CN111766039B - Method for calculating measurement result of compressible fluid disturbance mode of subsonic wind tunnel - Google Patents

Method for calculating measurement result of compressible fluid disturbance mode of subsonic wind tunnel Download PDF

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CN111766039B
CN111766039B CN202010659927.1A CN202010659927A CN111766039B CN 111766039 B CN111766039 B CN 111766039B CN 202010659927 A CN202010659927 A CN 202010659927A CN 111766039 B CN111766039 B CN 111766039B
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vortex
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CN111766039A (en
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杜钰锋
林俊
王勋年
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High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
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High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/08—Aerodynamic models
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract

The invention discloses a method for calculating a measurement result of a compressible fluid disturbance mode of a subsonic wind tunnel. The method comprises the following steps: (1) preparing data acquisition; (2) measuring the flow field pulsation quantity of the subsonic wind tunnel test section by using a hot wire anemometer to obtain the mass flow pulsation, the total temperature pulsation and the cross correlation quantity of the mass flow pulsation and the total temperature pulsation; (3) deducing and solving an acoustic mode and a vortex mode on the premise that the entropy mode is 0; (4) and deducing and solving the acoustic modal and eddy modal components of the basic physical quantity of the flow field. The method obtains a specific expression of a disturbance mode and acoustic mode and eddy mode components of the basic physical quantity of the flow field in the compressible fluid of the subsonic wind tunnel, solves the acoustic mode and eddy mode of the flow field and the acoustic mode and eddy mode components of the basic physical quantity of the flow field by using the measurement result of the hot wire anemometer, provides a feasible method for the disturbance mode analysis of the compressible fluid of the subsonic wind tunnel, and provides technical support for the flow field quality evaluation of a newly-built wind tunnel.

Description

Method for calculating measurement result of compressible fluid disturbance mode of subsonic wind tunnel
Technical Field
The invention belongs to the field of test aerodynamics, and particularly relates to a method for calculating a measurement result of a compressible fluid disturbance mode of a subsonic wind tunnel.
Background
As is known, the core flow area of the wind tunnel test section is an area with the best quality of a flow field in the wind tunnel after being rectified by a rectifying device, but the free incoming flow entering the wind tunnel test section still has unsteady characteristics. The disturbance of the free incoming flow can affect the precision of a wind tunnel test result, so that errors are generated in the wind tunnel test result, and the errors in the wind tunnel test result mean that design errors exist in the lift force, the drag coefficient and other pneumatic parameters for the design of the aircraft, so that the load capacity of the aircraft can be estimated, and the economy and the safety of the aircraft are severely restricted. Therefore, it is important to perform accurate quantitative evaluation on the disturbance of the free incoming flow.
The free incoming flow disturbance is formed by superposition of three basic disturbance modes, which are respectively as follows: the three disturbance modes are different in composition. The acoustic mode is composed of pressure pulsation, density pulsation, temperature pulsation and non-rotational speed pulsation in an isentropic state; the vortex mode is composed of rotational velocity pulsation; the entropy mode is composed of entropy pulsation, density pulsation and temperature pulsation in a constant pressure state. The three disturbance modes have different compositions, and the generation mechanisms are different. Generally, a turbulent boundary layer is a main source of an acoustic mode, a honeycomb device, a damping net and the like in a wind tunnel are main sources of a vortex mode, and a non-uniform temperature field in a flow field is a main source of an entropy mode. The three disturbance modes not only have different generation mechanisms, but also have different action mechanisms on the flow phenomenon. For example, Kendall has been published in 1998 to indicate that a rotating component (vortex mode) in a free incoming flow disturbance is a cause for initiating a three-dimensional breaking down process in a boundary layer transition process, a non-rotating component (mainly, an acoustic mode) in the free incoming flow disturbance is a main factor for triggering an initial amplitude of a two-dimensional TS wave, and different disturbance modes have different mechanisms of action on the boundary layer transition, and have different actions in prediction and control of the boundary layer transition.
The analysis can be combined to obtain: in order to accurately and quantitatively analyze the source of different disturbance modes in the wind tunnel and suppress the source, so as to improve the flow field quality of the wind tunnel and improve the accuracy of the test result of the wind tunnel, and in order to accurately and quantitatively analyze the influence mechanism of the different disturbance modes on the flow phenomenon, the different disturbance modes in the wind tunnel test section need to be quantitatively evaluated. At present, a compressible flow velocity region of a subsonic wind tunnel plays an important role in aerodynamic force evaluation and aerodynamic shape refinement design of advanced large-scale aircrafts such as passenger planes, military transport planes, remote strategic bombers, early warning planes and oiling machines, but the precision of a test result cannot be accurately quantified just because a free incoming flow disturbance mode is not quantitatively evaluated.
At present, a calculation method for a measurement result of a compressible fluid disturbance mode of a subsonic wind tunnel is in urgent need of development.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for calculating a measurement result of a compressible fluid disturbance mode of a subsonic wind tunnel.
The method for calculating the measurement result of the compressible fluid disturbance mode of the subsonic wind tunnel comprises the following steps:
a. mounting a one-dimensional hot wire probe on a support rod, fixing the support rod on a clamping mechanism, and mounting the whole clamping mechanism in a subsonic wind tunnel test section to be tested;
b. starting the subsonic wind tunnel to be measured, and measuring the flow field pulsation quantity of the subsonic wind tunnel test section by using a hot wire anemometer under the incoming flow Mach number M to obtain the mass flow pulsation quantity
Figure BDA0002578118500000021
Total temperature pulsation
Figure BDA0002578118500000022
And the cross-correlation quantity of the mass flow pulsation and the total temperature pulsation
Figure BDA0002578118500000023
m is the incoming flow mass flow, T0Delta represents the pulsation value and represents the average value for the total temperature of the incoming flow;
c. the subsonic wind tunnel compressible flow is isentropic flow, and the entropy mode is 0;
d. solving the magnitude of the acoustic mode and the eddy mode, wherein the expression of the acoustic mode and the eddy mode is as follows:
Figure BDA0002578118500000031
Figure BDA0002578118500000032
in the above two formulas, P is an acoustic mode, ω is an eddy mode, γ is a specific heat ratio, α and β are parameters related to mach number and specific heat ratio, and the expression is:
Figure BDA0002578118500000033
Figure BDA0002578118500000034
according to the expression, solving the root mean square value of the acoustic mode and the vortex mode to obtain the magnitude of the acoustic mode and the vortex mode;
e. solving the magnitude of the acoustic modal and the vortex modal component of the basic physical quantity of the flow field, wherein the expression of the velocity pulsation acoustic modal and the vortex modal component is as follows:
Figure BDA0002578118500000035
Figure BDA0002578118500000036
the expression of the total temperature pulsation acoustic mode and the vortex mode component is as follows:
Figure BDA0002578118500000037
Figure BDA0002578118500000038
the density pulsation has only an acoustic modal component, and the expression is as follows:
Figure BDA0002578118500000039
the static temperature pulsation only has an acoustic modal component, and the expression is as follows:
Figure BDA0002578118500000041
in the above formulas, u is the incoming flow velocity, ρ is the incoming flow density, and T is the incoming flow static temperature.
According to the expression, root mean square values of the acoustic modal and the vortex modal components of the basic physical quantity of the flow field are respectively solved, the magnitude values of the acoustic modal and the vortex modal components of the basic physical quantity of the flow field are obtained, and calculation of the measurement result of the compressible fluid disturbance modal of the subsonic wind tunnel is completed.
Further, the step of solving the magnitudes of the acoustic mode and the vortex mode in the step d is as follows:
d1. the fundamental definitions of the acoustic mode and the vortex mode are as follows:
Figure BDA0002578118500000042
Figure BDA0002578118500000043
wherein p is the incoming static pressure and u is the incoming velocity;
d2. the relationship of the mass flow pulsation to the density pulsation and the velocity pulsation is:
Figure BDA0002578118500000044
d3. the relationship between total temperature pulsation and static temperature pulsation and speed pulsation is:
Figure BDA0002578118500000045
d4. the ideal gas state equation pulsating quantity is in the form of:
Figure BDA0002578118500000046
d5. the pulse quantity form of the isentropic relation is as follows:
Figure BDA0002578118500000047
d6. and (3) carrying out simultaneous solution on equations from d2 to d5 to obtain specific expressions of velocity pulsation and pressure pulsation:
Figure BDA0002578118500000048
Figure BDA0002578118500000049
according to the definitions of the acoustic mode and the vortex mode in d1, the specific expressions of the acoustic mode and the vortex mode are obtained as follows:
Figure BDA0002578118500000051
Figure BDA0002578118500000052
further, the step of solving the flow field fundamental physical quantity acoustic modal and vortex modal component magnitudes in the step e is as follows:
e1. the velocity pulsations include an acoustic modal component of the velocity pulsations and a vortex modal component of the velocity pulsations in a relationship as follows:
Figure BDA0002578118500000053
in the formula, a lower subscript P represents an acoustic modal component, and a lower subscript omega represents a vortex modal component;
e2. the total temperature pulsation comprises an acoustic modal component of the total temperature pulsation and a vortex modal component of the total temperature pulsation, and the relation is as follows:
Figure BDA0002578118500000054
e3. according to the expression in d3, the total temperature pulsation acoustic modal component is:
Figure BDA0002578118500000055
in the formula, the relationship between the static temperature pulsating sound mode component and the velocity pulsating sound mode component is as follows:
Figure BDA0002578118500000056
e4. due to the stationary temperature pulsation without eddy modal components, i.e.
Figure BDA0002578118500000057
According to the expression in d3, the total temperature pulsation vortex modal component is:
Figure BDA0002578118500000058
e5. simultaneous solving is carried out on equations in e 1-e 4, and specific expressions of a velocity pulsation acoustic mode and a vortex mode component and a total temperature pulsation acoustic mode and a vortex mode component are obtained according to an expression of velocity pulsation in d6, wherein the specific expressions are as follows:
Figure BDA0002578118500000061
Figure BDA0002578118500000062
Figure BDA0002578118500000063
Figure BDA0002578118500000064
e6. in the isoentropy flow, both the density pulsation and the static temperature pulsation only have an acoustic mode component, the density pulsation and the static temperature pulsation acoustic mode component are corresponding pulsation quantities, and equations from d2 to d5 are solved in a simultaneous mode to obtain specific expressions of the density pulsation and the static temperature pulsation, wherein the specific expressions are as follows:
Figure BDA0002578118500000065
Figure BDA0002578118500000066
the calculation method for the disturbance modal measurement result of the compressible fluid of the subsonic wind tunnel obtains the specific expressions of the disturbance modal, the acoustic modal of the basic physical quantity of the flow field and the vortex modal component in the compressible fluid of the subsonic wind tunnel, and uses the measurement result of the hot wire anemometer to solve the magnitude of the disturbance modal, the acoustic modal of the basic physical quantity of the flow field and the vortex modal component, thereby providing a feasible method for the disturbance modal analysis of the compressible fluid of the subsonic wind tunnel and providing technical support for the flow field quality evaluation of a newly-built wind tunnel.
Drawings
FIG. 1 is a result diagram of mass flow pulsation, total temperature pulsation, and mass flow pulsation and total temperature pulsation cross-correlation quantity obtained by the subsonic wind tunnel compressible fluid disturbance modal measurement result calculation method of the present invention;
FIG. 2 is a diagram of a result of disturbance mode solution obtained by the method for solving a measurement result of a compressible fluid disturbance mode in a subsonic wind tunnel according to the present invention;
FIG. 3 is a result diagram of solving flow field fundamental physical quantity acoustic modal and vortex modal components obtained by the method for solving the measurement result of the compressible fluid disturbance modal in the subsonic wind tunnel.
In the figure: "+" indicates the pulsation of the mass flow at each Mach number
Figure BDA0002578118500000071
The measurement result of (a);
". O" indicates the total temperature pulsation at each Mach number
Figure BDA0002578118500000072
The measurement result of (a);
"+" represents the cross-correlation quantity of the mass flow pulsation and the total temperature pulsation under each Mach number
Figure BDA0002578118500000073
The measurement result of (a);
"x" represents the acoustic modal solution results at each mach number;
"□" represents the result of the vortex mode solution at each mach number;
"it means the solving result of the velocity pulsating vortex modal component at each mach number;
", denotes the velocity pulsation acoustic modal component solution at each mach number;
"Δ" represents the solution result of the total temperature pulsating vortex modal component at each mach number;
". represents the total temperature pulsation acoustic modal component solution at each Mach number;
Figure BDA0002578118500000074
representing the solving result of the density pulsation under each Mach number;
Figure BDA0002578118500000075
and expressing the solution result of the static temperature pulsation under each Mach number.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
The method for calculating the measurement result of the compressible fluid disturbance mode in the subsonic wind tunnel according to the embodiment is specifically explained by a disturbance mode measurement test performed in a probe calibration wind tunnel.
The method for calculating the measurement result of the compressible fluid disturbance mode of the subsonic wind tunnel comprises the following steps:
a. installing a one-dimensional hot wire probe on a supporting rod, fixing the supporting rod on a clamping mechanism, and installing the whole clamping mechanism in a probe calibration wind tunnel test section;
b. starting a probe calibration wind tunnel, and measuring the pulsating quantity of the flow field by using a hot-wire anemometer under the condition that the Mach number M of the incoming flow is 0.330, 0.420, 0.525, 0.627 and 0.719 to obtain the pulsating quantity of the mass flow
Figure BDA0002578118500000081
Total temperature pulsation
Figure BDA0002578118500000082
Mass flow pulsation and total temperature pulsation cross correlation quantity
Figure BDA0002578118500000083
The results are shown in FIG. 1, where m is the incoming mass flow, T0The total temperature of the incoming flow;
c. the subsonic wind tunnel compressible flow is isentropic flow, and the entropy mode is 0;
d. solving the magnitude of the acoustic mode and the eddy mode, wherein the expression of the acoustic mode and the eddy mode is as follows:
Figure BDA0002578118500000084
Figure BDA0002578118500000085
in the above two formulas, P is an acoustic mode, ω is an eddy mode, γ is a specific heat ratio, α and β are parameters related to mach number and specific heat ratio, and the expression is:
Figure BDA0002578118500000086
Figure BDA0002578118500000087
according to the expression, solving the root mean square value of the acoustic mode and the vortex mode to obtain the magnitude values of the acoustic mode and the vortex mode, wherein the result is shown in fig. 2;
e. solving the magnitude of the acoustic modal and the vortex modal component of the basic physical quantity of the flow field, wherein the expression of the velocity pulsation acoustic modal and the vortex modal component is as follows:
Figure BDA0002578118500000088
Figure BDA0002578118500000089
the expression of the total temperature pulsation acoustic mode and the vortex mode component is as follows:
Figure BDA0002578118500000091
Figure BDA0002578118500000092
the density pulsation has only an acoustic modal component, and the expression is as follows:
Figure BDA0002578118500000093
the static temperature pulsation only has an acoustic modal component, and the expression is as follows:
Figure BDA0002578118500000094
in the above formulas, u is the incoming flow velocity, ρ is the incoming flow density, and T is the incoming flow static temperature.
According to the expression, root mean square values of the acoustic modal and the vortex modal components of the basic physical quantity of the flow field are respectively solved, the magnitude values of the acoustic modal and the vortex modal components of the basic physical quantity of the flow field are obtained, the result is shown in fig. 3, and calculation of the measurement result of the compressible fluid disturbance modal of the subsonic wind tunnel is completed.
Further, the step of solving the magnitudes of the acoustic mode and the vortex mode in the step d is as follows:
d1. the fundamental definitions of the acoustic mode and the vortex mode are as follows:
Figure BDA0002578118500000095
Figure BDA0002578118500000096
wherein p is the incoming static pressure and u is the incoming velocity;
d2. the relationship of the mass flow pulsation to the density pulsation and the velocity pulsation is:
Figure BDA0002578118500000097
d3. the relationship between total temperature pulsation and static temperature pulsation and speed pulsation is:
Figure BDA0002578118500000098
d4. the ideal gas state equation pulsating quantity is in the form of:
Figure BDA0002578118500000101
d5. the pulse quantity form of the isentropic relation is as follows:
Figure BDA0002578118500000102
d6. and (3) carrying out simultaneous solution on equations from d2 to d5 to obtain specific expressions of velocity pulsation and pressure pulsation:
Figure BDA0002578118500000103
Figure BDA0002578118500000104
according to the definitions of the acoustic mode and the vortex mode in d1, the specific expressions of the acoustic mode and the vortex mode are obtained as follows:
Figure BDA0002578118500000105
Figure BDA0002578118500000106
further, the step of solving the flow field fundamental physical quantity acoustic modal and vortex modal component magnitudes in the step e is as follows:
e1. the velocity pulsations include an acoustic modal component of the velocity pulsations and a vortex modal component of the velocity pulsations in a relationship as follows:
Figure BDA0002578118500000107
in the formula, a lower subscript P represents an acoustic modal component, and a lower subscript omega represents a vortex modal component;
e2. the total temperature pulsation comprises an acoustic modal component of the total temperature pulsation and a vortex modal component of the total temperature pulsation, and the relation is as follows:
Figure BDA0002578118500000108
e3. according to the expression in d3, the total temperature pulsation acoustic modal component is:
Figure BDA0002578118500000111
in the formula, the relationship between the static temperature pulsating sound mode component and the velocity pulsating sound mode component is as follows:
Figure BDA0002578118500000112
e4. due to the stationary temperature pulsation without eddy modal components, i.e.
Figure BDA0002578118500000113
According to the expression in d3, the total temperature pulsation vortex modal component is:
Figure BDA0002578118500000114
e5. simultaneous solving is carried out on equations in e 1-e 4, and specific expressions of a velocity pulsation acoustic mode and a vortex mode component and a total temperature pulsation acoustic mode and a vortex mode component are obtained according to an expression of velocity pulsation in d6, wherein the specific expressions are as follows:
Figure BDA0002578118500000115
Figure BDA0002578118500000116
Figure BDA0002578118500000117
Figure BDA0002578118500000118
e6. in the isoentropy flow, both the density pulsation and the static temperature pulsation only have an acoustic mode component, the density pulsation and the static temperature pulsation acoustic mode component are corresponding pulsation quantities, and equations from d2 to d5 are solved in a simultaneous mode to obtain specific expressions of the density pulsation and the static temperature pulsation, wherein the specific expressions are as follows:
Figure BDA0002578118500000119
Figure BDA00025781185000001110
the results prove the feasibility of measuring and solving the subsonic wind tunnel compressible fluid disturbance mode, the flow field basic physical quantity acoustic mode and the vortex mode component by applying the method for solving the measurement results of the subsonic wind tunnel compressible fluid disturbance mode, and provide technical support for the flow field quality evaluation of a newly-built wind tunnel.

Claims (1)

1. A calculation method for measuring results of a disturbance modal of a compressible fluid of a subsonic wind tunnel is characterized in that the calculation method for measuring results obtains specific expressions of a disturbance modal and a flow field basic physical quantity acoustic modal and a vortex modal component in the compressible fluid of the subsonic wind tunnel, and the measurement results of a hot wire anemometer are utilized to solve the values of the disturbance modal and the flow field basic physical quantity acoustic modal and the vortex modal component;
the measurement result calculating method comprises the following steps:
a. mounting a one-dimensional hot wire probe on a support rod, fixing the support rod on a clamping mechanism, and mounting the whole clamping mechanism in a subsonic wind tunnel test section to be tested;
b. starting the subsonic wind tunnel to be measured, and measuring the flow field pulsation quantity of the subsonic wind tunnel test section by using a hot wire anemometer under the incoming flow Mach number M to obtain the mass flow pulsation quantity
Figure FDA0003543825930000011
Total temperature pulsation
Figure FDA0003543825930000012
And the cross-correlation quantity of the mass flow pulsation and the total temperature pulsation
Figure FDA0003543825930000013
m is the incoming flow mass flow, T0For the total temperature of the incoming flow, Δ represents the pulsation value,-represents the average value;
c. the subsonic wind tunnel compressible flow is isentropic flow, and the entropy mode is 0;
d. solving the magnitude of the acoustic mode and the eddy mode, wherein the expression of the acoustic mode and the eddy mode is as follows:
Figure FDA0003543825930000014
Figure FDA0003543825930000015
in the two formulas, P is an acoustic mode, omega is an eddy mode, gamma is a specific heat ratio, alpha and beta are parameters related to Mach number and the specific heat ratio, and the expression is as follows:
Figure FDA0003543825930000016
Figure FDA0003543825930000017
according to the expression, solving the root mean square value of the acoustic mode and the vortex mode to obtain the magnitude of the acoustic mode and the vortex mode;
d1. the fundamental definitions of the acoustic mode and the vortex mode are as follows:
Figure FDA0003543825930000021
Figure FDA0003543825930000022
wherein p is the incoming static pressure and u is the incoming velocity;
d2. the relationship of the mass flow pulsation to the density pulsation and the velocity pulsation is:
Figure FDA0003543825930000023
d3. the relationship between total temperature pulsation and static temperature pulsation and speed pulsation is:
Figure FDA0003543825930000024
d4. the ideal gas state equation pulsating quantity is in the form of:
Figure FDA0003543825930000025
d5. the pulse quantity form of the isentropic relation is as follows:
Figure FDA0003543825930000026
d6. and (3) carrying out simultaneous solution on equations from d2 to d5 to obtain specific expressions of velocity pulsation and pressure pulsation:
Figure FDA0003543825930000027
Figure FDA0003543825930000028
according to the definitions of the acoustic mode and the vortex mode in d1, the specific expressions of the acoustic mode and the vortex mode are obtained as follows:
Figure FDA0003543825930000029
Figure FDA00035438259300000210
e. solving the magnitude of the acoustic modal and the vortex modal component of the basic physical quantity of the flow field, wherein the expression of the velocity pulsation acoustic modal and the vortex modal component is as follows:
Figure FDA0003543825930000031
Figure FDA0003543825930000032
the expression of the total temperature pulsation acoustic mode and the vortex mode component is as follows:
Figure FDA0003543825930000033
Figure FDA0003543825930000034
the density pulsation has only an acoustic modal component, and the expression is as follows:
Figure FDA0003543825930000035
the static temperature pulsation only has an acoustic modal component, and the expression is as follows:
Figure FDA0003543825930000036
in the above formulas, u is the incoming flow velocity, ρ is the incoming flow density, and T is the incoming flow static temperature;
according to the expression, root mean square values of the acoustic modal and the vortex modal components of the basic physical quantity of the flow field are respectively solved, the magnitude values of the acoustic modal and the vortex modal components of the basic physical quantity of the flow field are obtained, and calculation of a measurement result of the compressible fluid disturbance modal of the subsonic wind tunnel is completed;
e1. the velocity pulsations include an acoustic modal component of the velocity pulsations and a vortex modal component of the velocity pulsations in a relationship as follows:
Figure FDA0003543825930000037
in the formula, a lower subscript P represents an acoustic modal component, and a lower subscript omega represents a vortex modal component;
e2. the total temperature pulsation comprises an acoustic modal component of the total temperature pulsation and a vortex modal component of the total temperature pulsation, and the relation is as follows:
Figure FDA0003543825930000041
e3. according to the expression in d3, the total temperature pulsation acoustic modal component is:
Figure FDA0003543825930000042
in the formula, the relationship between the static temperature pulsating sound mode component and the velocity pulsating sound mode component is as follows:
Figure FDA0003543825930000043
e4. due to the stationary temperature pulsation without eddy modal components, i.e.
Figure FDA0003543825930000044
According to the expression in d3, the total temperature pulsation vortex modal component is:
Figure FDA0003543825930000045
e5. simultaneous solving is carried out on equations in e 1-e 4, and specific expressions of a velocity pulsation acoustic mode and a vortex mode component and a total temperature pulsation acoustic mode and a vortex mode component are obtained according to an expression of velocity pulsation in d6, wherein the specific expressions are as follows:
Figure FDA0003543825930000046
Figure FDA0003543825930000047
Figure FDA0003543825930000048
Figure FDA0003543825930000049
e6. in the isoentropy flow, both the density pulsation and the static temperature pulsation only have an acoustic mode component, the density pulsation and the static temperature pulsation acoustic mode component are corresponding pulsation quantities, and equations from d2 to d5 are solved in a simultaneous mode to obtain specific expressions of the density pulsation and the static temperature pulsation, wherein the specific expressions are as follows:
Figure FDA00035438259300000410
Figure FDA00035438259300000411
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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002148141A (en) * 2000-11-14 2002-05-22 Mitsubishi Heavy Ind Ltd Device and method for wind tunnel test
CN107782523A (en) * 2017-10-31 2018-03-09 中国空气动力研究与发展中心高速空气动力研究所 A kind of new cavity modal noise standing wave decomposition method
CN108225717A (en) * 2017-12-15 2018-06-29 中国航空工业集团公司沈阳空气动力研究所 Flow resistance force measuring method in a kind of wind tunnel test
CN110455490A (en) * 2019-08-21 2019-11-15 中国人民解放军国防科技大学 Method and device for calculating supersonic velocity and hypersonic velocity wind tunnel flow field turbulence

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002148141A (en) * 2000-11-14 2002-05-22 Mitsubishi Heavy Ind Ltd Device and method for wind tunnel test
CN107782523A (en) * 2017-10-31 2018-03-09 中国空气动力研究与发展中心高速空气动力研究所 A kind of new cavity modal noise standing wave decomposition method
CN108225717A (en) * 2017-12-15 2018-06-29 中国航空工业集团公司沈阳空气动力研究所 Flow resistance force measuring method in a kind of wind tunnel test
CN110455490A (en) * 2019-08-21 2019-11-15 中国人民解放军国防科技大学 Method and device for calculating supersonic velocity and hypersonic velocity wind tunnel flow field turbulence

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
变热线过热比可压缩流湍流度测量方法优化;杜钰锋 等;《航空学报》;20191231;第40卷(第12期);第50-58页 *
高超声速风洞来流扰动测量及数据后处理技术研究;余涛 等;《实验流体力学》;20191231;第33卷(第5期);第50-57页 *

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