CN108304603A - A kind of high-speed aircraft is forced to turn to twist device verification method - Google Patents
A kind of high-speed aircraft is forced to turn to twist device verification method Download PDFInfo
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- CN108304603A CN108304603A CN201710703407.4A CN201710703407A CN108304603A CN 108304603 A CN108304603 A CN 108304603A CN 201710703407 A CN201710703407 A CN 201710703407A CN 108304603 A CN108304603 A CN 108304603A
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Abstract
A kind of high-speed aircraft disclosed by the embodiments of the present invention is forced to turn to twist device verification method, is related to high-speed aircraft pressure and turns to twist device verification technique, can solve the problems, such as to force to turn to twist device verification hardly possible.This method is carried out under laminar flow assays state under identical test state, and 5 kinds of different height k/ δ turn the experiment for forcing to turn to twist device, is obtained different height and is forced to turn to twist the heat flux distribution before and after device；According to the heat flux distribution for forcing to turn to twist before and after device with without heat flux distribution when forcing to turn to twist device compared with, verification forces to turn to twist device and turns to twist effect, and this method, which is mainly used for forcing to turn twisting device, to be verified.
Description
Technical field
It forces to turn to twist device verification technique field the present invention relates to high-speed aircraft more particularly to a kind of high-speed aircraft is strong
System turns to twist device verification method.
Background technology
Turn twist with turbulent flow be both high-speed aircraft great basic aerodynamics problem, and restrict high-speed aircraft hair
The key technical problem of exhibition, boundary layer transition is to high-speed aircraft Scramjet Inlet starting performance and engine
There can be vital influence.Existing research shows that：Under laminar condition, air intake duct compressing surface corner vicinities and every
Produce bigger Disengagement zone from section entrance shock wave reflection area, can cause when serious air intake duct block and it is inoperative；Work as boundary
It when layer is in turbulence state, can greatly inhibit boundary layer separation, improve flowing anti-reflective pressure energy power, ensure the normal work of air intake duct
Make, while engine chamber blending efficiency also can be improved, improves scramjet engine working performance.
In general, pressure can be disposed to turn to twist device in air suction type high-speed aircraft forebody and inlet, make aircraft flight
Boundary layer is in turbulence state in the process, and device is twisted in pressure turn can effectively inhibit boundary layer separation, improves flowing anti-reflective pressure
Ability ensures air intake duct normal work, while engine chamber blending efficiency also can be improved, and improves scramjet engine work
Make performance.Device is twisted in pressures turn most applied to engineering at present has ramp type, brilliant and to flute profile.
Turn to twist effect to be to force to turn to twist the important technology index of device, for force to turn to twist device turn to twist effect verification it is aobvious
It is particularly important, currently, two methods of flight test and wind tunnel test can be used to be verified to forcing to turn to twist device, fly
Test direct and effective, but the disadvantage of flight test is that of high cost, period is long；The most frequently used, feasible method is surface wind
Hole is tested, but due to forcing to turn to twist device without scale similitude, so forcing to turn to twist during being difficult to determining wind tunnel test
The contracting ratio of device, also can not just consider world difference, to realize the world consistency of wind tunnel test.The present invention is directed to ground wind-tunnel
The difficult point of experiment, it is proposed that a kind of feasible, effective to force to turn to twist device verification method.
Invention content
It is an object of the invention to overcome the shortage of prior art, provides a kind of high-speed aircraft and force to turn to twist device verification
Method can solve the problems, such as to force to turn to twist device verification hardly possible.
Technical solution of the invention：
A kind of high-speed aircraft is forced to turn to twist device verification method, and this method is for lifting body/Waverider air suction type high speed
Aircraft, this method include following procedure：
Step 1, it refers to keeping horse to select shock tunnel and trystate, the trystate according to trajectory condition
It is conspicuous constant, adjust Reynolds number and the angle of attack so that force to turn to keep laminar condition before twisting 0.5 meter of device installation site downstream；
Step 2 determines the maximum contracting ratio for forcing to turn to twist device experiment model according to the size of shock tunnel and parameter, really
Determining test model forces the installation site that flows to for turning to twist device to compare position to flow to the contracting of installation site under flying condition；
Step 3 calculates and forces to turn under trystate to twist the enthalpy boundary layer thickness that device flows to installed position, takes strong
It is δ that system, which turns to twist device installed position and open up to the maximum enthalpy boundary layer thickness in section, and the pressure for choosing 5 kinds of different heights turns to twist
Device, it is ensured that one is more than benchmark, and two are less than benchmark, while having δ=0 k/ to compare, normal condition k/ δ=n0 and flight item
Design criteria under part is consistent, separately takes k/ δ=n1, n2, n3,0, wherein n0<n1<=1.0, n0>n2>n3>0, k indicates to force
Turn to twist the height of device coarse cell；
Step 4 is carried out under identical test state, and 5 kinds of different height k/ δ turn the experiment for forcing to turn to twist device, is obtained different
Height forces to turn to twist the heat flux distribution before and after device；
Step 5, according to the heat flux distribution for forcing to turn to twist before and after device with without heat flux distribution ratio when forcing to turn to twist device
Compared with the determining starting altitude h_incipient, critical altitude h_critical and effective height h_ for forcing to turn to twist device
effective；If benchmark k/ δ=n0<H_incipient, then it is invalid to turn to twist device；If h_incipient<K/ δ=n0<h_
Critical then turns to twist device effectively but effect unobvious；If h_critical=<K/ δ=n0<H_effective then turns to twist
Device turns to twist with obvious effects；If k/ δ=n0>=h_effective, then turn to twist device effect and reach best.
It is further alternative, during experiment, is forcing to turn to twist device forward position flow direction 2~3 measuring points of arrangement, forcing to turn
It twists in device downstream (0,0.75m) range and arranges several measuring points along flow direction.
Further alternative, measuring point spacing is more than 10mm, and point layout is in the flow field range for forcing to turn to twist device control
It is interior.
A kind of high-speed aircraft provided in an embodiment of the present invention is forced to turn to twist device verification method, carries out identical test state
Under, 5 kinds of different height k/ δ turn the experiment for forcing to turn to twist device, obtain different height and force to turn to twist the heat flux distribution before and after device；
According to the heat flux distribution for forcing to turn to twist before and after device with without heat flux distribution when forcing to turn to twist device compared with, verification is forced turn to twist dress
It sets and turns to twist effect, this method operability is strong, and verification the verifying results are easy to identify, at low cost.This method is successfully verified.
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 aircraft precursor air intake duct compressing surface and turns to twist device and flow to schematic view of the mounting position；
Fig. 2 is verification test model point layout schematic diagram in the embodiment of the present invention；
Fig. 3 is that high-speed aircraft provided in an embodiment of the present invention is forced to turn to twist device verification method verification test result.
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.
A kind of high-speed aircraft of offer of the embodiment of the present invention is forced to turn to twist device verification method, is laid out for two dimensional inlet
Air suction type high-speed aircraft, create experimental condition in shock tunnel, and force to turn to twist device position in model installation brilliant
Set front and back placement sensor measurement model surface heat flow so that brilliant is installed on two dimensional inlet compressing surface and forces to turn to twist position
It sets and (is judged by surface heat flow and electric signal) in laminar region；When experiment, forced before and after turning to twist by comparing brilliant is installed
The hot-fluid of sensor determines along the change curve of flow direction and turns to twist the fluidised form before and after device, verifies brilliant and forces to turn to twist device
Turn to twist effect.
For lifting body/Waverider air suction type high-speed aircraft, this method includes following procedure：
First, it refers to keeping Mach constant to select shock tunnel and trystate, trystate according to trajectory condition,
Adjust Reynolds number and the angle of attack so that force to turn to keep laminar condition before twisting device installation site downstream 0.5m；
Step 2 determines the maximum contracting ratio for forcing to turn to twist device experiment model according to the size of shock tunnel and parameter, really
Determining test model forces the installation site that flows to for turning to twist device to compare position to flow to the contracting of installation site under flying condition；
Step 3 calculates and forces to turn under trystate to twist the enthalpy boundary layer thickness that device flows to installed position, (enthalpy
Boundary layer thickness refers to h0=0.99h0,∞Place between wall surface at a distance from, h0Refer to the total enthalpy along wall surface normal locality, h0, ∞Refer to
The total enthalpy of incoming) take pressure turn twist device installed position open up to the maximum enthalpy boundary layer thickness in section be δ.Choose 5 kinds not
It is level to force to turn to twist a device (ensuring that is more than a benchmark, two are less than benchmark, it is necessary to have δ=0 k/ to compare), benchmark shape
State k/ δ=n0 are consistent with the design criteria under flying condition, separately take k/ δ=n1, n2, n3,0, wherein n0<n1<=1.0, n0>
n2>n3>0, k indicates the height for forcing to turn to twist device coarse cell；
Step 4 is carried out under identical test state, and 5 kinds of different height k/ δ turn the experiment for forcing to turn to twist device, is obtained different
Height forces to turn to twist the heat flux distribution before and after device；
When experiment, carry out first do not install brilliant turn twist pressure turn twist device (i.e. two dimensional inlet compressing surface be it is smooth
Face) shock tunnel calorimetric test, analyze its along flow direction fluidized―bed furnace；Flow State Analysis is into need to be according to the telecommunications of thermal sensors
Number and CFD calculate laminar flow and turbulent flow result judged；After the completion of the experiment of shiny surface, it is ensured that installation brilliant is forced to turn
It is laminar flow to twist the fluidised form before 0.5 meter of position downstream, then carries out installation and forces the experiment for turning to twist device；Will twice test result into
Row comparative analysis determines that brilliant forces the effect for turning to twist device.
Step 5 analyzes test result, determines the validity for turning to twist design criteria；The heat before and after device is twisted according to pressure turn
Flow distribution with without force turn twist device when heat flux distribution compared with, determine force turn twist device a starting altitude h_incipient,
Critical altitude h_critical and effective height h_effective.
If benchmark k/ δ are greater than or equal to effective height, it is effective that determinating reference k/ δ turn to twist device, includes specifically following
Several situations：
If benchmark k/ δ=n0<H_incipient, illustrates to turn that twist device invalid；If h_incipient<K/ δ=n0<h_
Critical explanations turn to twist device effectively but effect unobvious；If h_critical=<K/ δ=n0<H_effective, explanation
Turn twist device turn twist it is with obvious effects；If k/ δ=n0>=h_effective illustrates to turn to twist device effect and reach best, flowing one
Cross pressure turn twist device begin to turn twist.Under normal circumstances, turn to twist device design criteria k/ δ=n0 to be preferably effective height.
It is noted that when test model point layout, need to force to turn to twist device forward position flow direction 2~3 measuring points of arrangement,
It is forcing to turn to twist in device downstream (0,0.75m) range to arrange several measuring points along flow direction, according to current measuring technique, measuring point
(such as installation platinum film heat flow transducer) minimum 10mm of spacing；Measuring point need to be arranged within the scope of the flow field for forcing to turn to twist device control.
Specifically, test result is shown in Fig. 3, in figure, solid black lines indicate the full turbulent flows of CFD calculate hot-fluid result (known technology,
See《Fluid Mechanics Computation method and application》, Yan Chao, publishing house of BJ University of Aeronautics ＆ Astronautics), black chain-dotted line indicates that CFD is entirely rapid
Stream calculation hot-fluid result (known technology), it is to force that other symbolic indication different heights, which force the test result for turning to twist device, x0,
Turn to twist the installation site of device.As seen from the figure, be not added with force turn twist device when, x<The measuring point of x1 is in laminar condition (examination
Test heat flow value and be less than or equal to laminar flow calculated value), at the position of x=x1 testing heat flow value starts from laminar flow calculated value to turbulent flow
Calculated value develops, therefore the position of x=x1 is to turn to twist position, and in the downstreams x=x1, flowing develops into turbulent flow (experiment hot-fluid quickly
Value is suitable with turbulent flow calculated value)；For with forcing to turn to twist the test result of device, " 0, n0, n1, n2, n3 " indicates different height
Pressure turn to twist device, turn to twist position ratio and be not added with when pressure turns to twist device obviously upward downstream, force to turn through analyzing brilliant
Device starting altitude is twisted as k/ δ=n3, critical altitude k/ δ ∈ (n2, n0), effective height k/ δ=n0, and benchmark k/ δ=n0, because
This judgement is forced to turn to twist device verification effectively.(definition of starting altitude, critical altitude, effective height is referring to document《High speed air inlet
It forces to turn to twist experiment in road boundary layer》, Zhao Hui is brave etc., experimental fluid mechanics, 2012,26 (1)).
A kind of high-speed aircraft provided in an embodiment of the present invention is forced to turn to twist device verification method, carries out identical test state
Under, 5 kinds of different height k/ δ turn the experiment for forcing to turn to twist device, obtain different height and force to turn to twist the heat flux distribution before and after device；
According to the heat flux distribution for forcing to turn to twist before and after device with without heat flux distribution when forcing to turn to twist device compared with, verification is forced turn to twist dress
It sets and turns to twist effect, this method operability is strong, and verification the verifying results are easy to identify, at low cost.This method is successfully verified.
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 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 (3)
1. a kind of high-speed aircraft is forced to turn to twist device verification method, which is characterized in that this method is inhaled for lifting body/Waverider
Gas formula high-speed aircraft, this method include following procedure：
Step 1, it refers to keeping Mach not to select shock tunnel and trystate, the trystate according to trajectory condition
Become, adjust Reynolds number and the angle of attack so that forces to turn to keep laminar condition before twisting 0.5 meter of device installation site downstream；
Step 2 determines the maximum contracting ratio for forcing to turn to twist device experiment model according to the size of shock tunnel and parameter, determines examination
Testing model forces the installation site that flows to for turning to twist device to compare position to flow to the contracting of installation site under flying condition；
Step 3 calculates and forces to turn under trystate to twist the enthalpy boundary layer thickness that device flows to installed position, pressure is taken to turn
It is δ to twist device installed position and open up to the maximum enthalpy boundary layer thickness in section, and the pressure for choosing 5 kinds of different heights turns to twist dress
It sets, it is ensured that one is more than benchmark, and two are less than benchmark, while having δ=0 k/ to compare, normal condition k/ δ=n0 and flying condition
Under design criteria it is consistent, separately take k/ δ=n1, n2, n3,0, wherein n0<n1<=1.0, n0>n2>n3>0, k indicates to force to turn
Twist the height of device coarse cell；
Step 4 is carried out under identical test state, and 5 kinds of different height k/ δ turn the experiment for forcing to turn to twist device, obtain different height
It forces to turn to twist the heat flux distribution before and after device；
Step 5, according to the heat flux distribution for forcing to turn to twist before and after device with without heat flux distribution when forcing turn to twist device compared with, really
The fixed starting altitude h_incipient, critical altitude h_critical and effective height h_effective for forcing to turn to twist device；
If benchmark k/ δ=n0<It is invalid to twist device for h_incipient, then pressure turn；If h_incipient<K/ δ=n0<h_critical
Then pressure turns to twist device effectively but effect unobvious；If h_critical=<K/ δ=n0<H_effective then forces to turn to twist
Device turns to twist with obvious effects；If k/ δ=n0>=h_effective then forces to turn to twist device effect and reach best.
2. according to the method described in claim 1, it is characterized in that, during experiment, twists device forward position in pressure turn and flow to cloth
2~3 measuring points are set, are forcing to turn to twist in device downstream (0,0.75m) range to arrange several measuring points along flow direction.
3. according to the method described in claim 2, it is characterized in that, measuring point spacing be more than 10mm, and point layout force turn
Within the scope of the flow field for twisting device control.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109900486A (en) * | 2019-03-04 | 2019-06-18 | 北京空天技术研究所 | A kind of winged hot aeroperformance acquisition methods of aircraft of band |
| CN110806300A (en) * | 2019-10-12 | 2020-02-18 | 北京临近空间飞行器系统工程研究所 | Measuring point arrangement method suitable for hypersonic flight test transition research |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4214210B2 (en) * | 2005-06-08 | 2009-01-28 | 独立行政法人 宇宙航空研究開発機構 | Measurement of Reynolds number using boundary layer turbulent transition phenomenon |
| DE102011054434A1 (en) * | 2011-10-12 | 2013-04-18 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Arrangement for wind tunnel for aerodynamic investigation of vehicle e.g. motor car on road, has nozzle drive belt that is arranged at sections of tapered transition section between inlet cross-section and outlet section |
| CN103954425A (en) * | 2014-04-30 | 2014-07-30 | 北京大学 | Hypersonic velocity static wind tunnel nozzle design method and hypersonic velocity static wind tunnel nozzle transition position determining method |
| CN104280205A (en) * | 2014-10-24 | 2015-01-14 | 中国人民解放军国防科学技术大学 | Supersonic velocity laminar flow spraying pipe and supersonic velocity quiet wind tunnel thereof |
| CN106122189A (en) * | 2016-07-18 | 2016-11-16 | 南京航空航天大学 | A kind of hypersonic precursor based on structure partial pressure differential disturbance turns twists control method |
| CN106872195A (en) * | 2017-01-06 | 2017-06-20 | 北京临近空间飞行器系统工程研究所 | A kind of association analysis method of high-speed aircraft Aerodynamic Heating test flight data |
| CN106885685A (en) * | 2017-04-06 | 2017-06-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of dual airfoil test model for flow transition detection |
-
2017
- 2017-08-16 CN CN201710703407.4A patent/CN108304603A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4214210B2 (en) * | 2005-06-08 | 2009-01-28 | 独立行政法人 宇宙航空研究開発機構 | Measurement of Reynolds number using boundary layer turbulent transition phenomenon |
| DE102011054434A1 (en) * | 2011-10-12 | 2013-04-18 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Arrangement for wind tunnel for aerodynamic investigation of vehicle e.g. motor car on road, has nozzle drive belt that is arranged at sections of tapered transition section between inlet cross-section and outlet section |
| CN103954425A (en) * | 2014-04-30 | 2014-07-30 | 北京大学 | Hypersonic velocity static wind tunnel nozzle design method and hypersonic velocity static wind tunnel nozzle transition position determining method |
| CN104280205A (en) * | 2014-10-24 | 2015-01-14 | 中国人民解放军国防科学技术大学 | Supersonic velocity laminar flow spraying pipe and supersonic velocity quiet wind tunnel thereof |
| CN106122189A (en) * | 2016-07-18 | 2016-11-16 | 南京航空航天大学 | A kind of hypersonic precursor based on structure partial pressure differential disturbance turns twists control method |
| CN106872195A (en) * | 2017-01-06 | 2017-06-20 | 北京临近空间飞行器系统工程研究所 | A kind of association analysis method of high-speed aircraft Aerodynamic Heating test flight data |
| CN106885685A (en) * | 2017-04-06 | 2017-06-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of dual airfoil test model for flow transition detection |
Non-Patent Citations (3)
| Title |
|---|
| BERRY,ET AL.: ""Boundary layer transition on X-43A"", 《ＡＩＡＡFLUID DYNAMICS CONFERENCE》 * |
| 战培国: ""超燃冲压发动机前体边界层转捩风洞"", 《航空科学技术》 * |
| 赵慧勇等: ""高超声速进气道边界层强制转捩试验"", 《实验流体力学》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109900486A (en) * | 2019-03-04 | 2019-06-18 | 北京空天技术研究所 | A kind of winged hot aeroperformance acquisition methods of aircraft of band |
| CN109900486B (en) * | 2019-03-04 | 2020-12-08 | 北京空天技术研究所 | Method for acquiring thermal aerodynamic performance of aircraft with flight |
| CN110806300A (en) * | 2019-10-12 | 2020-02-18 | 北京临近空间飞行器系统工程研究所 | Measuring point arrangement method suitable for hypersonic flight test transition research |
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