near-wall motion shock wave identification method is characterized by comprising the following steps:
acquiring wall dynamic pressure data;
identifying a pressure ramping sub-curve of the wall dynamic pressure data;
extracting shock wave information according to the pressure steep rising sub-curve;
and judging the motion direction of the shock wave.
2. The near-wall motion shock wave identification method according to claim 1, wherein the obtaining wall dynamic pressure data comprises:
and acquiring wall dynamic pressure data through numerical calculation or wind tunnel test.
3. The near-wall motion shock identification method of claim 1, wherein the shock information comprises: the number, intensity, appearance and departure time and movement direction of the shock waves passing through the pressure measuring points.
4. The near-wall motion shock wave identification method of claim 1, wherein identifying the pressure steep sub-curve of the wall dynamic pressure data comprises: the characteristic of the pressure signal showing a sharp rise is identified.
5. The near wall motion shock wave identification method of claim 2, wherein 10 is used-7Second to 10-8Seconds are time steps to perform numerical calculations.
6. The near-wall motion shock wave identification method according to claim 2, wherein a high-frequency dynamic pressure sensor is selected for a wind tunnel test.
7. The near wall motion shock identification method of claim 4, wherein identifying the characteristic of the abrupt rise in pressure signal comprises:
when the pressure rises, the slope of the curve is increased;
when the pressure increment is increased, the difference value at the two ends of the sub-curve is increased;
the slope and the height difference of the pressure steep rising sub-curve meet the condition:
wherein (t)m，p(tm) Starting point of the corresponding pressure ramp (t)n，p(tn) Corresponding to the end point of the pressure ramp-up sub-curve, alpha being the slope limiting factor, prmsIs the root mean square value of the pulsating pressure at the measuring point P, c∞And delta is the free incoming flow velocity, delta is the flow direction grid scale, and beta is the height difference limiting factor.
8. The near-wall motion shock wave identification method according to any one of claims 1 to 7, wherein the judging of the shock wave motion direction comprises: and utilizing the flow field information of the measuring point near the measuring point P.
9. The near-wall motion shock wave identification method according to claim 8, wherein the measurement points near the measurement point P include left and right sides of the measurement point P.
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