CN111780949A - CFD analysis-based total pressure correction method for high-speed air inlet channel precursor wind tunnel experiment - Google Patents

CFD analysis-based total pressure correction method for high-speed air inlet channel precursor wind tunnel experiment Download PDF

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CN111780949A
CN111780949A CN202010663193.4A CN202010663193A CN111780949A CN 111780949 A CN111780949 A CN 111780949A CN 202010663193 A CN202010663193 A CN 202010663193A CN 111780949 A CN111780949 A CN 111780949A
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CN111780949B (en
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俞宗汉
黄国平
朱宇
夏晨
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Nanjing University of Aeronautics and Astronautics
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Abstract

The invention discloses a CFD analysis-based total pressure correction method for a high-speed air inlet channel precursor wind tunnel experiment, which is characterized by comprising the following steps of: (1) based on the designed pneumatic configuration of the precursor/air inlet channel, dividing the flow field of the precursor/air inlet channel through CFD numerical simulation, dividing the high-speed flow field into a free flow field area, a boundary layer area and a shock wave rear area, and determining the geometric position of each area; (2) designing a wind tunnel experiment, making an experiment measurement scheme, and positioning the region to which each total pressure probe belongs according to the geometric position of each total pressure probe; (3) in a wind tunnel experiment, measuring the pressure value P of each total pressure probe pointmeasuredAnd (4) respectively measuring the pressure values P of the total pressure probes in different areas according to the area to which each total pressure probe belongsmeasuredAnd correcting to obtain corrected real total pressure. The total pressure correction method provided by the invention is utilized to achieve the purpose of measuring the total pressure of a complex high-speed flow field by using a conventional probe.

Description

CFD analysis-based total pressure correction method for high-speed air inlet channel precursor wind tunnel experiment
Technical Field
The invention belongs to the technical field of high Mach number experiments, and particularly relates to a total pressure correction method for a wind tunnel experiment of a high-speed air inlet channel precursor based on CFD analysis.
Background
The measurement of the total pressure value of the flow field is an important link in a high-speed wind tunnel experiment, and typical pneumatic performances such as flow loss, Mach number, profile distortion characteristics and the like at a specific position can be obtained, so that the measurement accuracy plays a key role in judging whether an experiment result is effective or not. For a typical supersonic speed/hypersonic speed wind tunnel experiment with a simple flow field structure, the total pressure measurement is relatively convenient and the result is reliable. For a high-speed wind tunnel experiment with a complex wave system structure and thick near-wall low-energy flow, a certain error often exists in measurement of total pressure, and the core reason of the error is that a measurement result is limited by factors such as severe high-speed flow field change, small measurement section size, high probe strength requirement and the like.
At present, aiming at supersonic/hypersonic wind tunnel experiments with complex wave system structures, the main research direction is to design different probes to meet pressure measurement under various different experimental conditions, although the problem of large error of total pressure measurement is solved to a certain extent, the requirements on materials, processes and the like of the probes are high, and for experiments with most special requirements, the probes cannot be reused, the cost is high, and the resource consumption is very high.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to provide a total pressure correction method for a wind tunnel experiment of a high-speed air inlet channel precursor based on CFD analysis aiming at the defects of the prior art, and the purpose of measuring the total pressure of a complex high-speed flow field by using a conventional probe is realized.
The technical scheme is as follows: the invention discloses a CFD analysis-based total pressure correction method for a high-speed air inlet channel precursor wind tunnel experiment, which comprises the following steps of:
(1) based on the designed pneumatic configuration of the precursor/air inlet channel, dividing the flow field of the precursor/air inlet channel through CFD numerical simulation, dividing the high-speed flow field into a free flow field area, a boundary layer area and a shock wave rear area, and determining the geometric position of each area;
(2) designing a wind tunnel experiment, making an experiment measurement scheme, and positioning the region to which each total pressure probe belongs according to the geometric position of each total pressure probe;
(3) in a wind tunnel experiment, measuring the pressure value P of each total pressure probe pointmeasured，
(4) According toThe pressure values P measured by the total pressure probes in different areas in the area to which each total pressure probe belongsmeasuredAnd correcting to obtain corrected real total pressure.
The further preferable technical scheme of the invention is that the free flow field area in the step (1) is an area directly facing the free incoming flow, a total pressure probe in the area faces the supersonic or hypersonic incoming flow, an arched shock wave is arranged in front of the total pressure probe, and the measured total pressure value is higher.
Preferably, the pressure value P measured by a total pressure probe in the free flow field areameasuredCorrected according to the incoming stream Mach number M∞And measuring the pressure PmeasuredThe corrected real total pressure P can be obtained through a normal shock wave relationtrue,AThe calculation formula is as follows:
Figure BDA0002579376800000021
wherein k is the specific heat ratio of air and is 1.4.
Preferably, the boundary layer region in the step (1) is a near-wall low-flow-velocity region, the near-wall low-flow-velocity region comprises a supersonic velocity region and a subsonic velocity region, and the pressure value P measured in the supersonic velocity regionmeasuredThe pressure value P measured in the subsonic region is corrected by the formula (1)measuredThe measured pressure is the real pressure Ptrue,BThe calculation formula is as follows:
Figure BDA0002579376800000022
preferably, the definition of the supersonic and subsonic regions is as follows: solving for the measured pressure PmeasuredThe ratio of the local static pressure P to the local static pressure P is judged as a supersonic speed area if the ratio is greater than or equal to 1.89293; if the ratio is less than 1.89293, the sound velocity region is determined.
Preferably, the post-shock region in step (1) is a region where shock exists upstream, and is divided into a precursor shock region including three-dimensional curved shock waves and bow-shaped shock waves, and a precursor shock wave including three-dimensional curved shock waves, one or more pre-compression shock waves and bow-shaped shock waves, and other pre-compression shock wave regions according to the corresponding precursor compression type.
Preferably, the method for correcting the pressure value of the precursor shock wave region comprises the following steps:
1) first, estimating the total pressure P after the wavet1The calculation formula is as follows:
Figure BDA0002579376800000031
wherein β is the oblique shock angle;
2) according to total pressure P after wavet1And measuring the pressure PmeasuredCalculating a wavefront Mach number M by using a normal shock wave relationxThe calculation formula is as follows:
Figure BDA0002579376800000032
3) according to local static pressure P and wave front Mach number MxCalculating an initial true pressure Ptrue,CThe following formula:
Figure BDA0002579376800000033
4) according to Ptrue,CAfter-and-wave total pressure Pt1Until (P) is reachedt1-Ptrue,C) The computation converges close to 0, when Ptrue,CI.e. the true pressure.
Preferably, the method for correcting the pressure values of the precursor shock and other pre-compressed shock regions is as follows:
1) first, estimating the total pressure P after the wavetnConsidering the situation of multi-shock wave compression in advance, the calculation formula is as follows:
Figure BDA0002579376800000034
wherein f (M, beta) is an oblique shock wave basic relational expression as follows:
Figure BDA0002579376800000035
at the same time, βiDepending on the particular compression type, Mi+1Calculated according to the following formula:
Figure BDA0002579376800000036
2) to obtain PtnThen, based on the measured pressure PmeasuredCombining with normal shock wave formula to calculate a wavefront Mach number MxThe following formula:
Figure BDA0002579376800000041
3) according to local static pressure P and wave front Mach number MxAn initial true pressure P can be calculatedtrue,DThe following formula:
Figure BDA0002579376800000042
4) according to its total pressure P after the wavetnUntil (P) is reachedtn-Ptrue,D) The computation converges close to 0, when Ptrue,DI.e. the true pressure.
Has the advantages that: based on the wind tunnel experiment requirement of the high-speed air suction type propulsion system, the invention provides a method for dividing the high-speed flow field into a plurality of areas influenced by shock waves and low-energy flow by grabbing typical characteristics of the flow field, judging the area of a probe according to the total pressure test result of the flow field, carrying out corresponding data correction, ensuring the correction accuracy through iterative calculation of multiple control factors, finally forming a CFD analysis-based high-speed air inlet channel precursor wind tunnel experiment total pressure correction method, and achieving the purpose of using a conventional probe to complete the total pressure measurement of a complex high-speed flow field.
Drawings
FIG. 1 is a schematic diagram of an application area of a high-speed inlet duct precursor wind tunnel experiment total pressure correction method based on CFD analysis.
FIG. 2 is a peripheral wave system of the probe in the region A of FIG. 1.
FIG. 3 is a peripheral wave system of the probe in the region B of FIG. 1.
FIG. 4 is a peripheral wave system of the probe in the region C of FIG. 1.
FIG. 5 is a peripheral wave system of the probe in region D of FIG. 1.
FIG. 6 is a general flow chart of a total pressure correction method for a high-speed inlet duct precursor wind tunnel experiment based on CFD analysis.
Fig. 7 is a flow chart of a "initial value + iteration" solving method of the total pressure correction method for the high-speed inlet duct precursor wind tunnel experiment based on CFD analysis with respect to the region C, D.
Fig. 8 is a graph showing the change rule of the relative error of the correction method result and the correction method directly applied to the pressure after the wave setting for the same position of the flow field along with the mach number.
Detailed Description
The technical solution of the present invention is described in detail below with reference to the accompanying drawings, but the scope of the present invention is not limited to the embodiments.
Example (b): a total pressure correction method for a wind tunnel experiment of a high-speed air inlet channel precursor based on CFD analysis comprises the following steps:
(1) dividing a flow field of the precursor/air inlet channel by CFD numerical simulation based on the designed pneumatic configuration of the precursor/air inlet channel, as shown in figure 1, dividing a high-speed flow field into a free flow field area A, a boundary layer area B and an after-shock area, wherein the after-shock area is divided into a precursor shock wave area C containing three-dimensional curved surface shock waves and bow shock waves according to a corresponding precursor compression type, and a precursor shock wave area D containing three-dimensional curved surface shock waves, one or more pre-compression shock waves and bow shock waves and other pre-compression shock wave areas D;
(2) designing a wind tunnel experiment, making an experiment measurement scheme, and positioning the region to which each total pressure probe belongs according to the geometric position of each total pressure probe;
(3) in a wind tunnel experiment, measuring the pressure value P of each total pressure probe pointmeasured，
(4) According to the region to which each total pressure probe belongs, respectively measuring the pressure values P of the total pressure probes in different regionsmeasuredAnd correcting to obtain corrected real total pressure.
The specific correction method comprises the following steps:
the correction method for the free flow field area A is suitable for the situation of directly facing the free incoming flow, as shown in figure 2. The total pressure probe faces supersonic and hypersonic incoming flow, and an arched shock wave appears in front of the probe, so that the measured total pressure value is higher. Because the size of the probe is small, the intensity of bow shock waves is similar to that of normal shock waves, and for the area A, the measured total pressure value is corrected by using a normal shock wave relational expression:
according to the Mach number M of the incoming flow∞And measuring the pressure PmeasuredThe corrected real total pressure P can be obtained through a normal shock wave relationtrue,AThe calculation formula is as follows:
Figure BDA0002579376800000051
wherein k is the specific heat ratio of air and is 1.4.
And II, the method for correcting the airflow data of the boundary layer area is suitable for the low flow velocity area near the wall surface, as shown in figure 3. The region includes a supersonic velocity region and a subsonic velocity region. The definition mode of the supersonic speed and the subsonic speed regions is as follows: solving for the measured pressure PmeasuredThe ratio of the local static pressure P to the local static pressure P is judged as a supersonic speed area if the ratio is greater than or equal to 1.89293; if the ratio is less than 1.89293, the sound velocity region is determined.
Pressure value P measured for supersonic zonemeasuredThe pressure value P measured in the subsonic region is corrected by the formula (1)measuredThe measured pressure is the real pressure Ptrue,BThe calculation formula is as follows:
Figure BDA0002579376800000061
III for precursor shock zone C gasThe flow data correction method, the area comprises three-dimensional curved surface shock waves and bow shock waves in front of the probe, and is shown in figure 4. The difference from the free-flow state is that the gas flow has undergone a three-dimensional curved shock wave of the precursor, so that the total pressure P after the wave is estimated firstt1。
1) The total pressure P after estimationt1The calculation formula is as follows:
Figure BDA0002579376800000062
wherein β is the oblique shock angle;
2) according to total pressure P after wavet1And measuring the pressure PmeasuredCalculating a wavefront Mach number M by using a normal shock wave relationxThe calculation formula is as follows:
Figure BDA0002579376800000063
3) according to local static pressure P and wave front Mach number MxCalculating an initial true pressure Ptrue,CThe following formula:
Figure BDA0002579376800000064
4) according to Ptrue,CAfter-and-wave total pressure Pt1Until (P) is reachedt1-Ptrue,C) The computation converges close to 0, when Ptrue,CI.e. the true pressure.
And IV, for precursor shock and other pre-compressed shock regions D, the regions comprise three-dimensional curved surface shock, one or more pre-compressed shock and bow shock in front of the probe, as shown in figure 5. The principle of this case is consistent with the method of flow data correction for the precursor shock zone C, but with its post-wave total pressure PtnIn the calculation of (2), the case of multi-shock compression needs to be considered in advance.
1) First, estimating the total pressure P after the wavetnConsidering the situation of multi-shock wave compression in advance, the calculation formula is as follows:
Figure BDA0002579376800000071
wherein f (M, beta) is an oblique shock wave basic relational expression as follows:
Figure BDA0002579376800000072
at the same time, βiDepending on the particular compression type, Mi+1Calculated according to the following formula:
Figure BDA0002579376800000073
2) to obtain PtnThen, based on the measured pressure PmeasuredCombining with normal shock wave formula to calculate a wavefront Mach number MxThe following formula:
Figure BDA0002579376800000074
3) according to local static pressure P and wave front Mach number MxAn initial true pressure P can be calculatedtrue,DThe following formula:
Figure BDA0002579376800000075
4) according to its total pressure P after the wavetnUntil (P) is reachedtn-Ptrue,D) The computation converges close to 0, when Ptrue,DI.e. the true pressure.
The total pressure correction method for the region C, D adopts a solution method of "initial value + iteration", and a flowchart thereof is shown in fig. 7, for the total pressure data of the region C, only the compression of the precursor shock wave is considered when Pt is given, so that only β needs to be given, and for the total pressure data of the region D, the influence of the precursor shock wave and other pre-compression waves needs to be considered when Pt is given, so that β and β 1, β 2, …, and β n in a dashed box of the flowchart need to be given.
For comparison, in this embodiment, the correction method of the present invention separately adopted for the same flow field is compared with the correction method adopted for directly giving the pressure after the wave, and the comparison result is shown in fig. 8, where Rp is calculated as:
Figure BDA0002579376800000081
in the formula PtureIs total pressure correction value P ' obtained by adopting a method of ' giving initial value + iterative solution 'tureThe total pressure correction value is obtained by a traditional method of directly determining the post-shock wave air flow parameters by using an oblique shock wave formula.
When a conventional total pressure probe is adopted to carry out a high-Mach cold-state wind tunnel experiment, the conventional wind tunnel total pressure data processing mode is adopted, for data processing of the region A, B, oblique shock waves are used for correcting total pressure data to replace more complex three-dimensional shock waves to solve post-wave flow field data, the simplified process omits the non-uniform characteristic of a three-dimensional curved surface post-wave flow field, and therefore the corrected total pressure data is often inaccurate. Meanwhile, for the condition that the angles of the symmetrical surface shock waves are equal, the intensity of correction by adopting an oblique shock wave relational expression is smaller than that of real three-dimensional compression, so that the correction value of the total pressure of the wave back is larger, the correction value of the wave front Mach number of the bow-shaped shock wave in front of the probe is smaller, and finally the correction value of the total pressure of the probe is smaller.
According to the method, the three-dimensional compression effect of the flow field is fully considered in data correction, and iterative calculation is further performed on the pre-estimated total pressure of the probe on the basis of the pre-estimated total pressure of the probe so as to approach the real total pressure value of the flow field. As shown in fig. 8, according to the correction of the previous experimental data, for the same flow field at a more complex shock wave downstream position (e.g., region C, D), the larger the incoming flow mach number or the facing compression strength, the larger the data correction degree, and the higher the total pressure data correction degree, and the method of the present invention is more accurate than the conventional method by about 3%, and the specific correction degree is determined by the incoming flow condition, the precursor pre-compression strength, and the like.
As noted above, while the present invention has been shown and described with reference to certain preferred embodiments, it is not to be construed as limited thereto. Various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

Claims (8)

1. A total pressure correction method for a wind tunnel experiment of a high-speed air inlet channel precursor based on CFD analysis is characterized by comprising the following steps:
(1) based on the designed pneumatic configuration of the precursor/air inlet channel, dividing the flow field of the precursor/air inlet channel through CFD numerical simulation, dividing the high-speed flow field into a free flow field area, a boundary layer area and a shock wave rear area, and determining the geometric position of each area;
(2) designing a wind tunnel experiment, making an experiment measurement scheme, and positioning the region to which each total pressure probe belongs according to the geometric position of each total pressure probe;
(3) in a wind tunnel experiment, measuring the pressure value P of each total pressure probe pointmeasured，
(4) According to the region to which each total pressure probe belongs, respectively measuring the pressure values P of the total pressure probes in different regionsmeasuredAnd correcting to obtain corrected real total pressure.
2. The CFD analysis-based total pressure correction method for the wind tunnel experiment of the high-speed inlet duct precursor is characterized in that in the step (1), the free flow field area is an area directly facing to the free incoming flow, the total pressure probe in the area faces to the supersonic speed or the hypersonic speed incoming flow, an arched shock wave is arranged in front of the total pressure probe, and the measured total pressure value is higher.
3. The CFD analysis-based total pressure correction method for high-speed air inlet channel precursor wind tunnel experiment according to claim 2, wherein the pressure value P measured by a total pressure probe in a free flow field areameasuredCorrected according to the incoming stream Mach number M∞And measuring the pressure PmeasuredThe corrected real total pressure P can be obtained through a normal shock wave relationtrue,AThe calculation formula is as follows:
Figure FDA0002579376790000011
wherein k is the specific heat ratio of air and is 1.4.
4. The CFD analysis-based total pressure correction method for high-speed inlet channel precursor wind tunnel experiment according to claim 3, wherein the boundary layer area in the step (1) is a near-wall low-flow-velocity area, the near-wall low-flow-velocity area comprises a supersonic velocity area and a subsonic velocity area, and a pressure value P measured in the supersonic velocity areameasuredThe pressure value P measured in the subsonic region is corrected by the formula (1)measuredThe measured pressure is the real pressure Ptrue,BThe calculation formula is as follows:
Figure FDA0002579376790000021
5. the CFD analysis-based total pressure correction method for the wind tunnel experiment of the high-speed inlet duct precursor is characterized in that the definition mode of the supersonic speed and the subsonic speed regions is as follows: solving for the measured pressure PmeasuredThe ratio of the local static pressure P to the local static pressure P is judged as a supersonic speed area if the ratio is greater than or equal to 1.89293; if the ratio is less than 1.89293, the sound velocity region is determined.
6. The CFD analysis-based total pressure correction method for the high-speed inlet channel precursor wind tunnel experiment is characterized in that in the step (1), a shock wave rear area is an area with a shock wave at the upstream, and is divided into a precursor shock wave area containing three-dimensional curved surface shock waves and bow-shaped shock waves, a precursor shock wave area containing three-dimensional curved surface shock waves, one or more pre-compression shock waves and bow-shaped shock waves and other pre-compression shock wave areas according to a corresponding precursor compression type.
7. The CFD analysis-based total pressure correction method for the wind tunnel experiment of the high-speed inlet duct precursor is characterized in that the correction method for the pressure value of the precursor shock wave region is as follows:
1) first, estimating the total pressure P after the wavet1The calculation formula is as follows:
Figure FDA0002579376790000022
wherein β is the oblique shock angle;
2) according to total pressure P after wavet1And measuring the pressure PmeasuredCalculating a wavefront Mach number M by using a normal shock wave relationxThe calculation formula is as follows:
Figure FDA0002579376790000023
3) according to local static pressure P and wave front Mach number MxCalculating an initial true pressure Ptrue,CThe following formula:
Figure FDA0002579376790000024
4) according to Ptrue,CAfter-and-wave total pressure Pt1Until (P) is reachedt1-Ptrue,C) The computation converges close to 0, when Ptrue,CI.e. the true pressure.
8. The CFD analysis-based total pressure correction method for the high-speed inlet channel precursor wind tunnel experiment is characterized in that the correction method for the pressure values of precursor shock waves and other pre-compression shock wave regions comprises the following steps:
1) first, estimating the total pressure P after the wavetnConsidering the situation of multi-shock wave compression in advance, the calculation formula is as follows:
Figure FDA0002579376790000031
wherein f (M, beta) is an oblique shock wave basic relational expression as follows:
Figure FDA0002579376790000032
at the same time, βiDepending on the particular compression type, Mi+1Calculated according to the following formula:
Figure FDA0002579376790000033
2) to obtain PtnThen, based on the measured pressure PmeasuredCombining with normal shock wave formula to calculate a wavefront Mach number MxThe following formula:
Figure FDA0002579376790000034
3) according to local static pressure P and wave front Mach number MxAn initial true pressure P can be calculatedtrue,DThe following formula:
Figure FDA0002579376790000035
4) according to its total pressure P after the wavetnUntil (P) is reachedtn-Ptrue,D) The computation converges close to 0, when Ptrue,DI.e. the true pressure.
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