CN103500265A - Method for confirming wind tunnel shrink section curve - Google Patents

Method for confirming wind tunnel shrink section curve Download PDF

Info

Publication number
CN103500265A
CN103500265A CN201310390407.5A CN201310390407A CN103500265A CN 103500265 A CN103500265 A CN 103500265A CN 201310390407 A CN201310390407 A CN 201310390407A CN 103500265 A CN103500265 A CN 103500265A
Authority
CN
China
Prior art keywords
curve
section
contraction
wind tunnel
biquadratic
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.)
Granted
Application number
CN201310390407.5A
Other languages
Chinese (zh)
Other versions
CN103500265B (en
Inventor
黄炳修
王铁进
孙勇堂
崔春
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Gloomy Wind-Tunnel Engineering Of Beijing Space Flight Benefit Co Ltd
Original Assignee
Gloomy Wind-Tunnel Engineering Of Beijing Space Flight Benefit Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Gloomy Wind-Tunnel Engineering Of Beijing Space Flight Benefit Co Ltd filed Critical Gloomy Wind-Tunnel Engineering Of Beijing Space Flight Benefit Co Ltd
Priority to CN201310390407.5A priority Critical patent/CN103500265B/en
Publication of CN103500265A publication Critical patent/CN103500265A/en
Application granted granted Critical
Publication of CN103500265B publication Critical patent/CN103500265B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Landscapes

  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention provides a method for confirming a wind tunnel shrink section curve. According to the method, once an inlet size, an outlet size, a shrink section length and a curvature radius of a shrink section outlet are given, a cylindrical curve, a first biquadratic curve, a conic curve and a second biquadratic curve are sequentially arranged from an inlet of the shrink section, and the shrink section curve is obtained. The shrink section curve designed in the method is suitable for a subsonic speed wind tunnel and a supersonic speed wind tunnel, the whole curve curvature is completely continuous, the curvature of the inlet and the curvature of an outlet are the same as the curvature of a front element and the curvature of a rear element, and perfect connection is achieved. The front of the curve cannot shrink abruptly, an overshoot phenomenon cannot occur to the outlet, and defects of an existing shrink curve are overcome. Air flows of the outlet are evenly distributed.

Description

A kind of definite method of Wind Tunnel Contraction curve
Technical field
The present invention relates to a kind of definite method of Wind Tunnel Contraction curve, belong to the hydrodynamic force technical field.
Background technology
The effect of Wind Tunnel Contraction is evenly to accelerate air-flow, the air-flow of stable section is accelerated to the flow velocity that the subsonic wind tunnel test section needs, or in super/hypersonic wind tunnel, air-flow is accelerated to the velocity of sound.In the forties in last century, people are just studied the Wind Tunnel Contraction Curve Design, and obtain the algorithm of multiple contraction section curve.The common ground of these algorithms is a given axial velocity profile, according to the fundamental equation of ideal flow, calculates whole flow field, then in this flow field, selects a streamline that meets the shrinkage ratio requirement as contraction section.Even some method has adopted the conformal projection of function of a complex variable to obtain.Above these algorithm very complexes, be not easy to the utilization on engineering.For simplifying, calculate, the formula obtained of during design, theory being derived under specific circumstances is directly used in design.In the contraction section curve, curve commonly used has hot this base curves in Vito, Vito Xin Siji to move axial curve, bicubic curve, cubic curve and quintic curve at present.
Now, in contraction section curve commonly used, all there are certain shortcoming or deficiency.Hot this base curves in Vito forwardly shrinks very steep, and approximate straight at back segment.Air-flow shrinks suddenly like this, can produce adverse pressure gradient, is unfavorable for obtaining uniform air-flow.Vito Xin Siji moves axial curve and to a certain degree is being eased, but addresses this problem on not having fully.Bicubic curve and quintic curve import are shunk smoother, and velocity of discharge has overshoot phenomenon.The entrance of cubic curve can not with the stable section smooth connection, the first order derivative of junction is discontinuous, can cause burbling and affect flow field quality.In super/hypersonic wind tunnel, the radius-of-curvature of existing contraction section curve outlet and the radius-of-curvature of supersonic speed expansion segment curve are unequal, and the contraction section outlet can not be smoothly transitted into the supersonic speed section, affects the flow field quality of whole wind-tunnel.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, a kind of definite method of wind-tunnel shrinkage curve is provided, the contraction section curve that overcomes prior art forwardly or rear portion shrink very steep, entrance can not with the radius-of-curvature of stable section smooth connection and outlet and the unequal problem of radius-of-curvature of supersonic speed expansion segment curve, obtain the contraction section curve by cylindrical section curve, article one biquadratic curve, conical section curve and second biquadratic curve are set.
Technical solution of the present invention:
A kind of definite method of Wind Tunnel Contraction curve, comprise the steps:
(1) the Wind Tunnel Contraction appearance curve being divided into to four parts, is respectively cylindrical section curve, article one biquadratic curve, conical section curve and second biquadratic curve;
(2) set up two-dimensional coordinate system, the line of Wind Tunnel Contraction entrance and exit central point of take is the x axle, the positive dirction that the direction of contraction section outlet is the x axle, and take the contraction section entrance is the y axle perpendicular to the straight line of x axle, the contraction section entrance is positioned on the positive axis of y axle, and the intersection point of x axle and y axle is initial point O;
(3) calculate the intermediate variable value, comprise the ordinate value R of intersection point of length d, second biquadratic curve and the conical section of second biquadratic curve +, second biquadratic curve and conical section the horizontal ordinate x of intersection point +, the length b of article one biquadratic curve and the length c of conical section;
(4) determine cylindrical section curve y 1(x)=R 1, 0≤x≤a;
(5) determine article one biquadratic curve y 2 ( x ) = R 1 - b tan θ 2 ( x - a b ) 3 ( 2 - x - a b ) , a≤x≤b；
(6) determine the conical section curve y 3 ( x ) = R 1 + ( a + b 2 ) tan θ - x tan θ , a+b≤x≤a+b+c；
(7) determine the second biquadratic curve y 4 ( x ) = ( L - x ) 2 12 R * [ 6 - ( L - x d ) 2 ] + R 2 , a+b+c≤x≤L；
(8) determine described Wind Tunnel Contraction curve according to step (4)-step (7), soon cylindrical section curve, article one biquadratic curve, conical section curve are connected successively with the second biquadratic curve, obtain described Wind Tunnel Contraction curve.
Calculating the intermediate variable value in described step (3) is specially:
(2.1) pass through formula calculate the length d of second biquadratic curve, wherein, R *for contraction section outlet radius-of-curvature, θ is angle of throat;
(2.2) pass through formula
Figure BDA0000374963450000025
calculate the ordinate value R of second biquadratic curve and conical section intersection point +;
(2.3) by formula x +=L-d calculates the horizontal ordinate x of the intersection point of second biquadratic curve and conical section +, L is the contraction section total length;
(2.4) pass through formula
Figure BDA0000374963450000026
calculate the length b of article one biquadratic curve, wherein a is cylindrical section length, a=0～0.1 * L, R 1for contraction section entrance section radius;
(2.5) pass through formula calculate the length c of conical section, wherein, intermediate variable
Figure BDA0000374963450000028
When described Wind Tunnel Contraction is the subsonic wind tunnel contraction section, the outlet radius of curvature R *for contraction section outlet radius R 26～10 times; When described Wind Tunnel Contraction is supersonic wind tunnel, the outlet radius of curvature R *value is the radius-of-curvature of supersonic wind tunnel expansion segment at wind-tunnel venturi place.
Described angle of throat θ gets 15 °～35 °.
The present invention's beneficial effect compared with prior art is:
Definite method of a kind of Wind Tunnel Contraction curve provided by the invention, the radius-of-curvature of given contraction section entrance size, outlet size, contraction section length and contraction section outlet, can be from the contraction section entrance, set gradually the mode of cylinder curve, article one biquadratic curve, conic section, second biquadratic curve, obtain the curve of contraction section.Contraction section curve according to the inventive method design, be applicable to subsonic wind tunnel, supersonic wind tunnel, and whole curvature of curve is fully continuous, and the curvature at entrance and exit place is consistent with the curvature of front and back parts, realizes perfect the connection.The curve front portion can not shunk very steep, and outlet does not also produce overshoot phenomenon, can overcome the deficiency of existing contraction section curve.Exit flow is uniformly distributed.
The accompanying drawing explanation
Fig. 1 is contraction section curve synoptic diagram of the present invention;
Fig. 2 is contraction section curve schematic diagram of the present invention;
Fig. 3 is the inventive method process flow diagram.
Embodiment
The inventive method is obtained the contraction section curve by cylindrical section curve, article one biquadratic curve, conical section curve and second biquadratic curve mode are set.
A kind of definite method of Wind Tunnel Contraction curve, as shown in Figure 3, comprise the steps:
(1) the Wind Tunnel Contraction appearance curve is divided into to four parts, respectively cylindrical section curve, article one biquadratic curve, conical section curve and second biquadratic curve, as shown in Figure 1, in figure, 1 means cylindrical section, 2 mean article one biquadratic curve section, 3 mean conical section, and 4 mean second biquadratic curve section, and 5 mean the contraction section outlet.
(2) as shown in Figure 2, set up coordinate system, the line of contraction section entrance and exit central point of take is the x axle, the positive dirction that the direction of contraction section outlet is the x axle, the contraction section entrance A of take is the y axle perpendicular to the straight line of x axle, entrance A is positioned on the positive axis of y axle, the intersection point of x axle and y axle is initial point O
(3) calculate the intermediate variable value, be specially:
(3.1) pass through formula calculate the length d of second biquadratic curve, wherein, R *for contraction section outlet radius-of-curvature, during design subsonic wind tunnel contraction section, R *for contraction section outlet radius R 26～10 times, design is super/during the hypersonic wind tunnel contraction section, R *value is the radius-of-curvature of supersonic speed expansion segment at the venturi place.θ is angle of throat, gets 15 °～35 °;
(3.2) pass through formula
Figure BDA0000374963450000041
calculate the intersection point of second biquadratic curve and conical section+ordinate value R +;
(3.3) by formula x +=L-d calculates+horizontal ordinate x +;
(3.4) pass through formula
Figure BDA0000374963450000042
calculate the length b of article one biquadratic curve, wherein a is cylindrical section length, can suitably regulate and choose according to reality, and a=0～0.1L, L is the contraction section total length;
(3.5) pass through formula calculate the length c of conical section, intermediate variable
Figure BDA0000374963450000044
(4) determine the cylindrical section curvilinear coordinates, when 0≤x≤a, by formula y 1(x)=R 1calculate cylindrical section curvilinear coordinates y (x);
(5) determine article one biquadratic curve coordinate,, when a≤x≤b, pass through formula y 2 ( x ) = R 1 - b tan θ 2 ( x - a b ) 3 ( 2 - x - a b ) Calculate article one biquadratic curve coordinate y (x);
(6) determine to determine the conical section curvilinear coordinates,, when a+b≤x≤a+b+c, pass through formula y 3 ( x ) = R 1 + ( a + b 2 ) tan θ - x tan θ Calculate conical section curvilinear coordinates y (x);
(6) determine second biquadratic curve coordinate,, when a+b+c≤x≤L, pass through formula y 4 ( x ) = ( L - x ) 2 12 R * [ 6 - ( L - x d ) 2 ] + R 2 Calculate second biquadratic curve coordinate y (x):
(7) determine described Wind Tunnel Contraction curve according to step (3)-step (6), soon cylindrical section curve, article one biquadratic curve, conical section curve are connected successively with the second biquadratic curve, obtain described Wind Tunnel Contraction curve, how to design the contraction section appearance curve while designing for wind-tunnel foundation and method are provided.

Claims (4)

1. definite method of a Wind Tunnel Contraction curve, is characterized in that: comprise the steps:
(1) the Wind Tunnel Contraction appearance curve being divided into to four parts, is respectively cylindrical section curve, article one biquadratic curve, conical section curve and second biquadratic curve;
(2) set up two-dimensional coordinate system, the line of Wind Tunnel Contraction entrance and exit central point of take is the x axle, the positive dirction that the direction of contraction section outlet is the x axle, and take the contraction section entrance is the y axle perpendicular to the straight line of x axle, the contraction section entrance is positioned on the positive axis of y axle, and the intersection point of x axle and y axle is initial point O;
(3) calculate the intermediate variable value, comprise the ordinate value R of intersection point of length d, second biquadratic curve and the conical section of second biquadratic curve +, second biquadratic curve and conical section the horizontal ordinate x of intersection point +, the length b of article one biquadratic curve and the length c of conical section;
(4) determine cylindrical section curve y 1(x)=R 1, 0≤x≤a;
(5) determine article one biquadratic curve y 2 ( x ) = R 1 - b tan θ 2 ( x - a b ) 3 ( 2 - x - a b ) , a≤x≤b；
(6) determine the conical section curve y 3 ( x ) = R 1 + ( a + b 2 ) tan θ - x tan θ , a+b≤x≤a+b+c；
(7) determine the second biquadratic curve y 4 ( x ) = ( L - x ) 2 12 R * [ 6 - ( L - x d ) 2 ] + R 2 , a+b+c≤x≤L；
(8) determine described Wind Tunnel Contraction curve according to step (4)-step (7), soon cylindrical section curve, article one biquadratic curve, conical section curve are connected successively with the second biquadratic curve, obtain described Wind Tunnel Contraction curve.
2. definite method of a kind of Wind Tunnel Contraction curve according to claim 1 is characterized in that: calculate the intermediate variable value in described step (3) and be specially:
(2.1) pass through formula
Figure FDA0000374963440000014
calculate the length d of second biquadratic curve, wherein, R *for contraction section outlet radius-of-curvature, θ is angle of throat;
(2.2) pass through formula
Figure FDA0000374963440000015
calculate the ordinate value R of second biquadratic curve and conical section intersection point +;
(2.3) by formula x +=L-d calculates the horizontal ordinate x of the intersection point of second biquadratic curve and conical section +, L is the contraction section total length;
(2.4) pass through formula
Figure FDA0000374963440000021
calculate the length b of article one biquadratic curve, wherein a is cylindrical section length, a=0～0.1 * L, R 1for contraction section entrance section radius;
(2.5) pass through formula
Figure FDA0000374963440000022
calculate the length c of conical section, wherein, intermediate variable
3. definite method of a kind of Wind Tunnel Contraction curve according to claim 2, is characterized in that: when described Wind Tunnel Contraction is the subsonic wind tunnel contraction section, export radius of curvature R *for contraction section outlet radius R 26～10 times; When described Wind Tunnel Contraction is supersonic wind tunnel, the outlet radius of curvature R *value is the radius-of-curvature of supersonic wind tunnel expansion segment at wind-tunnel venturi place.
4. definite method of a kind of Wind Tunnel Contraction curve according to claim 2, it is characterized in that: described angle of throat θ gets 15 °～35 °.
CN201310390407.5A 2013-08-30 2013-08-30 A kind of definite method of Wind Tunnel Contraction curve Expired - Fee Related CN103500265B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201310390407.5A CN103500265B (en) 2013-08-30 2013-08-30 A kind of definite method of Wind Tunnel Contraction curve

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201310390407.5A CN103500265B (en) 2013-08-30 2013-08-30 A kind of definite method of Wind Tunnel Contraction curve

Publications (2)

Publication Number Publication Date
CN103500265A true CN103500265A (en) 2014-01-08
CN103500265B CN103500265B (en) 2016-05-11

Family

ID=49865473

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201310390407.5A Expired - Fee Related CN103500265B (en) 2013-08-30 2013-08-30 A kind of definite method of Wind Tunnel Contraction curve

Country Status (1)

Country Link
CN (1) CN103500265B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104359647A (en) * 2014-10-17 2015-02-18 北京航天益森风洞工程技术有限公司 Method for determining profile of conical nozzle of hypersonic-velocity low-density wind tunnel
CN108363888A (en) * 2018-03-11 2018-08-03 广州富森环保科技股份有限公司 A kind of runner shrinkage curve design method
CN108534982A (en) * 2018-04-11 2018-09-14 西南交通大学 A kind of easement curve for mountain area simulation of wind
CN113536702A (en) * 2021-06-04 2021-10-22 中国人民解放军海军工程大学 Design method for wind tunnel contraction section with circular section torque-shaped section
CN113742821A (en) * 2021-08-23 2021-12-03 同济大学 Design method of wind tunnel contraction section capable of being contracted repeatedly
CN116933694A (en) * 2023-09-15 2023-10-24 中国空气动力研究与发展中心设备设计与测试技术研究所 Wind tunnel contraction section curve optimization design method based on flow separation prediction

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH10311774A (en) * 1997-05-12 1998-11-24 Mitsubishi Heavy Ind Ltd Apparatus for circuration flow
CN102023077A (en) * 2010-11-18 2011-04-20 中国人民解放军国防科学技术大学 Supersonic velocity axisymmetrical boundary layer wind tunnel
CN202614495U (en) * 2012-03-19 2012-12-19 西北工业大学 Three-coordinate movable testing device for wind tunnel

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH10311774A (en) * 1997-05-12 1998-11-24 Mitsubishi Heavy Ind Ltd Apparatus for circuration flow
CN102023077A (en) * 2010-11-18 2011-04-20 中国人民解放军国防科学技术大学 Supersonic velocity axisymmetrical boundary layer wind tunnel
CN202614495U (en) * 2012-03-19 2012-12-19 西北工业大学 Three-coordinate movable testing device for wind tunnel

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
张连河，等.: "三元收缩段优化设计研究", 《空气动力学学报》, vol. 21, no. 4, 31 December 2003 (2003-12-31), pages 417 - 423 *
王帅，等.: "直流式低速风洞收缩段收缩曲线的仿真分析", 《机床与液压》, vol. 40, no. 11, 30 June 2012 (2012-06-30), pages 100 - 104 *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104359647A (en) * 2014-10-17 2015-02-18 北京航天益森风洞工程技术有限公司 Method for determining profile of conical nozzle of hypersonic-velocity low-density wind tunnel
CN108363888A (en) * 2018-03-11 2018-08-03 广州富森环保科技股份有限公司 A kind of runner shrinkage curve design method
CN108363888B (en) * 2018-03-11 2022-03-08 广州富森环保科技股份有限公司 Method for designing flow channel contraction curve
CN108534982A (en) * 2018-04-11 2018-09-14 西南交通大学 A kind of easement curve for mountain area simulation of wind
CN113536702A (en) * 2021-06-04 2021-10-22 中国人民解放军海军工程大学 Design method for wind tunnel contraction section with circular section torque-shaped section
CN113536702B (en) * 2021-06-04 2022-07-22 中国人民解放军海军工程大学 Design method for wind tunnel contraction section with circular section torque-shaped section
CN113742821A (en) * 2021-08-23 2021-12-03 同济大学 Design method of wind tunnel contraction section capable of being contracted repeatedly
CN113742821B (en) * 2021-08-23 2024-04-26 同济大学 Design method of wind tunnel shrinkage section capable of shrinking repeatedly
CN116933694A (en) * 2023-09-15 2023-10-24 中国空气动力研究与发展中心设备设计与测试技术研究所 Wind tunnel contraction section curve optimization design method based on flow separation prediction
CN116933694B (en) * 2023-09-15 2023-12-19 中国空气动力研究与发展中心设备设计与测试技术研究所 Wind tunnel contraction section curve optimization design method based on flow separation prediction

Also Published As

Publication number Publication date
CN103500265B (en) 2016-05-11

Similar Documents

Publication Publication Date Title
CN103500265A (en) Method for confirming wind tunnel shrink section curve
CN104359647B (en) The method determining the conical nozzle molded line of hypersonic low density wind tunnel
CN102607799B (en) Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method
CN108846224A (en) Supersonic flow channel design method and device
CN108195544B (en) A kind of impulse type wind-tunnel tandem jet pipe
CN203616135U (en) Jet nozzle
CN102218378B (en) Ultrasonic nonuniform flow nozzle and design method thereof
CN105138787B (en) The supersonic flow field design method of feature based line tracking
CN103698100B (en) Supersonic wind tunnel and definite method thereof
CN107672821B (en) Variable Mach number parallel wide-speed-range waverider aircraft design method based on osculating cone theory
CN106005475A (en) Design method for hypersonic speed inner and outer flow integrated full wave rider flight vehicle
CN109927917A (en) Integrated design method for internal rotation type wave-rider forebody air inlet channel of supersonic aircraft
CN105329462A (en) Changeable wall surface pressure distribution rule-based osculating flow field ride precursor design method
CN108345714B (en) Numerical simulation method for parameter design of inner annular jet flow pressure stabilizing cavity
CN108182319A (en) A kind of supersonic speed integration Nozzle Design method
CN108100291A (en) Osculating waverider design method for given three-dimensional leading edge line
CN111553976B (en) Design method of three-dimensional inward rotation air inlet channel with controllable shock wave and pressure distribution
CN102054099A (en) Method and device for designing three-dimensional closed guide blade with tubular type conical space
CN110414168A (en) Hypersonic velocity isolation section design method and system based on coupling optimization with front fuselage
CN106089806A (en) A kind of diffuser that reduces separates the end wall processing method of loss
CN103926050A (en) Hypersonic speed silencing spray pipe and determining method thereof
CN105539863B (en) Hypersonic aircraft precursor, air intake duct and support plate integrated pneumatic layout method
CN108876911B (en) Calculation method and device for three-dimensional flow field of supersonic flow channel
Zhang Research progress of hypersonic inlet inverse design based on curved shock compression system
CN107016199A (en) It is a kind of that the design method for moving bulge is arranged without shock-boundary

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
CF01 Termination of patent right due to non-payment of annual fee
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20160511

Termination date: 20190830