CN108304601A - A kind of judgment method of hypersonic aircraft boundary layer transition - Google Patents
A kind of judgment method of hypersonic aircraft boundary layer transition Download PDFInfo
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Abstract
The present invention provides a kind of judgment method of hypersonic aircraft boundary layer transition, based on pre-stage test data determine aircraft surface turn twist position；The Laminar Flow of corresponding trystate aircraft surface orthogonalization is obtained, and using the N Distribution values for improving e N methods and obtaining aircraft surface for considering crossing current mode；Turn to twist position in conjunction with the aircraft surface that test data determines, determines that triggering turns the N values N twisted0, and be used for target aircraft and turn to twist the judgement of position.This method is based on test data, consider the three-dimensionality feature in lifting body/Waverider shape hypersonic aircraft flow field, when being integrated using e N methods other than considering second mode perturbation wave, it is also considered that the perturbation wave of the crossing current mode of more low frequency has obtained Accurate Prediction and turned to twist the transition criterion N of position0, the Accurate Prediction for lifting body/Waverider shape hypersonic aircraft boundary layer transition provides a kind of effective judgment method.
Description
Technical field
The invention belongs to the analysis of aircraft boundary layer stability and transition prediction technical fields, and in particular to a kind of high ultrasound
The judgment method of fast aircraft boundary layer transition more particularly to it is a kind of based on flight/test data be applied to lifting body/rider
Body hypersonic aircraft boundary layer turn twist judgment method.
Background technology
Hypersonic aircraft (hereinafter referred to as aircraft) during flight test, aircraft surface there are laminar flow and
Two kinds of fluidised forms of turbulent flow.The difference of fluidised form leads to aircraft lift, resistance, surface heat flow, engine performance and air intake duct startability
The difference of energy.Flow process defined in the present invention from laminar flow to turbulent flow is to turn to twist.Accurate prediction aircraft surface turns to twist
Position is the key that Flight Vehicle Design, determines flight test success or failure.
Prediction aircraft surface turn twist position, at present frequently with method have：Half warp based on linear stability theory
Traditional e-N methods for testing, the method (PSE) for solving parabolized stability equation, direct Numerical (DNS), Transitional And Turbulent Flow mould
Formula and engineering turn to twist criterion, wherein in engineer application, the e-N methods based on Theory of Stability are most widely used.In aviation
Industrial circle, e-N methods are typically considered prediction and turn to twist position most efficient method.
However, for traditional e-N methods, there are the microvariations of various frequencies in boundary layer, when they are downstream propagated
When, start to increase in different position amplitudes respectively；The perturbation wave of various frequencies is since the position increased it, useable linear
Theory of Stability calculates the increased times that they add up downstream, and increased times reach a certain particular value N first0Disturbance
Wave, which causes, to be turned to twist.
It is embodied as：
Or
What e-N methods considered is the relative growth for disturbing amplitude, does not account for the actual size of vibration amplitude, and triggering turns to twist
N0The size of value needs to be given by experiment or experience.
For hypersonic aircraft boundary layer transition, it is considered that second mode perturbation wave plays a leading role, e-N methods
In integral, only the perturbation wave of frequency range where second mode is integrated.Saric is carried out in the problem that turns to twist to hypersonic speed
After summary, gives high speed two-dimension flowing triggering and turn the N twisted0Value about 10, is subject to the numerical value substantially at present.But to lift
For the hypersonic aircraft of the complex appearances such as body/Waverider, three-dimensionality due to flow field is flow over apparent by force, such case
Under, the triggering provided early period turns the N twisted0=10 are no longer applicable in.Therefore, if accurately to obtain the table of hypersonic aircraft
The turning of face twists position, how to obtain accurately triggering and turns the N that twists0Value is a problem to be solved.
Invention content
It is an object of the invention to overcome the shortage of prior art, provides a kind of hypersonic aircraft boundary layer and turn to twist
Position judging method, this method are based on improved e-N methods, and crossing current is influenced to be introduced into the judgement for turn twisting position, give as
What, which obtains triggering in the e-N methods for considering crossing current influence, turns the N twisted0, solve the problems, such as traditional e-N methods engineerings application.
Technical solution of the invention：
A kind of judgment method of hypersonic aircraft boundary layer transition, includes the following steps：
Step 1, determine aircraft surface early period turn twist position；
1.1 obtain aircraft pre-stage test data, wherein required trystate selects as needed；
1.2 according to above-mentioned test data determine aircraft surface under above-mentioned trystate turn twist position；
Step 2 obtains transition criterion N using improved e-N stability analyses judgment method0；
2.1 calculate above-mentioned trystate underflow flow field, and flow field is interpolated into the orthogonal grid of aircraft surface normal direction
On, obtain the flow field of orthogonalization；
2.2 based on the flow field of above-mentioned orthogonalization, using the flow field of orthogonalization as basic flow, neutral curve is analyzed, is examined
Consider the neutral curve that crossing current influences；
2.3, based on obtained neutral curve, choose second mode of the amplitude growth rate more than 0 and crossing current modal perturbation wave,
Using e-N methods to the perturbation wave along potential barrier direction integral, and the envelope of the N values of all perturbation waves calculated is taken to make
For the N Distribution values of aircraft surface；
The 2.4 N Distribution values for turning to twist position and aircraft surface based on above-mentioned aircraft surface, determine that triggering turns the N twisted
It is worth transition criterion N0；
Step 3, the transition criterion N by gained0Judgement for the target aircraft surface positions Zhuan Lie.
A kind of judgment method of hypersonic boundary layer transition e-N stability analyses provided in an embodiment of the present invention, according to
Pre-stage test data determine aircraft surface turn twist position；Obtain the laminar flow stream of corresponding trystate aircraft surface orthogonalization
, and using the N Distribution values for improving e-N methods and obtaining aircraft surface for considering crossing current mode；It is determined in conjunction with test data
Aircraft surface turns to twist position, determines that triggering turns the N values N twisted0.This method is based on test data, it is contemplated that lifting body/Waverider
The three-dimensionality feature in shape hypersonic aircraft flow field, because for above-mentioned flow field, what primary edge layer turned to twist may be horizontal
Mode is flowed, when the present invention is integrated using e-N methods other than considering second mode perturbation wave, it is also considered that the crossing current mode of more low frequency
Perturbation wave, and then obtain consider crossing current mode turn twist discriminatory analysis method, obtained Accurate Prediction turn twist position turn
Twist criterion N0, one kind is provided effectively for the Accurate Prediction of lifting body/Waverider shape hypersonic aircraft boundary layer transition
Judgment method.
Description of the drawings
Included attached drawing is used for providing being further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together with verbal description to illustrate the principle of the present invention.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, other drawings may also be obtained based on these drawings.
Fig. 1 is a kind of flow of embodiment of the judgment method of hypersonic aircraft boundary layer transition provided by the invention
Figure；
Fig. 2 is that aircraft early period provided by the invention turns to twist location determination schematic diagram；
Fig. 3 is that hypersonic aircraft provided by the invention turns to twist consideration in position predicting method and do not consider in crossing current
Linearity curve comparison diagram；
Fig. 4 is different frequency perturbation wave edge in the judgment method of hypersonic aircraft boundary layer transition provided by the invention
The N Distribution values in potential barrier direction；
Fig. 5 is that hypersonic aircraft provided by the invention turns to twist N Distribution values schematic diagram in position predicting method；
Fig. 6 is that hypersonic aircraft provided by the invention turns to twist N in position predicting method0Determine schematic diagram；
Wherein, black line indicates to turn to twist position in Fig. 6.
Specific implementation mode
Specific embodiments of the present invention are described in detail below in conjunction with attached drawing.In the following description, for solution
Purpose and not restrictive is released, elaborates detail, to help to be apparent from the present invention.However, to people in the art
It is readily apparent that the present invention can also be put into practice in the other embodiments departing from these details for member.
It should be noted that in order to avoid having obscured the present invention because of unnecessary details, only show in the accompanying drawings
The device structure closely related with scheme according to the present invention and/or processing step are gone out, and have been omitted with relationship of the present invention not
Big other details.
Referring to Fig. 1, a kind of judgment method of hypersonic aircraft boundary layer transition is present embodiments provided, by following
Step is realized：
Step 1：It is a kind of based on test flight data turn twist location determining method；
Step 1.1 hypersonic aircraft test data；
In the step, the experimental data is somebody's turn to do based on the aircraft surface heat-flow measurement test data of early period
Technology well known in the art can be used in the acquisition of data, and test data obtains corresponding trystate and selects as needed, tries
Testing data can adjust according to actual needs,
Step 1.2 aircraft surface turns to twist the determination of position；
It is determined in conjunction with the heat flow value (Q) that numerical computations (laminar flow and turbulent flow) obtain by the hot-fluid test data of step 1.1
Under above-mentioned trystate aircraft surface turn twist position, specially：
First, the heat-flow measurement value of each sensor of aircraft surface is obtained according to test data, is flown by statistics
The heat flux distribution on row device surface；Then, using software or program calculate corresponding states at each sensing station holostrome stream and
Turbulent flow heat flow value；Finally, the heat flow value recognized by test data is obtained compared with the laminar flow and turbulent flow value that are calculated each
At sensing station corresponding states turn twist position；
Existing business software can be used in the software or program, such as engineering calculation software Fluent meters can be used
It calculates；
For example, referring to Fig. 2, in operating mode Ma4, Re5 × 107Under, according to each sensing of test data aircraft surface
The heat-flow measurement value of device obtains the identical distribution opened up to position (z=z0) measuring point hot-fluid along X (flow direction)；Then, using engineering
Laminar flow and turbulent flow heat flow value that software Fluent calculates corresponding trystate are calculated, point of the positions z=z0 hot-fluid in the x-direction is obtained
Cloth；Finally, compared with hot-fluid test value being calculated heat flow value with turbulent flow and laminar flow, the positions the z=z0 positions Zhuan Lie, hot-fluid experiment are obtained
Value deviates the position x0 that laminar flow calculated value develops to turbulent flow calculated value, as turns to twist position, and the position that turns to twist of all z locations is connected
Get up, obtain aircraft surface turn twist position；
Step 2：Transition criterion N is obtained using improved e-N stability analyses judgment method0；
Step 2.1 obtains neutral curve using Theory of Stability；
Step 2.1.1 corresponds to the Laminar Flow of trystate using numerical computations step 1.1, and wall temperature takes trystate wall
Temperature；
In the step, the technology that numerical computations are known in the art is specifically shown in document《It Fluid Mechanics Computation method and answers
With》, publishing house of BJ University of Aeronautics ＆ Astronautics；
The obtained Laminar Flows of step 2.1.1 are transformed into aircraft surface along the orthogonal grid of normal direction by step 2.1.2,
Obtain the Laminar Flow of orthogonalization；
The orthogonalization flow field that step 2.1.3 obtains step 2.1.2 is as basic flow field, using linear stability theory point
Neutral curve feature is analysed, obtains considering the neutral curve after crossing current, and maximum first will be influenced by crossing current in the neutral curve
Mode is as crossing current mode；
In the step, means well known in the art can be used using linear stability theory analysis neutral curve feature, have
Body is shown in《Flow stability》, all identical, National Defense Industry Press；
For example, referring to Fig. 3, it is generally the case that when using linear stability theory analysis neutral curve, in basic flow
The component for only considering x and y both directions, it is 0 to force z durection components；But after considering to flow over, the component in the directions z in basic flow
It is no longer forced to 0, Fig. 3 and gives the comparison for not considering to flow over and consider neutral curve when crossing current：Abscissa is perturbation wave in figure
It opens up to wave number β, ordinate is disturbance wave frequency rate f, and the variation of cloud atlas color indicates the amplitude growth rate-α of perturbation waveiSize,
Satisfaction-αiThe collection of the point of=0 condition is collectively referred to as neutral curve.It can be seen from the figure that compared to second mode (Mack mode),
Low-frequency excitation mode by flow over influenced it is very big, crossing current so that first mode unstability region expand and to more low frequency region move
It is dynamic.To maximum first mode can be influenced by crossing current at this time, and see crossing current mode as；
Step 2.2 transition criterion N0The determination method of value；
The neutral curve that step 2.2.1 is obtained according to 2.1.3 chooses amplitude growth rate-αi>0 second mode perturbation wave
The crossing current modal waves of more low frequency obtain different frequency perturbation wave along potential barrier direction using e-N methods along potential barrier direction integral
N Distribution values, as shown in Figure 4；
In the step, the specific formula for calculation of the N values is the general equation in e-N methods, as follows：
Wherein, A is the amplitude of disturbance, and A0 is amplitude when disturbance starts to increase, and 0.0001, x0 is generally taken to indicate a certain frequency
The perturbation wave of rate makes growth rate αi=0 flows to position, and x expressions flow to position；
The different frequency perturbation wave that step 2.2.2 is obtained according to 2.2.1 counts along the N Distribution values in potential barrier direction and obtains edge
The N values envelope (set of maximum N values at different x positions) in potential barrier direction, forming step 1.1 correspond to trystate aircraft table
The N Distribution values in face, as shown in Figure 5；
Step 2.2.3 based on step 2.2.2's as a result, turning to twist position with aircraft surface that step 1 obtains compared with, really
Fixed triggering turns the N values N twisted0Transition criterion as e-N methods；
Referring to Fig. 6, turn to twist at position what experiment obtained, the N values of aircraft surface are about 20, then triggering turns the N twisted0=
20, it can be seen that and the existing N obtained with experience0=10 have very big difference, it is seen that the existing N obtained with experience0Value is no longer suitable
With the judgement of lifting body/Waverider complex appearance hypersonic aircraft boundary layer transition；
Further, the N0Value can be constantly modified according to flight/ground test data.
Step 3：By the transition criterion N of gained0For the judgement of the target aircraft surface positions Zhuan Lie, specially：
Step 3.1 trajectory analysis；
For the trajectory of target aircraft, the variation range of the parameters of trajectory is counted by analysis, obtains horse
The variation range of conspicuous number, height, the angle of attack, wall surface temperature obtains establishing the required sample of database, this step is that this field is public
The step of knowing；
Step 3.2 establishes N Distribution value databases, including：
Step 3.2.1 obtains the Laminar Flow of aircraft sample operating mode；
Aircraft sample is calculated using engineering calculation software Fluent in the sample operating mode obtained according to step 3.1
The Laminar Flow of operating mode, in calculating process, using under the conditions of trajectory pneumatic thermal environment and true Flight Vehicle Structure as base
Plinth is analyzed to obtain the temperature of aircraft surface by structural thermal, the wall condition calculated using this temperature as Fluent；
The obtained Laminar Flows of step 3.2.1 are transformed into aircraft surface along the orthogonal grid of normal direction by step 3.2.2,
Obtain the Laminar Flow of orthogonalization；
Step 3.2.3 obtains orthogonalization flow field as basic flow using step 3.2.2, obtains target aircraft surface N values point
Cloth, specific implementation mode is the same as step 2.1.3~step 2.2.2；
Step 3.3 target aircraft turns to twist position judgment；
The N Distribution value databases established according to step 3.2 can be according to transition criterion N to any one trajectory point0=20,
Judgement aircraft surface turn twist position.
The present invention is verified through target aircraft flight test, according to new transition criterion N0, influenced using consideration crossing current
It improves e-N methods to predict target aircraft, in three-dimensionality strong position transition prediction result and flight test result
It coincide preferable, illustrates the validity of transition criterion.
As above it is directed to that a kind of embodiment describes and/or the feature that shows can be in a manner of same or similar at one or more
It is used in a number of other embodiments, and/or the feature in other embodiments is combined or substitutes with the feature in other embodiments
It uses.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when being used herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step, component or combinations thereof.
The device and method more than present invention can be by hardware realization, can also be by combination of hardware software realization.The present invention
It is related to such computer-readable program, when the program is performed by logical block, the logical block can be made to realize above
The device or component parts, or the logical block is made to realize various method or steps described above.The invention further relates to
Storage medium for storing procedure above, such as hard disk, disk, CD, DVD, flash memory.
The many features and advantage of these embodiments are clear according to the detailed description, therefore appended claims are intended to
Cover all these feature and advantage of these embodiments fallen into its true spirit and range.Further, since this field
Technical staff is readily apparent that many modifications and changes, therefore is not meant to the embodiment of the present invention being limited to illustrated and description essence
Really structurally and operationally, but all suitable modifications and the equivalent fallen within the scope of its can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (5)
1. a kind of judgment method of hypersonic aircraft boundary layer transition, which is characterized in that realized by following steps：
Step 1, determine aircraft surface early period turn twist position；
1.1 obtain aircraft pre-stage test data, wherein required trystate selects as needed；
1.2 according to above-mentioned test data determine aircraft surface under above-mentioned trystate turn twist position；
Step 2 obtains transition criterion N using improved e-N stability analyses judgment method0；
2.1 calculate above-mentioned trystate underflow flow field, and flow field is interpolated on the orthogonal grid of aircraft surface normal direction, obtain
To the flow field of orthogonalization；
Neutral curve is analyzed in 2.2 flow fields based on above-mentioned orthogonalization using the flow field of orthogonalization as basic flow, obtains considering horizontal
Flow the neutral curve influenced, wherein influenced maximum first mode as crossing current mode by crossing current using in the neutral curve；
2.3, based on obtained neutral curve, choose second mode of the amplitude growth rate more than 0 and crossing current modal perturbation wave, use
E-N methods to the perturbation wave along potential barrier direction integral, and take all perturbation waves calculated N values envelope as fly
The N Distribution values on row device surface；
The 2.4 N Distribution values for turning to twist position and aircraft surface based on above-mentioned aircraft surface determine that triggering turns the N values twisted and turns
Twist criterion N0；
Step 3, the transition criterion N by gained0Judgement for the target aircraft surface positions Zhuan Lie.
2. a kind of judgment method of hypersonic aircraft boundary layer transition according to claim 1, it is characterised in that：Institute
It states in step 2.1, when calculating Laminar Flow, required wall surface temperature is calculated according to along trajectory Aerodynamic Heating and Flight Vehicle Structure
It arrives.
3. a kind of judgment method of hypersonic aircraft boundary layer transition according to claim 1-2, it is characterised in that：
The N0Value can be constantly modified according to flight/ground test data.
4. a kind of judgment method of hypersonic aircraft boundary layer transition according to claim 1-3, it is characterised in that：
The transition criterion N by gained0For the judgement of the target aircraft surface positions Zhuan Lie, including：
The Laminar Flow of target aircraft flying condition typical condition is obtained, and it is orthogonal to be interpolated into target aircraft surface normal
On grid, the flow field of orthogonalization is obtained；
Based on the orthogonalization flow field, target flight is obtained using 2.2~2.3 identical analysis calculation methods in above-mentioned steps 2
The N Distribution values on device surface；
N Distribution values based on the target aircraft surface and above-mentioned N0Value, determine lower aircraft surface turn twist position.
5. a kind of judgment method of hypersonic aircraft boundary layer transition according to claim 1-4, which is characterized in that
The hypersonic aircraft is the hypersonic aircraft of lifting body/Waverider shape.
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