CN107977494A - Gas handling system characteristic predicting method and system under hypersonic aircraft back-pressure - Google Patents
Gas handling system characteristic predicting method and system under hypersonic aircraft back-pressure Download PDFInfo
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- CN107977494A CN107977494A CN201711155201.9A CN201711155201A CN107977494A CN 107977494 A CN107977494 A CN 107977494A CN 201711155201 A CN201711155201 A CN 201711155201A CN 107977494 A CN107977494 A CN 107977494A
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Abstract
The invention discloses gas handling system characteristic predicting method and system under a kind of hypersonic aircraft back-pressure.Wherein, this method comprises the following steps：Verify the accuracy of hypersonic aircraft gas handling system computational methods；Gas handling system schlieren figure under being emulated to obtain back-pressure incrementally to hypersonic aircraft gas handling system flow field, judge that the corresponding shock wave front open position of each gas handling system schlieren figure is put with the import of the distance piece of aircraft apart from specified range, then gas handling system is in unstart boundary；Gas handling system upper wall surface heat flux distribution figure under being emulated to obtain back-pressure incrementally to hypersonic aircraft gas handling system flow field, and according to the upper wall surface heat flow value of each gas handling system upper wall surface heat flux distribution figure detection and isolation section inlet point, if upper wall surface heat flow value is more than designated value, then gas handling system is in unstart boundary, then Aerodynamic Heating deteriorates.Anti-reflective pressure performance anticipation the invention enables gas handling system is accurate, and improves the design of gas handling system.
Description
Technical field
The invention belongs to air inlet under hypersonic aircraft technical field, more particularly to a kind of hypersonic aircraft back-pressure
System performance predicting method and system.
Background technology
Hypersonic jets (by taking scramjet engine as an example) are by gas handling system (air intake duct, distance piece), combustion chamber
Formed with jet pipe etc..Distance piece is the important portion that Dual-mode Scramjet realizes bimodal and mode conversion
Part.Meanwhile it opens air intake duct and combustion chamber isolated, preventing the high back-pressure of burning influences air intake duct, can provide one for air intake duct
A more broad working range.Factors affect initial position, intensity and the gas handling system performance of shock train, and burn
Room back-pressure is one of factor that must take into consideration.In addition, the maximum feature of gas handling system interior flow field is that there are shock wave-boundary layer
Interaction phenomenon, its performance directly influences the stability of engine and the performance of gas handling system.Therefore research back-pressure pair
The influence of gas handling system flow behavior has very important effect.
At present, be concentrated mainly on both at home and abroad the starting characteristic lower to the effect of supersonic speed/hypersonic gas handling system back-pressure with
Anti-reflective pressure energy power is studied, and is indicated without reference to the lower gas handling system shock wave impact position of combustion chamber back-pressure effect is inquired into air inlet
The anti-reflective pressure performance anticipation of system is inaccurate, and shock train forward pass causes gas handling system flowing and Aerodynamic Heating characteristic research not
It is enough comprehensive so as to prejudge inaccuracy to gas handling system performance, and influence the design of gas handling system.
The content of the invention
Present invention solves the technical problem that it is：Overcome the deficiencies of the prior art and provide a kind of hypersonic aircraft back-pressure
Lower gas handling system characteristic predicting method and system so that the anti-reflective pressure performance anticipation of gas handling system is accurate, and improves air inlet
The design of system.
The technical scheme is that：A kind of according to an aspect of the invention, there is provided hypersonic aircraft back-pressure
Lower flowing and Aerodynamic Heating characteristic predicting method, the described method comprises the following steps：
(1) accuracy of hypersonic aircraft gas handling system computational methods is verified；
(2) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system flow field according to two dimension
Gas handling system schlieren figure under being emulated to obtain back-pressure incrementally, and according to each gas handling system schlieren figure obtain it is corresponding swash
Wavefront open position is put, judge the corresponding shock wave front open position of each gas handling system schlieren figure put with the import of the distance piece of aircraft away from
From specified range, then gas handling system is in unstart boundary, then flowing deteriorates；
(3) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system flow field according to two dimension
Gas handling system upper wall surface heat flux distribution figure under being emulated to obtain back-pressure incrementally, and according to each gas handling system upper wall surface hot-fluid
The upper wall surface heat flow value of distribution map detection and isolation section inlet point, if upper wall surface heat flow value is more than designated value, gas handling system is in
Unstart boundary, then Aerodynamic Heating deterioration.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, step (1) includes：It is selected
Two dimension couples implicit NS equations and RNG κ-ε turbulence models, and default hypersonic aircraft gas handling system flow field is emulated
Obtain no back-pressure numerical value schlieren figure and the back-pressure numerical value schlieren figure under certain throttling degree, by no back-pressure numerical value schlieren figure obtain into
Shock wave impact position in gas system, shock wave impact position and the shock wave of default no back-pressure experiment schlieren figure rush in the gas handling system
Whether consistent position judgment is hit, if unanimously, verifying the accuracy of hypersonic aircraft gas handling system computational methods；Pass through
No back-pressure numerical value schlieren figure obtains the distribution of gas handling system inner wall surface pressure, gas handling system inner wall surface pressure distribution and default nothing
The wall pressure distribution of back-pressure experiment schlieren figure judges whether unanimously, if unanimously, verifying hypersonic aircraft air inlet system
The accuracy for computational methods of uniting；Shock wave in gas handling system is obtained by the back-pressure numerical value schlieren figure under necessarily degree of throttling and impacts position
Put, the shock wave impact position of shock wave impact position and the back-pressure experiment schlieren figure under default certain throttling degree in the gas handling system
Judge whether unanimously, if unanimously, verifying the accuracy of hypersonic aircraft gas handling system computational methods；By necessarily saving
Back-pressure numerical value schlieren figure under mobility obtains the distribution of gas handling system inner wall surface pressure, gas handling system inner wall surface pressure distribution with it is pre-
If certain throttling degree under back-pressure experiment schlieren figure wall pressure distribution judge whether unanimously, if unanimously, verification height
The accuracy of supersonic aircraft gas handling system computational methods.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(4) two dimension in step (1) couples implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft gas handling system
Flow field emulated to obtain back-pressure incrementally under gas handling system motion pattern, and obtained according to each gas handling system motion pattern corresponding
Shock/Boundary-Layer interference separation zone position, judge the interference separation of each gas handling system motion pattern corresponding Shock/Boundary-Layer
The import of the distance piece of zone position and aircraft is in unstart boundary apart from specified range, then gas handling system, then flowing deteriorates.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(5) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system stream according to the two dimension in step (1)
Gas handling system lower wall surface Mach Number Distribution figure under being emulated to obtain back-pressure incrementally, and according to each gas handling system lower wall surface
The Mach number of Mach Number Distribution figure detection and isolation section import lower wall millet cake, if Mach number is less than designated value, gas handling system is in
Unstart boundary, then flowing deteriorate.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(6) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system stream according to the two dimension in step (1)
Gas handling system central axes static pressure distribution figure under being emulated to obtain back-pressure incrementally, and it is quiet according to each gas handling system central axes
The central axes static pressure of distribution map detection and isolation section inlet point is pressed, if central axes static pressure is more than designated value, at gas handling system
In unstart boundary, then flowing deteriorates.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(7) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system stream according to the two dimension in step (1)
Gas handling system lower wall surface static pressure distribution figure under being emulated to obtain back-pressure incrementally, and it is quiet according to each gas handling system lower wall surface
The lower wall surface static pressure of distribution map detection and isolation section inlet point is pressed, if lower wall surface static pressure is more than designated value, at gas handling system
In unstart boundary, then flowing deteriorates.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(8) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system stream according to the two dimension in step (1)
The gas handling system lower wall surface heat flux distribution figure that to be emulated to obtain back-pressure incrementally lower, and it is hot according to each gas handling system lower wall surface
The lower wall surface heat flow value of flow point Butut detection and isolation section inlet point, if lower wall surface heat flow value is more than designated value, at gas handling system
In unstart boundary, then Aerodynamic Heating deterioration.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(9) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system flow field according to two dimension in step (1)
Gas handling system outlet pressure distribution curve under being emulated to obtain back-pressure incrementally, judges every gas handling system outlet pressure distribution
The Pressure maximum value of curve and the difference of minimum value, if difference is more than 8P0-10P0, the outlet pressure skewness of gas handling system
Even property deteriorates i.e. flowing and deteriorates.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(10) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system flow field according to two dimension in step (1)
Gas handling system exit temperature profiles under being emulated to obtain back-pressure incrementally, judge every gas handling system Exit temperature distribution
The temperature maximum of curve and the difference of minimum value, if difference is more than 150K-200K, the Exit temperature distribution of gas handling system is uneven
Even property deteriorates.
Under above-mentioned hypersonic aircraft back-pressure flowing and Aerodynamic Heating characteristic predicting method in, further include following steps：
(11) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system flow field according to two dimension in step (1)
Gas handling system exit Mach number distribution curve under being emulated to obtain back-pressure incrementally, judges every gas handling system exit Mach number
The difference of the Mach number maxima and minima of distribution curve, if difference is more than Ma2.5-3, the exit Mach number point of gas handling system
Cloth inhomogeneities deteriorates.
According to another aspect of the present invention, it is special that flowing and Aerodynamic Heating under a kind of hypersonic aircraft back-pressure are additionally provided
Property forecasting system, including：First module, for verifying the accuracy of hypersonic aircraft gas handling system computational methods；Second
Module, for according to two dimension couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft gas handling system flow field into
Row emulates the gas handling system schlieren figure under obtaining back-pressure incrementally, and obtains corresponding shock wave according to each gas handling system schlieren figure
Forward pass position, judges that the corresponding shock wave front open position of each gas handling system schlieren figure puts the import distance with the distance piece of aircraft
Specified range, then gas handling system be in unstart boundary, then flowing deteriorate；3rd module, for coupling implicit NS according to two dimension
Equation and RNG κ-ε turbulence models emulated to obtain back-pressure incrementally to hypersonic aircraft gas handling system flow field under air inlet
System upper wall surface heat flux distribution figure, and according to the upper wall of each gas handling system upper wall surface heat flux distribution figure detection and isolation section inlet point
Face heat flow value, if upper wall surface heat flow value is more than designated value, gas handling system is in unstart boundary, then Aerodynamic Heating deteriorates.
The present invention compared with prior art the advantages of be：
(1) present invention using two dimension couple implicit NS equations and RNG κ-ε turbulence models to two-dimentional scramjet engine into
Flowing and Aerodynamic Heating property calculation in gas system, accurately capturing shock structure and variation characteristic, indication shock wave can impact position
Put；
(2) present invention can disclose gas handling system and gas handling system exit flow performance, Aerodynamic Heating performance etc., indication
Shock wave/shock wave, Shock/Boundary-Layer interfere with each other lower separation flowing, and foundation is provided for gas handling system Optimized Re-design.
Brief description of the drawings
By reading the detailed description of hereafter preferred embodiment, it is various other the advantages of and benefit it is common for this area
Technical staff will be clear understanding.Attached drawing is only used for showing the purpose of preferred embodiment, and is not considered as to the present invention
Limitation.And in whole attached drawing, identical component is denoted by the same reference numerals.In the accompanying drawings：
Fig. 1 is flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure provided in an embodiment of the present invention
Flow chart；
Fig. 2 is the schematic diagram of gas handling system physical model provided in an embodiment of the present invention
Fig. 3 (a) is the schematic diagram provided in an embodiment of the present invention without section gas handling system shock wave impact position schlieren figure；
Fig. 3 (b) is that gas handling system shock wave impact position schlieren figure shows under 68% throttling degree provided in an embodiment of the present invention
It is intended to；
Fig. 4 (a) is the schematic diagram provided in an embodiment of the present invention without the lower gas handling system wall pressure distribution of throttling；
Fig. 4 (b) is the schematic diagram of the lower gas handling system wall pressure distribution of provided in an embodiment of the present invention 68% throttling；
Fig. 5 (a) is the schematic diagram provided in an embodiment of the present invention without different back-pressure gas handling system schlieren figures；
Fig. 5 (b) is the schematic diagram of different back-pressure gas handling system motion patterns provided in an embodiment of the present invention；
Fig. 6 (a) is the schematic diagram of different back-pressure gas handling system Mach Number Distributions provided in an embodiment of the present invention；
Fig. 6 (b) is the schematic diagram of different back-pressure gas handling system central axes static pressure distributions provided in an embodiment of the present invention；
Fig. 6 (c) is the schematic diagram of different back-pressure gas handling system lower wall surface static pressure distributions provided in an embodiment of the present invention；
Fig. 7 (a) is the schematic diagram of different back-pressure gas handling system upper wall surface heat flux distributions provided in an embodiment of the present invention；
Fig. 7 (b) is the schematic diagram of different back-pressure gas handling system lower wall surface heat flux distributions provided in an embodiment of the present invention；
Fig. 8 (a) is the schematic diagram of gas handling system outlet pressure provided in an embodiment of the present invention distribution；
Fig. 8 (b) is the schematic diagram of gas handling system Exit temperature distribution provided in an embodiment of the present invention；
Fig. 8 (c) is the schematic diagram of gas handling system exit Mach number provided in an embodiment of the present invention distribution.
Embodiment
The exemplary embodiment of the disclosure is more fully described below with reference to accompanying drawings.Although the disclosure is shown in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
Limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
Completely it is communicated to those skilled in the art.It should be noted that in the case where there is no conflict, embodiment in the present invention and
Feature in embodiment can be mutually combined.Below with reference to the accompanying drawings and the present invention will be described in detail in conjunction with the embodiments.
Fig. 1 is flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure provided in an embodiment of the present invention
Flow chart.As shown in Figure 1, flowing and Aerodynamic Heating characteristic predicting method include following step under the hypersonic aircraft back-pressure
Suddenly：
(1) accuracy of hypersonic aircraft gas handling system computational methods is verified：Selected two dimension couples implicit NS equations
With RNG κ-ε turbulence models, default hypersonic aircraft gas handling system flow field is emulated to obtain no back-pressure numerical value schlieren
Figure and the back-pressure numerical value schlieren figure under 68% throttling degree, obtain shock wave in gas handling system by no back-pressure numerical value schlieren figure and impact position
Put, shock wave impact position and the shock wave impact position of default no back-pressure experiment schlieren figure judge whether one in the gas handling system
Cause, if unanimously, verifying the accuracy of hypersonic aircraft gas handling system computational methods；
Gas handling system inner wall surface pressure is obtained by no back-pressure numerical value schlieren figure to be distributed, the gas handling system inner wall surface pressure point
The wall pressure distribution of cloth and default no back-pressure experiment schlieren figure judges whether unanimously, if unanimously, verified hypersonic
The accuracy of aircraft gas handling system computational methods；
Shock wave impact position in gas handling system is obtained by the back-pressure numerical value schlieren figure under 68% throttling degree, the gas handling system
The shock wave impact position that back-pressure under interior shock wave impact position and default 68% throttling degree tests schlieren figure judges whether unanimously,
If consistent, the accuracy of hypersonic aircraft gas handling system computational methods is verified；
Gas handling system inner wall surface pressure is obtained by the back-pressure numerical value schlieren figure under 68% throttling degree to be distributed, the gas handling system
Inner wall surface pressure is distributed to be judged whether unanimously with the wall pressure distribution of the back-pressure experiment schlieren figure under default 68% throttling degree,
If consistent, the accuracy of hypersonic aircraft gas handling system computational methods is verified；
(2) two dimension in step (1) couples implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft
Gas handling system flow field emulated to obtain back-pressure incrementally under gas handling system schlieren figure, and obtained according to each gas handling system schlieren figure
Put to corresponding shock wave front open position, judge the corresponding shock wave front open position of each gas handling system schlieren figure put with aircraft every
Specified range (10mm-20mm) with a distance from the import of section, then gas handling system be in unstart boundary, then flowing deteriorate；
(3) two dimension in step (1) couples implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft
Gas handling system flow field emulated to obtain back-pressure incrementally under gas handling system motion pattern, and obtained according to each gas handling system motion pattern
Separation zone position is disturbed to corresponding Shock/Boundary-Layer, judges each corresponding Shock/Boundary-Layer of gas handling system motion pattern
The import of the distance piece of interference separation zone position and aircraft is in not apart from specified range (10mm-20mm), then gas handling system
Moving boundary is played, then flowing deteriorates；
(4) according to the two dimension in step (1) couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft into
Gas system flow field emulated to obtain back-pressure incrementally under gas handling system lower wall surface Mach Number Distribution figure, and according to each air inlet system
The Mach number of system lower wall surface Mach Number Distribution figure detection and isolation section import lower wall millet cake, if Mach number is less than designated value (Ma 3.5-
3.6), then gas handling system is in unstart boundary, then flowing deteriorates；
(5) according to the two dimension in step (1) couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft into
Gas system flow field emulated to obtain back-pressure incrementally under gas handling system central axes static pressure distribution figure, and according to each gas handling system
The central axes static pressure of central axes static pressure distribution figure detection and isolation section inlet point, if central axes static pressure is more than designated value (20P0-
30P0), then gas handling system is in unstart boundary, then flowing deteriorates；Wherein, P0 is the free incoming static pressure of gas handling system import；
(6) according to the two dimension in step (1) couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft into
Gas system flow field emulated to obtain back-pressure incrementally under gas handling system lower wall surface static pressure distribution figure, and according to each gas handling system
The lower wall surface static pressure of lower wall surface static pressure distribution figure detection and isolation section inlet point, if lower wall surface static pressure is more than designated value (3P0-
5P0), then gas handling system is in unstart boundary, then flowing deteriorates；Wherein, P0 is the free incoming static pressure of gas handling system import；
(7) according to the two dimension in step (1) couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft into
Gas system flow field emulated to obtain back-pressure incrementally under gas handling system upper wall surface heat flux distribution figure, and according to each gas handling system
The upper wall surface heat flow value of upper wall surface heat flux distribution figure detection and isolation section inlet point, if upper wall surface heat flow value is more than designated value
(200000-300000W/m2), then gas handling system be in unstart boundary, then Aerodynamic Heating deteriorate；
(8) according to the two dimension in step (1) couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft into
Gas system flow field emulated to obtain back-pressure incrementally under gas handling system lower wall surface heat flux distribution figure, and according to each gas handling system
The lower wall surface heat flow value of lower wall surface heat flux distribution figure detection and isolation section inlet point, if lower wall surface heat flow value is more than designated value
(150000-200000W/m2), then gas handling system is in unstart boundary, then Aerodynamic Heating deteriorates；
(9) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft air inlet according to two dimension in step (1)
System flow field emulated to obtain back-pressure incrementally under gas handling system outlet pressure distribution curve, judge the outlet of every gas handling system
The Pressure maximum value of pressure distribution curve and the difference of minimum value, if difference is more than 8P0-10P0, the outlet pressure of gas handling system
Nonunf ormity deteriorates i.e. flowing and deteriorates；
(10) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft air inlet according to two dimension in step (1)
System flow field emulated to obtain back-pressure incrementally under gas handling system exit temperature profiles, judge the outlet of every gas handling system
The temperature maximum of temperature distribution history and the difference of minimum value, if difference is more than 150K-200K, the outlet temperature of gas handling system
Nonunf ormity deteriorates；
(11) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft air inlet according to two dimension in step (1)
System flow field emulated to obtain back-pressure incrementally under gas handling system exit Mach number distribution curve, judge that every gas handling system goes out
The difference of the Mach number maxima and minima of mouth Mach number distribution curve, if difference is more than Ma2.5-3, the outlet of gas handling system
Mach Number Distribution inhomogeneities deteriorates.
Embodiment
Below by certain hypersonic aircraft combustion chamber back-pressure effect under flowing and Aerodynamic Heating characteristic counted
Calculate, analyze the effect of the method for the present invention.
Fig. 2 is example hypersonic aircraft gas handling system physical model, and simulated flight Mach number Ma=6's is hypersonic
Engine behavior, simulates wind-tunnel condition, gives free incoming-flow pressure far field boundary condition, gives combustion chamber import back-pressure point
The different multiples of not free incoming static pressure.
Using two dimension couple implicit NS equations and RNG κ-ε turbulence models to hypersonic jets gas handling system flow field into
Row simulation calculation, is handled using Standard law of wall, it is contemplated that free incoming air total temperature is relatively low, can be by preferable gas treatment.
Grid is generated using ICEM CFD softwares, and carries out wall encryption, y+Control guarantees accurately to catch and swashs within 5
Ripple, reflects the correctness of gas handling system flow field.
The present invention is bored come simulated combustion room back-pressure by setting to block up in gas handling system outlet, and the resistance of stifled cone is can adjust in experiment
Plug obtains different degrees of back-pressure than (gas handling system outlet throttling degree).Meanwhile simulation calculation is without throttling and 68% throttling
The lower gas handling system flow field situation of degree, and carried out detailed comparisons with result of the test.As shown in figure 3, rushed for gas handling system shock wave
Position emulation is hit to analyze with Experimental Comparison, shock wave species, Disengagement zone and the boundary layer thickness in simulation result numerical value schlieren figure with
It is consistent to test schlieren figure, has been accurately captured and has been rushed without hypersonic aircraft gas handling system shock wave in the case of back-pressure and part back-pressure
Hit position, can disclose oblique shock wave and dilatational wave intersect and the main feature of flow field.
As shown in figure 4, analyzed for gas handling system wall pressure distribution emulation under no back-pressure and part back-pressure with Experimental Comparison,
All in all, emulation coincide preferably with result of the test.And back-pressure no matter is whether there is, the wall pressure of gas handling system expansion segment Disengagement zone
Distributed simulation and experiment slightly difference, the reason for causing measurement error are probably the situation of emulation and experiment, or sensor measurement
Error.
The calculating of Fig. 3 (a), Fig. 3 (b), Fig. 4 (a) and Fig. 4 (b) are analyzed, and are established one kind and are suitable for hypersonic aircraft
Gas handling system shock wave impact position predicting method, being capable of accurately capturing shock structure, clear and definite gas handling system flow performance.
Fig. 5 back-pressures increase process gas handling system flow field structure, and shown in Fig. 5 (a) figures, back-pressure increases shock train in air inlet first
System outlet is formed, and outlet back-pressure constantly increases, and is flowed in gas handling system and is not changed；Continue to increase back-pressure, until air inlet system
System outlet boundary-layer is when separating, and shock wave start of string is toward moving in gas handling system.When back-pressure is more than limit back-pressure, shock wave quilt
Fighter Inlet is released, air intake duct is inoperative.Furthermore the particularity of the non-homogeneous and air intake system structure due to incoming so that
Upper wall surface boundary-layer is thicker than lower wall surface, and upper wall surface flowing is easier to separate, and forms asymmetrical shock string structure.In addition, work as
(Pb during back-pressure very little<65P0), shock train is there's almost no in gas handling system, whole passage keeps supersonic flows state, gas
Body causes pressure to rise to match back-pressure by wall viscous effect；When back-pressure continues to increase to certain value, pressure passes through attached
Surface layer uploads, adverse pressure gradient causes boundary-layer to separate, and shock train matches back-pressure.All in all, as stagnation pressure increases, into
Gas system Disengagement zone becomes larger, position reach, and gas handling system capture flow declines, pitot loss increase.Shown in Fig. 5 (b) figures,
Back-pressure starts to increase, and gas handling system lower wall surface boundary layer is thick compared with upper wall surface, boundary-layer caused by shock-boundary interferes with each other point
Lower wall surface is concentrated mainly on from area；Continue to increase back-pressure, boundary-layer Disengagement zone is concentrated mainly on upper wall surface, when back-pressure increases to one
Determine degree, Disengagement zone has been pushed out gas handling system, causes inoperative.
Shown in Fig. 6 (a), Fig. 6 (b) and Fig. 6 (c), for the lower gas handling system central axes Mach number of different back-pressures effect, static pressure and
Lower wall surface static pressure distribution.Central axes Mach number reduces when air-flow runs into oblique shock wave, but still keeps supersonic flows, runs into afterwards swollen
Swollen ripple effect, and cause Mach number increase, but it is overall on a declining curve.Central axes static pressure first rises to be declined afterwards, and overall becomes
Gesture is in rising, to match back-pressure size.In gas handling system the complexity of shock train cause central axes Mach number and static pressure fluctuation compared with
Greatly.Lower wall surface static pressure is in rising trend, in gas handling system outlet increase to a certain extent, to match back-pressure, when back-pressure continues to increase
Greatly, Disengagement zone enters in air intake duct compressing surface under adverse pressure gradient effect so that gas handling system entrance pressure rises very big.At this
In the research of text, when increasing back-pressure to Pb=115P0, cause gas handling system inoperative.
Fig. 7 (a) and Fig. 7 (b) is distributed for different back-pressure gas handling system wall heat fluxes, and upper wall surface hot-fluid is first along flow direction
Decline, it is rear to rise but overall on a declining curve.This is mainly the increase of back-pressure so that gas handling system rear end Disengagement zone constantly increases
Greatly, Aerodynamic Heating decreased effectiveness causes, and rapid fluctuation occurs in Aerodynamic Heating at the interaction of wall shock wave and boundary-layer.
Two states are presented in lower wall surface heat flux distribution, and back-pressure increase first is in certain value when (Pb=65P0), and hot-fluid is along flowing side
Decline afterwards to first rising, it is overall to keep downward trend；Continue to increase back-pressure, hot-fluid first rises along flow direction and declines afterwards, always
Body keeps ascendant trend.In general, back-pressure increase causes boundary-layer separated region to weaken Aerodynamic Heating effect.
The calculating analysis of Fig. 5 to Fig. 7, establishes gas handling system UNSTEADY FLOW and thermal environment under a variety of work back-pressure patterns
Analog analysing method：On the one hand, arq mode before introducing shock train, back-pressure change to shock-wave spot in gas handling system and Disengagement zone shadow
Analysis is rung, obtains gas handling system flow behavior；On the other hand, back-pressure change is carried out to gas handling system wall Aerodynamic Heating characteristic shadow
Analysis is rung, has obtained thermal environment simulation method.
Fig. 8 (a), Fig. 8 (b) and Fig. 8 (c) are distributed for different back-pressure gas handling system outlet parameters, when gas handling system outlet is anti-
When pressure is not big enough, back-pressure is smaller on the influence of gas handling system flow field wave system structure, corresponding, and gas handling system outlet at this time is quiet
Pressure, static temperature and Mach Number Distribution also compared with zero back-pressure when change it is little.Due to the influence of pressure fluctuation so that under the conditions of high back-pressure into
Asymmetric phenomenon is presented in the outlet parameter of gas symmetry system having symmetry wall.
The increase of gas handling system outlet back-pressure is focused first near lower wall surface, this is the separated inverse pressure of lower wall surface boundary-layer
Caused by ladder, but the increase of back-pressure is smaller on the influence of outlet pressure distributing homogeneity.The increase of back-pressure causes gas handling system to export
Temperature Distribution is presented center and is higher than both sides, and gas handling system outlet subsonic speed region progressively expands, and works as Pb=65P0, air inlet system
System exit Mach number is gradually transitions part supersonic speed via pure supersonic speed.The change of back-pressure situation lower combustion chamber inlet flow field
Change, directly affect engine combustion situation, in addition, needing to consider when analyzing hypersonic aircraft anti-reflective pressure performance.
Complex chart 5 is formd and resisted suitable for hypersonic aircraft in the range of limit back-pressure to the Calculation results of Fig. 8
Back-pressure performance synthesis appraisal procedure system, in the case of gas handling system and combustion chamber coupling operational, considers air inlet system start
Can, traffic capture rate, pitot loss, Disengagement zone size and location etc., reach the overall merit to gas handling system performance, while
Combustion chamber incoming quality is taken into account, ensures combustibility etc..
The present embodiment using two dimension couple implicit NS equations and RNG κ-ε turbulence models to two-dimentional scramjet engine into
Flowing and Aerodynamic Heating property calculation in gas system, can accurately capture shock wave structure and variation characteristic, indication shock wave impact
Position；The present embodiment can disclose gas handling system and gas handling system exit flow performance, Aerodynamic Heating performance etc., and indication swashs
Ripple/shock wave, Shock/Boundary-Layer interfere with each other lower separation flowing, and foundation is provided for gas handling system Optimized Re-design.
The present embodiment additionally provides flowing and Aerodynamic Heating characteristic forecasting system under a kind of hypersonic aircraft back-pressure, should
System includes：First module, the second module and the 3rd module；
First module, for verifying the accuracy of hypersonic aircraft gas handling system computational methods；
Second module, for according to two dimension couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft into
Gas system flow field emulated to obtain back-pressure incrementally under gas handling system schlieren figure, and obtained according to each gas handling system schlieren figure
Corresponding shock wave front open position is put, and is judged that each gas handling system schlieren figure corresponding shock wave front open position is put and is isolated with aircraft
The import of section is in unstart boundary apart from specified range, then gas handling system, then flowing deteriorates；
3rd module, for according to two dimension couple implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft into
Gas system flow field emulated to obtain back-pressure incrementally under gas handling system upper wall surface heat flux distribution figure, and according to each gas handling system
The upper wall surface heat flow value of upper wall surface heat flux distribution figure detection and isolation section inlet point, if upper wall surface heat flow value is more than designated value, into
Gas system is in unstart boundary, then Aerodynamic Heating deteriorates.
Embodiment described above is the present invention more preferably embodiment, and those skilled in the art is in this hair
The usual variations and alternatives carried out in the range of bright technical solution should all include within the scope of the present invention.
Claims (10)
1. flowing and Aerodynamic Heating characteristic predicting method under a kind of hypersonic aircraft back-pressure, it is characterised in that the method
Comprise the following steps：
(1) accuracy of hypersonic aircraft gas handling system computational methods is verified；
(2) implicit NS equations and RNG κ-ε turbulence models is coupled according to two dimension to carry out hypersonic aircraft gas handling system flow field
The gas handling system schlieren figure under obtaining back-pressure incrementally is emulated, and corresponding shock wave front is obtained according to each gas handling system schlieren figure
Open position is put, and is judged that the corresponding shock wave front open position of each gas handling system schlieren figure is put and is referred to the import distance of the distance piece of aircraft
Determine scope, then gas handling system is in unstart boundary, then flowing deteriorates；
(3) implicit NS equations and RNG κ-ε turbulence models is coupled according to two dimension to carry out hypersonic aircraft gas handling system flow field
The gas handling system upper wall surface heat flux distribution figure under obtaining back-pressure incrementally is emulated, and according to each gas handling system upper wall surface heat flux distribution
The upper wall surface heat flow value of figure detection and isolation section inlet point, if upper wall surface heat flow value is more than designated value, gas handling system can be in
Moving boundary, then Aerodynamic Heating deterioration.
2. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 1, it is special
Sign is that step (1) includes：Selected two dimension couples implicit NS equations and RNG κ-ε turbulence models, to default hypersonic winged
Row device gas handling system flow field is emulated to obtain no back-pressure numerical value schlieren figure and the back-pressure numerical value schlieren figure under certain throttling degree, is led to
Cross no back-pressure numerical value schlieren figure and obtain shock wave impact position in gas handling system, in the gas handling system shock wave impact position with it is default
The shock wave impact position of no back-pressure experiment schlieren figure judges whether unanimously, if unanimously, verifying hypersonic aircraft air inlet
The accuracy of system-computed method；
By no back-pressure numerical value schlieren figure obtain gas handling system inner wall surface pressure be distributed, the gas handling system inner wall surface pressure distribution with
The wall pressure distribution of default no back-pressure experiment schlieren figure judges whether unanimously, if unanimously, verifying hypersonic flight
The accuracy of device gas handling system computational methods；
Shock wave impact position in gas handling system is obtained by the back-pressure numerical value schlieren figure under necessarily degree of throttling, is swashed in the gas handling system
The shock wave impact position that wave impact position tests schlieren figure with the back-pressure under default certain throttling degree judges whether unanimously, if
Unanimously, then the accuracy of hypersonic aircraft gas handling system computational methods is verified；
Gas handling system inner wall surface pressure is obtained by the back-pressure numerical value schlieren figure under necessarily degree of throttling to be distributed, the gas handling system inner wall
Surface pressure is distributed to be judged whether unanimously with the wall pressure distribution of the back-pressure experiment schlieren figure under default certain throttling degree, if
Unanimously, then the accuracy of hypersonic aircraft gas handling system computational methods is verified.
3. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 2, it is special
Sign is, further includes following steps：
(4) two dimension in step (1) couples implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft air inlet
System flow field emulated to obtain back-pressure incrementally under gas handling system motion pattern, and phase is obtained according to each gas handling system motion pattern
Corresponding Shock/Boundary-Layer interference separation zone position, judges the corresponding Shock/Boundary-Layer interference of each gas handling system motion pattern
The import of the distance piece of separation zone position and aircraft is in unstart boundary apart from specified range, then gas handling system, then flows
Deteriorate.
4. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 2, it is special
Sign is, further includes following steps：
(5) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft air inlet system according to the two dimension in step (1)
System flow field emulated to obtain back-pressure incrementally under gas handling system lower wall surface Mach Number Distribution figure, and according under each gas handling system
The Mach number of wall Mach Number Distribution figure detection and isolation section import lower wall millet cake, if Mach number is less than designated value, gas handling system
In unstart boundary, then flowing deteriorates.
5. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 2, it is special
Sign is, further includes following steps：
(6) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft air inlet system according to the two dimension in step (1)
System flow field emulated to obtain back-pressure incrementally under gas handling system central axes static pressure distribution figure, and according to each gas handling system axis
The central axes static pressure of line static pressure distribution figure detection and isolation section inlet point, if central axes static pressure is more than designated value, air inlet system
System is in unstart boundary, then flowing deteriorates.
6. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 2, it is special
Sign is, further includes following steps：
(7) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft air inlet system according to the two dimension in step (1)
System flow field emulated to obtain back-pressure incrementally under gas handling system lower wall surface static pressure distribution figure, and according to each gas handling system lower wall
The lower wall surface static pressure of face static pressure distribution figure detection and isolation section inlet point, if lower wall surface static pressure is more than designated value, air inlet system
System is in unstart boundary, then flowing deteriorates.
7. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 2, it is special
Sign is, further includes following steps：
(8) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft air inlet system according to the two dimension in step (1)
System flow field emulated to obtain back-pressure incrementally under gas handling system lower wall surface heat flux distribution figure, and according to each gas handling system lower wall
The lower wall surface heat flow value of face heat flux distribution figure detection and isolation section inlet point, if lower wall surface heat flow value is more than designated value, air inlet system
System is in unstart boundary, then Aerodynamic Heating deteriorates.
8. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 2, it is special
Sign is, further includes following steps：
(9) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system according to two dimension in step (1)
Flow field emulated to obtain back-pressure incrementally under gas handling system outlet pressure distribution curve, judge every gas handling system outlet pressure
The Pressure maximum value of distribution curve and the difference of minimum value, if difference is more than 8P0-10P0, the outlet pressure distribution of gas handling system
Inhomogeneities deteriorates i.e. flowing and deteriorates.
9. flowing and Aerodynamic Heating characteristic predicting method under hypersonic aircraft back-pressure according to claim 2, it is special
Sign is, further includes following steps：
(10) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system according to two dimension in step (1)
Flow field emulated to obtain back-pressure incrementally under gas handling system exit temperature profiles, judge every gas handling system outlet temperature
The temperature maximum of distribution curve and the difference of minimum value, if difference is more than 150K-200K, the Exit temperature distribution of gas handling system
Inhomogeneities deteriorates；
(11) implicit NS equations and RNG κ-ε turbulence models are coupled to hypersonic aircraft gas handling system according to two dimension in step (1)
Flow field emulated to obtain back-pressure incrementally under gas handling system exit Mach number distribution curve, judge that every gas handling system goes out a kind of horse raised north of the Grean Wall
The difference of the Mach number maxima and minima of conspicuous several distribution curves, if difference is more than Ma2.5-3, the outlet Mach of gas handling system
Number nonunf ormity deteriorates.
10. flowing and Aerodynamic Heating characteristic forecasting system under a kind of hypersonic aircraft back-pressure, it is characterised in that including：
First module, for verifying the accuracy of hypersonic aircraft gas handling system computational methods；
Second module, for coupling implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft air inlet system according to two dimension
System flow field emulated to obtain back-pressure incrementally under gas handling system schlieren figure, and obtained relatively according to each gas handling system schlieren figure
The shock wave front open position answered is put, and judges that the corresponding shock wave front open position of each gas handling system schlieren figure is put and the distance piece of aircraft
Import is in unstart boundary apart from specified range, then gas handling system, then flowing deteriorates；
3rd module, for coupling implicit NS equations and RNG κ-ε turbulence models to hypersonic aircraft air inlet system according to two dimension
System flow field emulated to obtain back-pressure incrementally under gas handling system upper wall surface heat flux distribution figure, and according to each gas handling system upper wall
The upper wall surface heat flow value of face heat flux distribution figure detection and isolation section inlet point, if upper wall surface heat flow value is more than designated value, air inlet system
System is in unstart boundary, then Aerodynamic Heating deteriorates.
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| CN112417709A (en) * | 2020-12-12 | 2021-02-26 | 西北工业大学 | Dynamic modal analysis method based on schlieren image |
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