CN113065201B - Radiation balance temperature calculation method considering slip correction - Google Patents

Radiation balance temperature calculation method considering slip correction Download PDF

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CN113065201B
CN113065201B CN202110497667.7A CN202110497667A CN113065201B CN 113065201 B CN113065201 B CN 113065201B CN 202110497667 A CN202110497667 A CN 202110497667A CN 113065201 B CN113065201 B CN 113065201B
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slip
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gas
radiation balance
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CN113065201A (en
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丁明松
江涛
陈坚强
刘庆宗
董维中
高铁锁
傅杨奥骁
李鹏
郭勇颜
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Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
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Abstract

The invention discloses a radiation balance temperature calculation method considering slip correction, which is mainly used for a coupling treatment process of a slip temperature boundary and a wall radiation balance temperature boundary in a hypersonic slip flow process based on numerical simulation of a Navier-Stokes control equation set. According to the method, on the basis of a traditional radiation balance energy equation, wall surface gas rarefied slip temperature correction is introduced to form a slip temperature-based radiation balance equation, the slip temperature radiation balance equation is solved through implicit iteration to obtain gas slip temperature, and wall surface radiation balance temperature distribution is obtained through a surface temperature slip relation. The method is well compatible with two physical mechanisms of surface radiation energy balance and surface temperature rarefied slip effect, and has good calculation stability and rapid convergence.

Description

Radiation balance temperature calculation method considering slip correction
Technical Field
The invention relates to the field of numerical simulation calculation, in particular to a calculation method of hypersonic rarefied slip flow wall radiation balance temperature.
Background
The wall radiation balance temperature condition and the surface gas temperature slip condition are two temperature boundary conditions commonly used in the hypersonic flow simulation. For these two boundary conditions, separate studies are common: when the wall radiation equilibrium temperature condition is used, the rarefied slip effect of the surface gas is usually ignored, namely the surface gas temperature is considered to be the same as the wall temperature; when the surface gas temperature slip effect is considered, generally, an isothermal wall surface condition, that is, a wall surface temperature is a certain fixed temperature condition. The comprehensive utilization of the two is rare.
With the increase of the flying speed and the flying height, under the condition of high altitude and high enthalpy, the wall temperature of the aircraft is often close to the radiation equilibrium temperature, and meanwhile, the temperature slip phenomenon exists in the surface gas of the aircraft (the flying height is generally considered to appear above 60 km). When the high-altitude high-enthalpy hypersonic flow is finely simulated, the two physical mechanisms need to be considered simultaneously.
Generally, the wall radiation equilibrium temperature can be obtained by iteratively solving an energy radiation equilibrium equation of the wall temperature, and the surface gas slip temperature is given by the wall temperature and the surface gas temperature gradient through a gas slip model, so the calculation sequence of the wall radiation equilibrium temperature and the surface gas temperature is usually that the wall temperature is calculated by the energy radiation equilibrium equation first, and then the gas slip temperature is calculated by the wall temperature through the slip model.
The method is suitable for decoupling calculation of hypersonic rarefied slip flow and wall radiation balance temperature, but non-physical oscillation, non-convergence and even divergence are easy to occur in the numerical simulation process of coupling the hypersonic rarefied slip flow and the wall radiation balance temperature. The method is mainly characterized in that in each step of solving process of the flow control N-S equation, the value of a non-boundary point infinitesimal in a flow field is obtained by calculation of the N-S equation, so that the temperature of the wall surface sublayer grid infinitesimal is a known definite value when the wall surface temperature boundary condition is processed. At this time, in the process of solving the energy radiation balance equation of the wall temperature boundary processing, if the wall temperature generates non-physical fluctuation due to some reason (such as numerical error), the fluctuation is transmitted to the gas slip temperature through the slip relation, so that the slip temperature generates fluctuation; the temperature of the wall surface sub-layer micro element is a determined value, and the normal distance of the wall surface of the first layer is extremely small, so that the heat flow of the wall surface is severely fluctuated; the violent fluctuation of the heat flow adversely affects the solution of the energy radiation balance equation, so that the non-physical fluctuation is fed back and amplified rapidly, and even the calculation is invalid and dispersed.
Therefore, it is still necessary to develop a more efficient and stable wall radiation balance temperature calculation method considering the slip correction.
Disclosure of Invention
The invention aims to solve the slip temperature radiation balance equation through implicit iteration to obtain the gas slip temperature, avoid the problem of error iteration feedback amplification of the traditional method, obtain the wall radiation balance temperature distribution through the surface temperature slip relation through reverse calculation, and be compatible with two physical mechanisms of surface radiation energy balance and surface temperature rarefaction slip effect.
In order to achieve the purpose, the invention adopts the following technical scheme:
the method comprises the following steps: acquiring initial values of the temperature of the wall surface grid infinitesimal elements, the initial value of the gas slip temperature, the temperature of the wall surface sublayer infinitesimal elements and related quantities thereof in the numerical simulation process;
step two: judging a flow field area needing iterative computation;
step three: constructing a radiation balance equation based on the slip temperature for a flow field region needing iteration, and calculating the slip temperature through implicit iteration;
step four: judging whether the iteration converges;
step five: and repeating the third step and the fourth step until iteration convergence to obtain the gas slip temperature, and calculating to obtain the wall surface temperature according to the wall surface gas temperature slip relation.
The method is mainly used for processing the wall temperature boundary in the hypersonic speed slip flow numerical simulation process, wherein the flow numerical simulation control equation is a Navier-Stokes equation set considering the slip effect.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the invention is better compatible with two physical mechanisms of surface radiation energy balance and surface temperature rarefaction sliding effect, and realizes the coupling treatment of the sliding temperature boundary and the wall radiation balance temperature boundary.
According to the invention, on the basis of the traditional radiation balance energy equation, wall gas rarefied slip temperature correction is introduced to form a slip temperature-based radiation balance equation, and the equation comprehensively represents the energy balance relationship among slip temperature, surface heat flow and surface radiation, so that the problem of error iterative feedback amplification of the traditional method is avoided.
According to the method, the radiation energy is subjected to implicit treatment to form the implicit iterative calculation method of the slip temperature radiation balance equation, so that the problem of poor iterative stability caused by 'drastic change of radiation energy along with temperature' is solved.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a calculation flow of the present solution;
FIG. 2 is a schematic diagram of an example reflector profile;
FIG. 3 is an example of heat flow calculated using the present invention compared to literature;
FIG. 4 is an example of wall radiation equilibrium temperature and gas slip temperature calculated using the present invention.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
As shown in fig. 1, it is a calculation flow of the present embodiment, taking "complete gas lean slip flow radiation balance boundary processing considering Maxwell classical slip model" as an example, to explain its specific implementation process:
step S1: in thatIn the hypersonic speed slippage flow numerical simulation process, the initial value of the wall surface temperature on the wall surface grid infinitesimal is obtained
Figure DEST_PATH_IMAGE001
Initial value of gas slip temperature
Figure 716320DEST_PATH_IMAGE002
And a gas temperature corresponding to wall normal sublayer microelements of
Figure DEST_PATH_IMAGE003
；
The control equation is mainly aimed at the hypersonic flow numerical simulation of a Navier-Stokes equation set considering the slip effect. At the beginning of the propulsion process of each time step of the control equation, the initial value of the wall temperature on the wall grid infinitesimal
Figure 525138DEST_PATH_IMAGE001
And initial value of gas slip temperature
Figure 304876DEST_PATH_IMAGE002
All known conditions (given by the advance of the previous step); after discrete calculation of a control equation, the gas temperature of the wall normal sublayer infinitesimal can be obtained
Figure 700085DEST_PATH_IMAGE003
. In the process, a wall temperature boundary meeting two physical mechanisms of 'surface radiation energy balance' and 'surface temperature rarefaction slip effect', namely the wall temperature, needs to be obtained
Figure 639091DEST_PATH_IMAGE004
And gas slip temperature
Figure DEST_PATH_IMAGE005
And (4) distribution for further advancement of the flow control equation set. Therefore, the calculation of the present embodiment is mainly used for: by
Figure 822073DEST_PATH_IMAGE006
、
Figure DEST_PATH_IMAGE007
、
Figure 89106DEST_PATH_IMAGE003
Obtaining the gas slip temperature simultaneously meeting the two physical mechanisms through iterative calculation under the known conditions
Figure 678219DEST_PATH_IMAGE008
And wall temperature
Figure DEST_PATH_IMAGE009
。
Step S2: judging whether iterative computation is needed or not according to the ratio of the allowance of a temperature slip equation and a surface energy radiation balance equation on the grid infinitesimal to the size of the iterative computation precision requirement;
when the grid infinitesimal satisfies
Figure 707617DEST_PATH_IMAGE010
Then on the infinitesimal
Figure 700981DEST_PATH_IMAGE006
、
Figure 455311DEST_PATH_IMAGE007
、
Figure 582536DEST_PATH_IMAGE003
The calculation accuracy requirement of simultaneously meeting the temperature slip relation and the surface energy radiation balance equation is met, namely two physical mechanisms of 'surface radiation energy balance' and 'surface temperature rarefied slip effect' are simultaneously met, so that iterative calculation is not needed, and the gas slip temperature is not needed
Figure 105921DEST_PATH_IMAGE011
Wall surface temperature
Figure 161864DEST_PATH_IMAGE012
. Otherwise, when the grid infinitesimal satisfies
Figure 403489DEST_PATH_IMAGE013
Then, iterative calculation and setting are required
Figure 537667DEST_PATH_IMAGE007
For initial values calculated for iterations, i.e. at the number of iterations
Figure 181138DEST_PATH_IMAGE014
When the temperature of the water is higher than the set temperature,
Figure DEST_PATH_IMAGE015
. Here, theR 1 Is the margin of the temperature slip equation,R 2 the balance of the surface energy radiation balance equation.
The reason why it is determined whether iteration is necessary in step S2 is because of the fact that the control equation advances on the grid elements
Figure 407982DEST_PATH_IMAGE006
、
Figure 136904DEST_PATH_IMAGE007
The equivalent is obtained by iterative calculation of the advance of one time step on the flow control equation, so that the temperature slip equation and the surface energy radiation balance equation can be directly satisfied, an iterative calculation process is not required, and the calculation amount can be reduced. As the control equation continues to advance, the flow field gradually tends to be stable, and the "calculation-free" area may also be increased, so that the calculation amount is further reduced.
Wherein the margin of the temperature slip equation
Figure 340352DEST_PATH_IMAGE016
In this example, it can be derived from the Maxwell classic slip model. Neglecting the effect of thermal creep, the first order form of the slip temperature condition in the Maxwell classical slip model is:
Figure DEST_PATH_IMAGE017
wherein
Figure 838330DEST_PATH_IMAGE008
Is the gas slip temperature, and is,
Figure 970496DEST_PATH_IMAGE018
is the normal gradient of the gas temperature wall surface,
Figure 921135DEST_PATH_IMAGE009
the temperature of the wall surface is used as the temperature of the wall surface,
Figure DEST_PATH_IMAGE019
pr is the Plantt number, which is the gas specific heat ratio,
Figure 193853DEST_PATH_IMAGE020
is the thermal coordination coefficient.
Figure DEST_PATH_IMAGE021
Is the local gas molecular free path, which is generally of the form:
Figure 742794DEST_PATH_IMAGE022
here, the
Figure DEST_PATH_IMAGE023
Respectively gas viscosity coefficient, gas density and gas universal constant.
The temperature slip equation can be obtained from the two formulas:
Figure 75555DEST_PATH_IMAGE024
here, the slip correction function is according to Maxwell classical slip model in the form:
Figure DEST_PATH_IMAGE025
normally, the wall pressure of the hypersonic flow field
Figure 513490DEST_PATH_IMAGE026
Satisfy the requirement of
Figure DEST_PATH_IMAGE027
The conditions, and therefore the wall pressure, are primarily influenced by the flow field structure and are relatively less influenced by the wall gas temperature. In this example, from the complete gas state equation,
Figure 560205DEST_PATH_IMAGE028
it is known that the gas density at the wall surface is relatively greatly affected by the wall surface gas temperature. Therefore, to better characterize the wall gas glide temperature pairMBy substituting the above formula, the influence of (2) is obtainedMAboutp、T s The functional form of the variables is equal to,
Figure 891829DEST_PATH_IMAGE029
the temperature slip equation is subjected to first order dispersion and substituted into
Figure 5279DEST_PATH_IMAGE030
To obtain the balance of the equation
Figure 822187DEST_PATH_IMAGE031
Wherein
Figure 46495DEST_PATH_IMAGE032
Is the normal spacing of the first layer of wall mesh. It can be seen that when
Figure 107992DEST_PATH_IMAGE033
When the voltage of the power supply approaches to 0,
Figure 516977DEST_PATH_IMAGE034
the temperature slip equation is approximately satisfied.
Balance of surface energy radiation balance equation
Figure 929504DEST_PATH_IMAGE035
And the surface infinitesimal radiation energy balance equation can be obtained. Constructing infinite thin patch infinitesimal on the wall surface, and obtaining a radiation energy balance equation according to the energy conservation relation
Figure 318022DEST_PATH_IMAGE036
Wherein
Figure 499605DEST_PATH_IMAGE037
In order to obtain a thermal conductivity coefficient of the gas,
Figure 79491DEST_PATH_IMAGE038
is the coefficient of surface emissivity of the material,
Figure 979313DEST_PATH_IMAGE039
is the stefan-boltzmann constant,
Figure 545424DEST_PATH_IMAGE040
is the radiant energy from the wall.
Figure 207612DEST_PATH_IMAGE041
The heat flow term which is not directly related to the wall temperature is determined by the actual surface physical mechanism, including but not limited to single or more of surface component diffusion heat flow, wall mass induced energy flux and wall mechanical loss energy flux, and the heat flow term in the formula is eliminated
Figure 568186DEST_PATH_IMAGE042
Then the radiant energy balance equation can be written in a form without differentiation:
Figure DEST_PATH_IMAGE043
will be provided with
Figure 345518DEST_PATH_IMAGE001
、
Figure 715319DEST_PATH_IMAGE002
Substituting the formula to obtain the equation allowance
Figure 232014DEST_PATH_IMAGE044
It can be seen that when
Figure DEST_PATH_IMAGE045
When the voltage of the power supply approaches to 0,
Figure 888123DEST_PATH_IMAGE006
、
Figure 496959DEST_PATH_IMAGE007
the equality approximately satisfies the radiation balance energy equation.
Step S3, introducing wall gas rarefied slip temperature correction to flow field grid infinitesimal needing iterative computation on the basis of a traditional energy radiation balance equation to obtain an energy radiation balance equation based on slip temperature, and implicitly iteratively computing the slip temperature:
Figure 562129DEST_PATH_IMAGE046
Figure DEST_PATH_IMAGE047
in order to be able to iterate the number of steps,
Figure 572810DEST_PATH_IMAGE048
and
Figure DEST_PATH_IMAGE049
are respectively the first iteration
Figure 665400DEST_PATH_IMAGE047
And
Figure 387631DEST_PATH_IMAGE050
the glide temperature of the step.
The construction method of the iterative relationship is described here. By eliminating wall temperature in the radiation energy balance equation
Figure 99235DEST_PATH_IMAGE009
To obtain a radiation balance equation related to the slip temperature
Figure DEST_PATH_IMAGE051
The radiant energy of the right-hand term of the above equation is recorded
Figure 89056DEST_PATH_IMAGE052
Its first derivative is of the form
Figure DEST_PATH_IMAGE053
The radiation balance equation for slip temperature can be written as:
Figure 588433DEST_PATH_IMAGE054
carrying out iterative implicit processing on the conduction heat flow and radiation energy items in the formula to obtain an implicit equation form:
Figure DEST_PATH_IMAGE055
energy term of radiation
Figure 171861DEST_PATH_IMAGE056
In that
Figure 811790DEST_PATH_IMAGE048
Is subjected to Taylor expansion
Figure DEST_PATH_IMAGE057
Here, the
Figure 423162DEST_PATH_IMAGE058
If the high order infinitesimal quantities are ignored
Figure 732921DEST_PATH_IMAGE059
Then, the above formula is rewritten as:
Figure 662700DEST_PATH_IMAGE060
combining the above formula by substitution to obtain:
Figure 716106DEST_PATH_IMAGE062
substituting the above formula into implicit equation form, and obtaining by spatial first-order dispersion
Figure 555886DEST_PATH_IMAGE064
And further sorting the above formula to obtain a formula for implicit iterative calculation of the slip temperature.
Because the iterative synthesis of the formula for implicitly and iteratively calculating the slip temperature represents the energy balance relationship among the slip temperature, the surface heat flow and the surface radiation, the problem of error iterative feedback amplification of the traditional method is avoided. Meanwhile, the formula for implicitly calculating the slip temperature performs implicit treatment on the radiation energy to form an implicit iterative calculation method of a slip temperature radiation balance equation, so that the problem of poor iteration stability caused by 'the radiation energy is in' severe change of 4 th power of the temperature 'along with the change of the temperature' is solved.
Step S4: judging whether the iteration of the (m + 1) th step is converged according to the ratio of the iteration residual on the grid infinitesimal to the iteration calculation precision requirement;
iterative residual satisfy
Figure 928224DEST_PATH_IMAGE065
Then, the infinitesimal iterative computation converges;
when in use
Figure 220665DEST_PATH_IMAGE066
Then the infinitesimal iterative computation is not converged, and the next iteration is carried out, namely
Figure 202396DEST_PATH_IMAGE067
Returning to step S3.
Step S5: repeating the iteration of S3 and S4 until the calculation is converged to obtain the gas slip temperature, and then obtaining the wall gas temperature slip relation
Figure 896683DEST_PATH_IMAGE068
And calculating to obtain the distribution of the wall radiation equilibrium temperature.
The wall gas temperature slip relation is obtained by the first-order dispersion of the temperature slip equation space.
The first embodiment is as follows: and (3) numerical simulation of coupling of the non-equilibrium lean slip flow of the reflector and the surface radiation balance. The reflector profile is shown in FIG. 2, and the calculated simulation state is the flying height of 85km and the incoming flow velocity of 7600.0 m/s. The high-temperature gas model is a 5-component air chemical reaction Park model and a single-temperature model, and the slip model is a classical Maxwell slip model; aircraft surface fully catalyzed conditions (FCW) and fully uncatalyzed conditions (NCW).
FIG. 3 shows a comparison of the results of the calculations using the present invention with the literature (Votta R, Schettino A, Ranuzzi G, Borrelli S, Hypersonic low-intensity aerothermo-dynamics of orion-like expression vector [ J ]. Journal of Spacecraft and Rockets, 2009, 4(46): 781-787). It can be seen that the heat flow results are closer to the DSMC results.
FIG. 4 shows an example of wall radiation equilibrium temperature and wall gas slip temperature distributions calculated using the present invention. It can be seen that the temperature distribution calculated by the invention is smooth and flat, and no non-physical numerical oscillation occurs. This shows that the invention can stably realize the numerical simulation of the coupling of two physical mechanisms of 'nonequilibrium rarefied slip flow' and 'surface radiation balance'. As can also be seen, the literature, using the wall temperature setting (1184K), only approximates the wall thermal equilibrium situation to a certain extent.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.

Claims (5)

1. A radiation balance temperature calculation method considering slip correction is characterized in that wall surface gas rarefied slip temperature correction is introduced on the basis of a traditional energy radiation balance equation to obtain an energy radiation balance equation based on slip temperature, the energy radiation balance equation based on slip temperature is solved through implicit iteration to obtain gas slip temperature, and wall surface radiation balance temperature distribution is obtained through a gas temperature slip relation, and the method comprises the following steps:
s1: in the hypersonic speed slip flow numerical simulation process, the initial value of the wall surface temperature on the wall surface grid infinitesimal is obtained
Figure 447194DEST_PATH_IMAGE001
Initial value of gas slip temperature
Figure 789182DEST_PATH_IMAGE002
And a gas temperature corresponding to wall normal sublayer microelements of
Figure 199435DEST_PATH_IMAGE003
；
S2: the allowance of the temperature slip equation on the grid infinitesimal is as follows:
Figure 732791DEST_PATH_IMAGE004
，
the balance of the surface energy radiation balance equation is:
Figure 595705DEST_PATH_IMAGE005
，
when the grid infinitesimal satisfies
Figure 6964DEST_PATH_IMAGE007
In time, iterative calculation is required, and the number of iterations is
Figure 694559DEST_PATH_IMAGE008
When the temperature of the water is higher than the set temperature,
Figure 992292DEST_PATH_IMAGE009
；
when the grid infinitesimal satisfies
Figure 201557DEST_PATH_IMAGE010
Without iterative calculation, i.e. gas slip temperature
Figure 652392DEST_PATH_IMAGE011
Wall radiation equilibrium temperature
Figure 302816DEST_PATH_IMAGE012
，
S3, introducing wall gas rarefied slip temperature correction to flow field grid infinitesimal needing iterative computation on the basis of a traditional energy radiation balance equation to obtain an energy radiation balance equation based on slip temperature, and implicitly iteratively computing the slip temperature:
Figure 945019DEST_PATH_IMAGE013
s4: according to the iterative residual error on the grid infinitesimal and the iterative calculation precision requirement
Figure 782525DEST_PATH_IMAGE014
The ratio of the magnitudes of (A) to (B), is judged
Figure 198504DEST_PATH_IMAGE015
Whether the iteration is converged;
s5: iterating S3 and S4 repeatedly until the calculation converges to obtain the gas slip temperature
Figure 687123DEST_PATH_IMAGE016
Then slip relationship by wall gas temperature
Figure 516539DEST_PATH_IMAGE017
Calculating to obtain the wall radiation equilibrium temperature
Figure 998598DEST_PATH_IMAGE018
The distribution of (a);
wherein:
Figure 289771DEST_PATH_IMAGE019
in order to be a function of the slip correction,
Figure 383629DEST_PATH_IMAGE020
in order to iteratively calculate the accuracy requirements,
Figure 662907DEST_PATH_IMAGE021
in order to obtain a thermal conductivity coefficient of the gas,
Figure 209426DEST_PATH_IMAGE022
is a heat flow term that has no direct relation to the wall temperature,
Figure 569869DEST_PATH_IMAGE023
is the coefficient of surface emissivity of the material,
Figure 518233DEST_PATH_IMAGE024
is the stefan-boltzmann constant,
Figure 377867DEST_PATH_IMAGE025
the normal spacing of the first layer of wall mesh,
Figure 411682DEST_PATH_IMAGE026
in order to be able to perform the number of iterations,
Figure 44658DEST_PATH_IMAGE027
and
Figure 113108DEST_PATH_IMAGE028
are respectively the first iteration
Figure 937451DEST_PATH_IMAGE026
And
Figure 724142DEST_PATH_IMAGE015
the glide temperature of the step.
2. The radiation balance temperature calculation method considering the slip correction as claimed in claim 1, wherein the hypersonic slip flow numerical simulation of S1 is a Navier-Stokes equation system considering the slip effect.
3. The radiation balance temperature calculation method considering slip correction according to claim 1, wherein: in S3
Figure 160808DEST_PATH_IMAGE022
The heat flow term which is not directly related to the wall surface temperature is determined by an actual surface physical mechanism and comprises one or more of surface component diffusion heat flow, wall surface mass injection energy flux and wall surface mechanical loss energy flux.
4. The radiation balance temperature calculation method considering slip correction according to claim 1, wherein in S4, when the iteration residual satisfies
Figure 83765DEST_PATH_IMAGE029
Then, the infinitesimal iterative computation converges; when in use
Figure 659103DEST_PATH_IMAGE030
Then the infinitesimal iterative computation is not converged, and the next iteration is carried out, namely
Figure 887084DEST_PATH_IMAGE031
Returning to step S3.
5. The radiation balance temperature calculation method considering slip correction according to claim 1, wherein: said slip correction function
Figure 143753DEST_PATH_IMAGE019
The expression of (a) is determined by a slip model adopted by numerical simulation, the thermal creep effect is ignored, and the first-order temperature slip condition in the slip model is passed through
Figure 249112DEST_PATH_IMAGE032
Is expressed in the form of
Figure 182302DEST_PATH_IMAGE033
Is the gas temperature wall normal gradient.
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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108255781A (en) * 2018-01-04 2018-07-06 北京环境特性研究所 A kind of hypersonic target surface dynamic temperature modeling method
CN108304595A (en) * 2017-05-04 2018-07-20 北京空天技术研究所 A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft
CN110489709A (en) * 2019-08-01 2019-11-22 中国空气动力研究与发展中心计算空气动力研究所 The method for numerical simulation of parsing Wall-function based on compressible flows
CN111859532A (en) * 2020-06-16 2020-10-30 空气动力学国家重点实验室 Improved hot wall correction method considering hypersonic chemical non-equilibrium effect

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11098575B2 (en) * 2018-02-26 2021-08-24 Exxonmobil Upstream Research Company Method for flow profiling using active-source heating or cooling and temperature profiling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108304595A (en) * 2017-05-04 2018-07-20 北京空天技术研究所 A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft
CN108255781A (en) * 2018-01-04 2018-07-06 北京环境特性研究所 A kind of hypersonic target surface dynamic temperature modeling method
CN110489709A (en) * 2019-08-01 2019-11-22 中国空气动力研究与发展中心计算空气动力研究所 The method for numerical simulation of parsing Wall-function based on compressible flows
CN111859532A (en) * 2020-06-16 2020-10-30 空气动力学国家重点实验室 Improved hot wall correction method considering hypersonic chemical non-equilibrium effect

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