CN111766039A - Method for calculating measurement result of compressible fluid disturbance mode of subsonic wind tunnel - Google Patents
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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
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 quantityTotal temperature pulsationAnd the cross-correlation quantity of the mass flow pulsation and the total temperature pulsationm 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:
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:
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:
the expression of the total temperature pulsation acoustic mode and the vortex mode component is as follows:
the density pulsation has only an acoustic modal component, and the expression is as follows:
the static temperature pulsation only has an acoustic modal component, and the expression is as follows:
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:
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:
d3. the relationship between total temperature pulsation and static temperature pulsation and speed pulsation is:
d4. the ideal gas state equation pulsating quantity is in the form of:
d5. the pulse quantity form of the isentropic relation is as follows:
d6. and (3) carrying out simultaneous solution on equations from d2 to d5 to obtain specific expressions of velocity pulsation and pressure pulsation:
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:
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:
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:
e3. according to the expression in d3, the total temperature pulsation acoustic modal component is:
in the formula, the relationship between the static temperature pulsating sound mode component and the velocity pulsating sound mode component is as follows:
e4. due to the stationary temperature pulsation without eddy modal components, i.e.According to the expression in d3, the total temperature pulsation vortex modal component is:
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:
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:
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 numberThe measurement result of (a);
"+" represents the cross-correlation quantity of the mass flow pulsation and the total temperature pulsation under each Mach numberThe 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;
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 flowTotal temperature pulsationMass flow pulsation and total temperature pulsation cross correlation quantityThe 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:
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:
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:
the expression of the total temperature pulsation acoustic mode and the vortex mode component is as follows:
the density pulsation has only an acoustic modal component, and the expression is as follows:
the static temperature pulsation only has an acoustic modal component, and the expression is as follows:
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:
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:
d3. the relationship between total temperature pulsation and static temperature pulsation and speed pulsation is:
d4. the ideal gas state equation pulsating quantity is in the form of:
d5. the pulse quantity form of the isentropic relation is as follows:
d6. and (3) carrying out simultaneous solution on equations from d2 to d5 to obtain specific expressions of velocity pulsation and pressure pulsation:
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:
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:
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:
e3. according to the expression in d3, the total temperature pulsation acoustic modal component is:
in the formula, the relationship between the static temperature pulsating sound mode component and the velocity pulsating sound mode component is as follows:
e4. due to the stationary temperature pulsation without eddy modal components, i.e.According to the expression in d3, the total temperature pulsation vortex modal component is:
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:
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:
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 (3)
1. A calculation method for measurement results of a compressible fluid disturbance mode of a subsonic wind tunnel is characterized by comprising 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 quantityTotal temperature pulsationAnd the cross-correlation quantity of the mass flow pulsation and the total temperature pulsationm 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:
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:
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:
the expression of the total temperature pulsation acoustic mode and the vortex mode component is as follows:
the density pulsation has only an acoustic modal component, and the expression is as follows:
the static temperature pulsation only has an acoustic modal component, and the expression is as follows:
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.
2. The method for calculating the measurement result of the subsonic wind tunnel compressible fluid disturbance mode according to claim 1, wherein the step of calculating the values of the acoustic mode and the vortex mode in step d is as follows:
d1. the fundamental definitions of the acoustic mode and the vortex mode are as follows:
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:
d3. the relationship between total temperature pulsation and static temperature pulsation and speed pulsation is:
d4. the ideal gas state equation pulsating quantity is in the form of:
d5. the pulse quantity form of the isentropic relation is as follows:
d6. and (3) carrying out simultaneous solution on equations from d2 to d5 to obtain specific expressions of velocity pulsation and pressure pulsation:
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:
3. the subsonic wind tunnel compressible fluid disturbance modal measurement result calculation method according to claims 1 and 2, characterized in that the step of calculating the flow field fundamental physical quantity acoustic modal and vortex modal component magnitudes in 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:
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:
e3. according to the expression in d3, the total temperature pulsation acoustic modal component is:
in the formula, the relationship between the static temperature pulsating sound mode component and the velocity pulsating sound mode component is as follows:
e4. due to the stationary temperature pulsation without eddy modal components, i.e.According to the expression in d3, the total temperature pulsation vortex modal component is:
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:
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:
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