CN106596038B - The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic - Google Patents
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic Download PDFInfo
- Publication number
- CN106596038B CN106596038B CN201611252569.2A CN201611252569A CN106596038B CN 106596038 B CN106596038 B CN 106596038B CN 201611252569 A CN201611252569 A CN 201611252569A CN 106596038 B CN106596038 B CN 106596038B
- Authority
- CN
- China
- Prior art keywords
- current
- aspiration rates
- hypersonic
- wind tunnel
- supersonic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
Abstract
The invention discloses a kind of calculation methods of the mute wind tunnel nozzle suction flow of supersonic and hypersonic, applied in the mute wind tunnel nozzle of supersonic and hypersonic, the calculation method of the mute wind tunnel nozzle suction flow of the supersonic and hypersonic is comprising steps of obtain current test gas flow and current intake-gas flow；According to the current test gas flow of acquisition and current intake-gas flow, current aspiration rates are calculated.The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention, current aspiration rates are calculated by the current test gas flow and current intake-gas flow of the hypersonic mute wind tunnel nozzle of acquisition, and the performance level of hypersonic mute wind tunnel nozzle is assessed by calculated current aspiration rates, to adjust out the aspiration rates of optimum state, to improve nozzle performance and flow field quality, the turbulivity and noise of jet pipe is greatly reduced, reaches the level of mute wind-tunnel.
Description
Technical field
The present invention relates to aerospace fields, particularly, are related to a kind of mute wind tunnel nozzle pumping of supersonic and hypersonic
Inhale the calculation method of flow.
Background technique
Wind tunnel experiment refers in a pipeline by certain requirement design, drives one controllable using power device
Experimental model is fixed in the trial zone of pipeline by air-flow, and carries out various skies according to motion composition and similarity principle
Aerodynamic force experiment obtains model experiment data to simulate aerial various state of flights.Hypersonic wind tunnel is one kind of wind-tunnel,
It is widely used in the model experiments such as guided missile, aircraft and rocket, is a basic experimental facilities in aerospace field.
There are higher aerodynamic noise and turbulivity, " peace and quiet " than upper atmosphere are flowed in common hypersonic wind tunnel flow field
High 1~2 order of magnitude in field, therefore model is tested in common hypersonic wind tunnel, the accuracy of certain test results
Substantial deviation truth, to influence the design objective of aircraft etc..
Need to study a kind of reduction aerodynamic noise and turbulivity thus, and (high-altitude is big with the upper atmosphere of hypersonic wind tunnel
The turbulivity of gas generally only has 0.03%) close hypersonic mute wind-tunnel.Hypersonic mute wind-tunnel is hypersonic wind
The one kind in hole is performance and a kind of best wind-tunnel of flow field quality in hypersonic wind tunnel.
Jet pipe is the critical component of hypersonic wind tunnel, jet pipe be mounted on wind-tunnel stable section downstream and test section it is upper
Trip.As shown in Figure 1, traditional jet pipe generally comprises 30 three parts of shrinking zone 10, venturi area 20 and expansion regions, shrinking zone 10 is a company
The continuous type face shunk, venturi area 20 are the smallest part of curve diameter, and expansion regions 30 are a continuous widened type face, venturi area 20
Shrinking zone 10 and the seamless connection of expansion regions 30 are got up, whole jet pipe curve is formed.
Referring to Fig. 1, test model 100 is tested at nozzle exit 11.In order to generate hypersonic gas in test section
Air-flow is uniformly accelerated to the velocity of sound from low subsonic speed by stream, the shrinking zone 10 of jet pipe, and then air-flow is since the throat region of jet pipe 20
The uniform accelerated expansion of constant entropy, until the nozzle exit 11 in nozzle-divergence area 30 reaches required Mach number, therefore jet pipe is to guarantee
Experimental section obtains the important wind tunnel component of design Mach number.
To obtain hypersonic mute wind-tunnel, the design of jet pipe is most important, it is desirable that the design of jet pipe reaches laminar flow jet pipe
Level, so-called laminar flow jet pipe, that is the flowing of nozzle surface must be laminar boundary layer, still, as shown in Figure 1, traditional
Jet pipe its inner surface almost all be turbulent boundary layer 12, and the jet pipe of turbulent boundary layer 12 be impossible obtain it is hypersonic
Mute wind-tunnel.
In order to reach hypersonic mute wind-tunnel design requirement, traditional Nozzle Design has been unable to meet requirement, for this purpose, right
Traditional jet pipe needs are transformed, and hypersonic mute wind tunnel nozzle structure as shown in Figure 2 are generally configured to, hypersonic
In mute wind tunnel nozzle structure, jet pipe " is interrupted " in venturi position, curve of the jet pipe in venturi area 20 is no longer continuous, by jet pipe
It is divided into four parts, i.e. shrinking zone 10, suction district 40, venturi area 20 and expansion regions 30, the effect of suction district 40 is by shrinking zone 10
The shrinking zone turbulent boundary layer 13 of wall surface development aspirates away, eliminates influence of the front turbulent flow to jet pipe downstream, maintains jet pipe
Wall boundary layer is laminar flow；Since Flow Field in Wind Tunnel quality and jet pipe wall boundary layer laminar flow length have substantial connection, jet pipe wall surface
Boundary layer laminar flow length is longer, and the flow field quality of jet pipe is better.Therefore nozzle performance and flow field quality can be improved in this measure, substantially drops
The turbulivity and noise of low jet pipe, reach the level of mute wind-tunnel.
Fig. 3 show the mute jet pipe transition figure with boundary layer suction, and as can be seen from Fig., suction district 40 will be shunk
The turbulent boundary layer 12 of 10 wall surface of area development aspirates away, since turbulent boundary layer 12 is pumped, since venturi area 20, and boundary
Layer restarts to generate, and the boundary layer started at this time is laminar boundary layer 14, development of the laminar boundary layer 14 Jing Guo a distance
Become turbulent boundary layer 12 again, as shown in figure 3, be laminar boundary layer 14 between the T point of venturi area 20 to expansion regions 30, but layer
Laminar boundary layer 14 can not maintain the length of entire expansion regions 30, that is to say, that laminar boundary layer 14 does not reach ideal
C point, but begin to turn to twist to the flowing of T point.Since the T point that 12 turns of turbulent boundary layer are twisted, Mach wave is downstream radiated, turbulent flow
The noise radiation in boundary layer 12 influences downstream area TEFC, is not the mute test area of mute wind tunnel nozzle.
According to hypersonic aerodynamics knowledge, hypersonic nozzle model test region is four side of diamond shape of CSDF
Shape.According to the above analysis, the rhombic quadrangles of CSDF subtract the noise region CAEF and DBEF of downstream Turbulent Flow Effects, for superb
The test diamond-shaped area 26 of the mute wind-tunnel of the velocity of sound is exactly the rhombic quadrangles of ASBE, and the length of mute test area is Δ X, height
It is a very important index for measuring mute performance of wind tunnel for Δ Y, the length Δ X of mute trial zone.
As shown in Figure 4, it is assumed that the total gas couette of front incoming flow is Q0, by suction seam by the intake-gas stream of 41 abstraction
Amount is Q2, then remaining test gas flow is Q1, according to flow conservation law: Q0=Q1+Q2.The gas being pumped is by suction
Seam 41 reaches suction air collecting chamber 42, sprays after suction air collecting chamber 42 is stablized from compression ring 44 out, compression ring 44 and shrinking zone 10 are logical out
Cross adjustment gasket 43 connection, adjustment gasket 43 with a thickness of L, wherein adjustment gasket 43 can replace, i.e., thickness L can change.
It is told about according to front, jet pipe incoming flow test gas flow Q1, continues to flow toward jet pipe area, area constantly shrinks change
Small, gas constantly accelerates, and when the position for reaching venturi 0, test gas reaches velocity of sound, the radius r of venturi 0 be mute jet pipe most
Small value is constantly accelerated by the air-flow after venturi toward downstream flow, preferably in nozzle exit according to supersonic nozzle flow principles
11 reach supersonic speed or hypersonic speed, this is also Laval nozzle basic principle.According to the base of aerodynamics Supersonic Flow
Present principles, the value of r determine test gas uninterrupted.
12 turbulent flow Q2 of turbulent boundary layer similar with the flowing of test gas flow Q1, that suction seam 41 is taken away, and pass through
Suction seam 41 first shrinks the process expanded afterwards, as shown in figure 5, suction venturi position is AB, AB length is suction seam minimum position,
Equally, according to the basic principle of aerodynamics Supersonic Flow, AB length determines the value of intake-gas flow Q2.
As previously described, the maximum feature of the mute wind tunnel nozzle of supersonic and hypersonic is exactly by 10 wall surface of shrinking zone
The turbulent boundary layer 12 of development aspirates away, eliminates influence of the front turbulent flow to jet pipe downstream, maintains jet pipe wall boundary layer
For laminar flow.Therefore nozzle performance and flow field quality can be improved in this measure, and the turbulivity and noise of jet pipe is greatly reduced, reaches mute wind
The level in hole.It is maximum different with routine jet pipe that suction seam 41 is exactly hypersonic mute wind tunnel nozzle, aspiration number
Determine the performance indicator of mute jet pipe, in general, it is ratio that it is about 15%-25% that suction flow, which accounts for the percentage of total flow,
Appropriate, most suitable numerical value is 20%, i.e. Q2/Q0=20%, when intake-gas flow Q2 accounts for total gas couette Q0Hundred
Point than being lower than 15%, it is possible to aspirate very few, do not take the turbulent flow of turbulent boundary layer 12 all away, remaining turbulent boundary layer 12 according to
So it will affect downstream Nozzle Flow, to influence nozzle performance；Total gas couette Q is accounted for when inhaling gas flow Q20High percentage
In 25%, it is possible to which suction is excessive, and suction stitches 41 pairs of mainstreams and generates disturbance, equally influence nozzle performance.Both the above situation is equal
Be difficult to obtain hypersonic mute jet pipe, thus design suction flow account for total flow percentage it is extremely important, directly affect
To wind-tunnel design whether successful key factor.However, not providing the mute wind-tunnel of supersonic and hypersonic in the prior art
The calculation method of jet pipe suction flow.
Therefore, the suction flow size for how calculating the mute jet pipe of supersonic and hypersonic is one urgently to be resolved
Problem.
Summary of the invention
The present invention provides a kind of calculation methods of the mute wind tunnel nozzle suction flow of supersonic and hypersonic, to solve
The technical issues of suction flow size of the mute jet pipe of supersonic and hypersonic calculates.
The technical solution adopted by the invention is as follows:
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention is applied to ultrasound
In fast and hypersonic mute wind tunnel nozzle, the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic includes
Step:
Obtain current test gas flow and current intake-gas flow；
According to the current test gas flow of acquisition and current intake-gas flow, current aspiration rates are calculated.
Further, according to the current test gas flow of acquisition and current intake-gas flow, current suction is calculated
After the step of rate further include:
According to calculated current aspiration rates, determine whether current aspiration rates reach optimum state.
Further, according to calculated current aspiration rates, the step of whether current aspiration rates reach optimum state determined
Include:
Calculated current aspiration rates and preset aspiration rates threshold value are compared, whether are reached with the current aspiration rates of determination
To optimum state.
Further, according to calculated current aspiration rates, the step of whether current aspiration rates reach optimum state determined
Later further include:
If calculated current aspiration rates have reached optimum state, current aspiration rates are not adjusted；If calculated current
Aspiration rates are not up to optimum state, then adjust current aspiration rates.
Further, if calculated current aspiration rates are wrapped the step of being not up to optimum state, adjust current aspiration rates
It includes:
Current aspiration rates are adjusted by replacing the current adjustment gasket being arranged on suction air collecting chamber.
Further, the step of current aspiration rates is adjusted by replacing the current adjustment gasket being arranged on suction air collecting chamber
Suddenly include:
It keeps out compression ring and jet pipe area fixed, adjusts current suction by adjusting the thickness of current adjustment gasket
Rate.
Further, it keeps out compression ring and jet pipe area fixed, is adjusted by adjusting the thickness of current adjustment gasket
The step of current aspiration rates includes:
If calculated current aspiration rates are less than preset aspiration rates threshold value, the thickness of current adjustment gasket is reduced；If
Calculated current aspiration rates are greater than preset aspiration rates threshold value, then increase the thickness of current adjustment gasket.
Further, it keeps out compression ring and jet pipe area fixed, is adjusted by adjusting the thickness of current adjustment gasket
The step of current aspiration rates includes:
According to the thickness of the adjustment gasket after replacement, intake-gas flow after adjustment is calculated；
According to intake-gas flow after calculated adjustment, aspiration rates after adjustment are obtained.
Further, current aspiration rates are as follows:
Wherein, rARadius in suction seam minimum position between the endpoint in jet pipe area, rBFor in suction seam minimum position
Far from jet pipe area endpoint between radius, r be jet pipe area venturi minimum position radius, a be suction seam minimum position with it is vertical
Angle between line.
Further, the aspiration rates after reducing the thickness of current adjustment gasket are as follows:
And
Aspiration rates after increasing the thickness of current adjustment gasket are as follows:
Wherein, rAFor the radius in suction seam minimum position between the endpoint in jet pipe area, rBMinimum position is stitched for suction
In far from jet pipe area endpoint between radius, r be jet pipe area venturi minimum position radius, a be suction seam minimum position and hang down
Angle between straight line, d are adjustment thickness.
The invention has the following advantages:
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention is super by obtaining
The current test gas flow and current intake-gas flow of the velocity of sound and hypersonic mute wind tunnel nozzle calculates current suction
Rate, and the performance level of hypersonic mute wind tunnel nozzle is assessed by calculated current aspiration rates, it is best to adjust out
The aspiration rates of state are greatly reduced the turbulivity and noise of jet pipe, reach mute wind to improve nozzle performance and flow field quality
The level in hole.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to figure, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the structural schematic diagram of traditional jet pipe；
Fig. 2 is the structural schematic diagram of the hypersonic mute wind tunnel nozzle with boundary layer suction；
Fig. 3 is the transition schematic diagram of the hypersonic mute wind tunnel nozzle with boundary layer suction；
Fig. 4 is the structural schematic diagram of the hypersonic mute wind tunnel nozzle with boundary suction socket；
Hypersonic mute wind tunnel nozzle enlarged schematic partial view in Fig. 5 figure 4 above with boundary suction socket；
Fig. 6 is the pumping and seam minimum position schematic diagram of the mute jet pipe with boundary suction socket；
Fig. 7 is the partial enlargement diagram of Fig. 6；
Fig. 8 is that the calculation method first of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention is real
Apply the flow diagram of example；
Fig. 9 is that the calculation method second of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention is real
Apply the flow diagram of example；
Figure 10 is the calculation method third of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention
The flow diagram of embodiment；
Figure 11 is the calculation method the 4th of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention
The flow diagram of embodiment；
Figure 12 is to keep out compression ring and jet pipe area fixed described in Figure 11, by adjusting the thickness of current adjustment gasket
Come the refinement flow diagram for the step of adjusting current aspiration rates.
Drawing reference numeral explanation:
10, shrinking zone；11, nozzle exit；12, turbulent boundary layer；13, shrinking zone turbulent boundary layer；14, wake boundary
Layer；15, transition range domain；20, venturi area；21, skip zone starting point；22, skip zone end point；23, turbulent boundary layer Mach wave
Radiation；24, nozzle exit wall surface；25, shock wave is exported；26, static test rhomboid；30, expansion regions；40, suction district；41, it aspirates
Seam；42, air collecting chamber is aspirated；43, gasket is adjusted；44, go out compression ring；50, jet pipe area；100, test model；200, BC annulus area.
Specific embodiment
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Referring to Fig. 8, the preferred embodiment of the present invention provides a kind of mute wind tunnel nozzle suction of supersonic and hypersonic
The calculation method of flow is applied in the mute wind tunnel nozzle of supersonic and hypersonic, as shown in figure 3, supersonic speed and Gao Chaosheng
The mute wind tunnel nozzle of speed includes shrinking zone 10, venturi area 20, expansion regions 30 and suction district 40, the mute wind of supersonic and hypersonic
The calculation method of hole jet pipe suction flow comprising steps of
Step S100, current test gas flow and current intake-gas flow are obtained.
As shown in Figure 4, it is assumed that Incoming gas temperature is T0, and gas pressure P0, area under control venturi minimum position radius is r,
Current test gas flow Q1 can be then obtained with following formula:
Wherein, for air, γ=1.4, R=287J/ (kg.K), P0 is gas pressure, and unit is Pascal；T0 is gas
Temperature, unit are thermodynamic temperature K；R is area under control venturi minimum position radius, and unit is m, and Q1 is current test gas stream
Amount, unit is kg/s.
As shown in figure 5, the hypersonic mute wind tunnel nozzle enlarged schematic partial view in Fig. 5 figure 4 above with boundary suction socket,
Wherein, AB is suction seam minimum position, and area is stitched in the suction for first calculating AB, which is cirque structure.
By measurement, the radius r in suction seam minimum position AB between the endpoint in jet pipe area is obtainedA, suction seam is most
The radius r between endpoint in small position far from jet pipe areaB, the phase of the angle a between suction seam minimum position AB and vertical line
Close numerical value.
As shown in fig. 6, really circulation area is AB annulus, after the circulation area that can first calculate BC annulus, then come
To the area of AB annulus.
Referring to Fig. 6, BC annulus area 200 are as follows:
SBC=π (rB 2-rA 2) (2)
The then area of AB annulus:
SAB=SBC/ cosa=π (rB 2-rA 2)/cosa (3)
Intake-gas flow Q2 is obtained by following formula:
Wherein, for air, γ=1.4, R=287J/ (kg.K), P0 is gas pressure, and unit is Pascal；T0 is gas
Temperature, unit are thermodynamic temperature K；R is area under control venturi minimum position radius, and unit is m, and Q2 is intake-gas flow, single
Position is kg/s.
Step S200, according to the current test gas flow of acquisition and current intake-gas flow, current suction is calculated
Rate.
Current aspiration rates (percentage that current suction flow accounts for current total flow), are calculated by following formula and are obtained:
Wherein, Q1 is current test gas flow, and Q2 is current intake-gas flow, and rA suction is stitched close in minimum position
Radius between the endpoint in jet pipe area, rBFor the radius between the endpoint far from jet pipe area in suction seam minimum position, r is jet pipe
Area's venturi minimum position radius, a are the angle between suction seam minimum position and vertical line.
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided in this embodiment, passes through acquisition
The current test gas flow of the mute wind tunnel nozzle of supersonic and hypersonic and current intake-gas flow calculate current pumping
Suction rate, and the performance level of hypersonic mute wind tunnel nozzle is assessed by calculated current aspiration rates, to adjust out most
The aspiration rates of good state are greatly reduced the turbulivity and noise of jet pipe, reach mute to improve nozzle performance and flow field quality
The level of wind-tunnel.
As shown in figure 9, Fig. 9 is the calculating of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention
The flow diagram of method second embodiment, on the basis of first embodiment, supersonic speed provided in this embodiment and Gao Chaosheng
The calculation method of the mute wind tunnel nozzle suction flow of speed, after step S200 comprising steps of
Step S300, according to calculated current aspiration rates, determine whether current aspiration rates reach optimum state.
Calculated current aspiration rates η and preset aspiration rates threshold value are compared, with the current aspiration rates η of determination whether
Reach optimum state.Wherein, it is 15% -25% that preset aspiration rates threshold value, which is range, most preferably 20%.If calculating current
Aspiration rates η in preset aspiration rates threshold value, then does not need to readjust aspiration rates.
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided in this embodiment, according to calculating
Current aspiration rates out, determine whether current aspiration rates reach optimum state, to adjust out the aspiration rates of optimum state, to mention
High nozzle performance and flow field quality are greatly reduced the turbulivity and noise of jet pipe, reach the level of mute wind-tunnel.
As shown in Figure 10, Figure 10 is the meter of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention
The flow diagram of calculation method 3rd embodiment, on the basis of second embodiment, supersonic speed provided in this embodiment and superb
The calculation method of the mute wind tunnel nozzle suction flow of the velocity of sound, after step S300 comprising steps of
If step S400, calculated current aspiration rates have reached optimum state, current aspiration rates are not adjusted；If calculating
Current aspiration rates out are not up to optimum state, then adjust current aspiration rates.
If calculated current aspiration rates are in the range of preset aspiration rates threshold value, i.e., in 15% -25% range,
Current aspiration rates are not adjusted then；If calculated current aspiration rates do not exist not in the range of preset aspiration rates threshold value
In 15% -25% range, then current aspiration rates are adjusted.
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided in this embodiment, according to calculating
Current aspiration rates out, determine whether current aspiration rates reach optimum state, if so, being not required to settled preceding aspiration rates；If it is not, then
The aspiration rates of optimum state need to be readjusted out, to improve nozzle performance and flow field quality, the turbulivity of jet pipe is greatly reduced
And noise, reach the level of mute wind-tunnel.
As shown in figure 11, Figure 11 is the meter of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided by the invention
The flow diagram of calculation method fourth embodiment, on the basis of 3rd embodiment, supersonic speed provided in this embodiment and superb
The calculation method of the mute wind tunnel nozzle suction flow of the velocity of sound, after step S400 comprising steps of
Step S500, current aspiration rates are adjusted by replacing the current adjustment gasket being arranged on suction air collecting chamber.
In the present embodiment, as shown in figure 4, current adjustment gasket can be replaced, current adjustment spacer thickness is allowed to become
Change.It first keeps out compression ring and jet pipe area fixed, then adjusts current suction by adjusting the thickness of current adjustment gasket
Rate.If calculated current aspiration rates are less than preset aspiration rates threshold value, the thickness of current adjustment gasket is reduced；If calculating
Current aspiration rates be greater than preset aspiration rates threshold value, then increase the thickness of current adjustment gasket.
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided in this embodiment, passes through replacement
Current adjustment gasket on suction air collecting chamber is set to adjust current aspiration rates, so that nozzle performance and flow field quality are improved,
The turbulivity and noise of jet pipe is greatly reduced, reaches the level of mute wind-tunnel.
As shown in figure 12, the calculating side of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided in this embodiment
Method, step S500 are specifically included:
Step S510, according to the thickness of the adjustment gasket after replacement, intake-gas flow after adjustment is calculated.
Step S520, according to intake-gas flow after calculated adjustment, aspiration rates after adjustment are obtained.
One, assume to want to increase suction flow, then current adjustment gasket is replaced, by the thickness of the adjustment gasket after replacement
Degree reduces d, then shrinking zone can move right d as a rigid body, d distance, such as Fig. 7 then B point position can accordingly move right
Shown, B point will be moved into B1, and C point is moved to C1 point, to form new triangle AB1C1, angle a1Greater than a, it is clear that B1C1
The circulation area for projecting annulus is equal with the BC projection circulation area of annulus, as long as therefore calculating a1Size, so that it may calculate
Suction flow Q after reducing the thickness of current adjustment gasket2'。
As shown in Figure 7, the length between AC are as follows:
LAC=(rB-rA)×tan a (6)
Wherein, rARadius in suction seam minimum position between the endpoint in jet pipe area, rBFor in suction seam minimum position
Radius between endpoint far from jet pipe area, a are the angle between suction seam minimum position and vertical line.
On the basis of formula (6), a is acquired1:
At this point, reducing the suction flow Q after the current thickness for adjusting gasket2' are as follows:
So, the aspiration rates after reducing the thickness of current adjustment gasket are as follows:
By formula (9) it is found that the suction flow for reducing the aspiration rates after the current thickness for adjusting gasket increases.
Two, assume to want to reduce suction flow, then the thickness of the adjustment gasket after replacement is increased into d, shrinking zone is as one
Rigid body can be moved to the left d, it is clear that B point can be moved to the left d distance, using method like above, can find out the current adjustment of increase
Suction flow Q after the thickness of gasket2":
So, the aspiration rates after increasing the thickness of current adjustment gasket are as follows:
Wherein, rARadius in suction seam minimum position between the endpoint in jet pipe area, rBFor in suction seam minimum position
Far from jet pipe area endpoint between radius, r be jet pipe area venturi minimum position radius, a be suction seam minimum position with it is vertical
Angle between line, d are adjustment thickness.
By formula (11) it is found that the suction flow for increasing the aspiration rates after the current thickness for adjusting gasket reduces.
The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic provided in this embodiment, in reality
It tests room and has carried out test of many times, the present embodiment provides the mute wind tunnel nozzle suction streams of supersonic and hypersonic for experiment results proved
The calculation method of amount is correct, and test result is good.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (9)
1. a kind of calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic is applied to supersonic speed and Gao Chaosheng
In the mute wind tunnel nozzle of speed, which is characterized in that the calculating side of the mute wind tunnel nozzle suction flow of supersonic and hypersonic
Method comprising steps of
Obtain current test gas flow and current intake-gas flow, wherein current test gas flow
Current intake-gas flowγ=1.4, R=287J/
(kg.K), P0For gas pressure, T0For gas temperature, r is area under control venturi minimum position radius, rAFor in suction seam minimum position
Radius between the endpoint in jet pipe area, rBFor the radius between the endpoint far from jet pipe area in suction seam minimum position, a is
Angle between suction seam minimum position and vertical line；
According to the current test gas flow of acquisition and current intake-gas flow, current aspiration rates, aspiration rates are calculated
2. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 1, special
Sign is that the current test gas flow and current intake-gas flow according to acquisition calculates the step of current aspiration rates
After rapid further include:
According to calculated current aspiration rates, determine whether current aspiration rates reach optimum state.
3. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 2, special
Sign is,
It is described according to calculated current aspiration rates, determine that the step of whether current aspiration rates reach optimum state includes:
Calculated current aspiration rates and preset aspiration rates threshold value are compared, whether are reached most with the current aspiration rates of determination
Good state.
4. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 2 or 3,
It is characterized in that,
It is described according to calculated current aspiration rates, determine also wrap after the step of whether current aspiration rates reach optimum state
It includes:
If calculated current aspiration rates have reached optimum state, current aspiration rates are not adjusted；If calculated current suction
Rate is not up to optimum state, then adjusts current aspiration rates.
5. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 4, special
Sign is,
If the step of calculated current aspiration rates are not up to optimum state, adjust current aspiration rates includes:
Current aspiration rates are adjusted by replacing the current adjustment gasket being arranged on suction air collecting chamber.
6. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 5, special
Sign is,
It is described to include: the step of adjusting current aspiration rates by replacing the current adjustment gasket being arranged on suction air collecting chamber
It keeps out compression ring and jet pipe area fixed, adjusts current aspiration rates by adjusting the thickness of current adjustment gasket.
7. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 6, special
Sign is,
It is described to keep out compression ring and jet pipe area fixed, current aspiration rates are adjusted by adjusting the thickness of current adjustment gasket
The step of include:
If calculated current aspiration rates are less than preset aspiration rates threshold value, the thickness of current adjustment gasket is reduced；If calculating
Current aspiration rates out are greater than preset aspiration rates threshold value, then increase the thickness of current adjustment gasket.
8. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 7, special
Sign is,
It is described to keep out compression ring and jet pipe area fixed, current aspiration rates are adjusted by adjusting the thickness of current adjustment gasket
The step of include:
According to the thickness of the adjustment gasket after replacement, intake-gas flow after adjustment is calculated；
According to intake-gas flow after calculated adjustment, aspiration rates after adjustment are obtained.
9. the calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic according to claim 8, special
Sign is,
Aspiration rates after the thickness of the current adjustment gasket of reduction are as follows:
And
Aspiration rates after the thickness of the current adjustment gasket of increase are as follows:
Wherein, rARadius in suction seam minimum position between the endpoint in jet pipe area, rBIt is separate in suction seam minimum position
Radius between the endpoint in jet pipe area, r be jet pipe area venturi minimum position radius, a be suction seam minimum position and vertical line it
Between angle, d be adjustment thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611252569.2A CN106596038B (en) | 2016-12-30 | 2016-12-30 | The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611252569.2A CN106596038B (en) | 2016-12-30 | 2016-12-30 | The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106596038A CN106596038A (en) | 2017-04-26 |
| CN106596038B true CN106596038B (en) | 2019-03-29 |
Family
ID=58605234
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611252569.2A Active CN106596038B (en) | 2016-12-30 | 2016-12-30 | The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106596038B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108760222B (en) * | 2018-06-08 | 2020-04-21 | 中国人民解放军国防科技大学 | Silence wind tunnel nozzle with adjustable suction flow |
| CN111024359B (en) * | 2019-11-22 | 2021-12-07 | 中国航天空气动力技术研究院 | Short-time gas injection flow measuring method |
| CN112067237B (en) * | 2020-09-24 | 2023-03-14 | 北京卫星环境工程研究所 | Hypersonic wind tunnel based on plasma |
| CN112665815B (en) * | 2020-12-28 | 2023-03-21 | 中国航天空气动力技术研究院 | Low-noise flow field debugging platform |
| CN113984325B (en) * | 2021-10-11 | 2022-10-11 | 南京航空航天大学 | Device and method for improving total pressure of incoming flow of hypersonic static wind tunnel |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5099685A (en) * | 1990-08-09 | 1992-03-31 | The Boeing Company | Boundary layer control diffuser for a wind tunnel or the like |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
| CN102998084A (en) * | 2012-12-28 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Hypersonic velocity spray pipe structure |
| CN103954424A (en) * | 2014-04-30 | 2014-07-30 | 北京大学 | Method for expanding silent test area of hypersonic-velocity silent spray pipe and hypersonic-velocity spray pipe |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102043963B1 (en) * | 2013-04-25 | 2019-11-12 | (주)수도프리미엄엔지니어링 | Operation Method of Virtual Wind Tunnel |
-
2016
- 2016-12-30 CN CN201611252569.2A patent/CN106596038B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5099685A (en) * | 1990-08-09 | 1992-03-31 | The Boeing Company | Boundary layer control diffuser for a wind tunnel or the like |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
| CN102998084A (en) * | 2012-12-28 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Hypersonic velocity spray pipe structure |
| CN103954424A (en) * | 2014-04-30 | 2014-07-30 | 北京大学 | Method for expanding silent test area of hypersonic-velocity silent spray pipe and hypersonic-velocity spray pipe |
| 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 |
Non-Patent Citations (3)
| Title |
|---|
| 200高超声速风洞调试和流场校测;周勇为等;《国防科技大学学报》;20091231;第31卷(第6期);第58-61页 |
| 分布抽吸率对整车风洞试验段流场影响的数值模拟;杨帆等;《计算机辅助工程》;20081231;第17卷(第4期);第36-40页 |
| 高超声速进气道启动问题研究;王翼;《中国博士学位论文全文数据库 工程科技Ⅱ辑》;20100515(第5期);第111-121页 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106596038A (en) | 2017-04-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106596038B (en) | The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic | |
| Ito et al. | Film cooling of a gas turbine blade | |
| Mathur et al. | Base-bleed experiments with a cylindrical afterbody in supersonic flow | |
| CN102218378B (en) | Ultrasonic nonuniform flow nozzle and design method thereof | |
| Li et al. | Analysis of instabilities in non-axisymmetric hypersonic boundary layers over cones | |
| CN102323961B (en) | Asymmetric supersonic velocity spray pipe and design method thereof | |
| CN102302989B (en) | Supersonic velocity spray pipe with shared throat part and design method of supersonic velocity spray pipe | |
| CN104359647B (en) | The method determining the conical nozzle molded line of hypersonic low density wind tunnel | |
| CN105550467B (en) | The method for building up of high-speed wind tunnel inclined hole wall wall surface flow model | |
| CN108345714B (en) | Numerical simulation method for parameter design of inner annular jet flow pressure stabilizing cavity | |
| CN102998084A (en) | Hypersonic velocity spray pipe structure | |
| CN107672821B (en) | Variable Mach number parallel wide-speed-range waverider aircraft design method based on osculating cone theory | |
| CN110160734A (en) | Wind tunnel nozzle, active noise reducing device and method based on porous media | |
| Zhang et al. | A Karman-Vortex Generator for passive separation control in a conical diffuser | |
| Lysenko et al. | Stability of supersonic boundary layer under the influence of heavy gas injection: experimental study | |
| Chauhan et al. | Aspect ratio effect on elliptical sonic jet mixing | |
| Gounko et al. | Numerical modeling of the conditions for realization of flow regimes in supersonic axisymmetric conical inlets of internal compression | |
| Zapryagaev et al. | Flow structure at the initial section of a supersonic jet exhausting from a nozzle with chevrons | |
| Frolov et al. | Reducing cylinder drag by adding a plate | |
| CN109815549A (en) | A kind of design method of single pair hypersonic flow to vortex generating device | |
| Levensteins et al. | Aerodynamic characteristics of hypersonic wakes. | |
| Rufer et al. | Hot-Wire Measurements of Instabilty Waves on Cones at Mach 6 | |
| Smith | An investigation of supersonic swirling jets | |
| Wang et al. | Pressure distribution measurements in scramjet isolators under asymmetric supersonic flow | |
| Zapryagaev et al. | Structure of supersonic jets with vortex generators at the nozzle exit. |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |