CN105181289A - Fairing for empennage wind tunnel testing - Google Patents
Fairing for empennage wind tunnel testing Download PDFInfo
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- CN105181289A CN105181289A CN201510586919.8A CN201510586919A CN105181289A CN 105181289 A CN105181289 A CN 105181289A CN 201510586919 A CN201510586919 A CN 201510586919A CN 105181289 A CN105181289 A CN 105181289A
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Abstract
The invention discloses a fairing for empennage wind tunnel testing. The fairing is divided into three segments: a front segment, a middle segment, and a rear segment. The middle segment is divided into an A part, a B part, and a C part; the projection of the root chord length of the model at an X shaft is used as a reference length being B; the length of the A is 1.0 to 1.4% of that of the B; and the length of the C is 2.16 to 2.56% of that of the B. The rear segment uses an ending point of the C segment as an original point and an XOY coordinate shaft is established; anti-clockwise rotation is used as the positive one; a straight line is made, wherein an included angel theta 1 is formed between the straight line and an X shaft; a length R1 is cut from the straight line and a D1 point is obtained; projection X1 of the D1 point on the X shaft is obtained; a straight line with an angle theta 2 is made by using the X1 as an original center; a length R2 is cut from the straight line and a D2 point is obtained; and then all points are obtained successively. And then all points are connected smoothly, thereby obtaining a fairing appearance meeting the requirement.
Description
Technical field
The present invention relates to a kind of radome fairing, particularly relate to a kind of radome fairing being applicable to empennage wind tunnel test.
Background technology
Radome fairing is aircraft components model when carrying out wind tunnel test, the device designed for the protection of measuring and controlling equipment circuit.The configuration design of conventional rectifier cover is comparatively random, only simply processes a fluidics profile to reach the object of rectification.But for the aerodynamics state of not only moving but also changing, often occur a lot of wild effect, make test findings inaccurate, serious meeting causes test failure.
Summary of the invention
The object of the present invention is to provide a kind of radome fairing being applicable to empennage wind tunnel test, for the wind tunnel test of empennage model, compared with conventional rectifier cover, decrease the interference of radome fairing to test figure, improve the confidence level of test figure.
The present invention adopts following technical proposals to realize: this radome fairing is divided into three sections: leading portion, stage casing, back segment.Leading portion needs to reduce flow field as far as possible and changes, and ensures that model is within controlled flow field; Stage casing is model support section, and can place premised on testing apparatus etc., length and model root string keep certain proportion can effective steady flow condition; Back segment is constriction, and excessive shrinkage factor can impact in flow field model, and too small shrinkage factor can cause test model to exceed test section effective length.
The stage casing of radome fairing of the present invention is divided into ABC tri-part, be projected in X-axis for datum length, i.e. B, and the length that the length of A is 1.0 ~ 1.4% of B, C is 2.16 ~ 2.56% of B with model root chord length;
The back segment of radome fairing of the present invention, with the end point O of C section for initial point, build an XOY coordinate axis, rotate counterclockwise as just, make an angle becomes θ 1 straight line with X-axis, intercepted length R1 on straight line, obtains D1 point, makes the projection X1 of D1 point in X-axis, be the straight line that the former heart does that an angle is θ 2 with X1, intercepted length R2 on straight line, obtains D2 point, arrives D6 successively; By round and smooth for each point connection, the rectification profile of requirement can be met.
Wherein, the value of R, θ can obtain by following experimental formula:
(0<n≤5)
The leading portion of radome fairing of the present invention is based on back segment rectification profile, and X value reduces by the multiplying power of 1.1 ~ 1.3, and Y value is constant.
Conventional rectifier cover, although have low-profile, save the advantages such as processing materials, but being through CFD calculates rear known, because radome fairing contraction is too urgent, produces rarefaction wave and beats on model, strongly have impact on experimental flow field, radome fairing of the present invention carries out CFD calculating, and result shows, the impact cancellation of rarefaction wave.Radome fairing of the present invention decreases the interference of radome fairing profile to test figure, improves the confidence level of test figure.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present invention.
Fig. 2 is radome fairing stage casing of the present invention schematic diagram.
Fig. 3 is radome fairing back segment schematic diagram of the present invention.
Fig. 4 is the CFD calculating chart of conventional rectifier cover.
Fig. 5 is the CFD calculating chart of radome fairing of the present invention.
Embodiment
embodiment 1
As shown in Figure 1, this radome fairing is divided into three sections: leading portion, stage casing, back segment.
As shown in Figure 2, stage casing is also divided into ABC tri-part in stage casing, and be projected in X-axis for datum length with model root chord length, i.e. B, and the length that the length of A is 1.2% of B, C is 2.36% of B, such stage casing just completes;
Back segment as shown in Figure 3, with the end point O of C section for initial point, build an XOY coordinate axis, rotate counterclockwise as just, make an angle becomes θ 1 straight line with X-axis, intercepted length R1 on straight line, obtains D1 point, makes the projection X1 of D1 point in X-axis, be the straight line that the former heart does that an angle is θ 2 with X1, intercepted length R2 on straight line, obtains D2 point, arrives D6 successively; By round and smooth for each point connection, the rectification profile of requirement can be met.
Wherein, the value of R, θ can obtain by following experimental formula:
(0<n≤5)
Leading portion is based on back segment rectification profile, and X value reduces by the multiplying power of 1.1, and Y value is constant.
Conventional rectifier cover, although have low-profile, saves the advantages such as processing materials, but be through CFD calculate after, result as shown in Figure 4, as seen from the figure, because radome fairing contraction is too urgent, produce rarefaction wave and beat on model, strongly have impact on experimental flow field, radome fairing of the present invention carries out CFD calculating, result as shown in Figure 5, the impact cancellation of rarefaction wave, decreases the interference of radome fairing profile to test figure, improves the confidence level of test figure.
embodiment 2
This radome fairing is divided into three sections: leading portion, stage casing, back segment.Stage casing is also divided into ABC tri-part, and be projected in X-axis for datum length with model root chord length, i.e. B, and the length that the length of A is 1.0% of B, C is 2.16% of B, such stage casing just completes;
Back segment with the end point O of C section for initial point, build an XOY coordinate axis, rotate counterclockwise as just, make an angle becomes θ 1 straight line with X-axis, intercepted length R1 on straight line, obtain D1 point, making the projection X1 of D1 point in X-axis, is the straight line that the former heart does that an angle is θ 2 with X1, intercepted length R2 on straight line, obtain D2 point, arrive D6 successively; By round and smooth for each point connection, the rectification profile of requirement can be met.
Wherein, the value of R, θ can obtain by following experimental formula:
(0<n≤5)
Leading portion is based on back segment rectification profile, and X value reduces by the multiplying power of 1.2, and Y value is constant.
embodiment 3
This radome fairing is divided into three sections: leading portion, stage casing, back segment.Stage casing is also divided into ABC tri-part, and be projected in X-axis for datum length with model root chord length, i.e. B, and the length that the length of A is 1.4% of B, C is 2.56% of B, such stage casing just completes;
Back segment with the end point O of C section for initial point, build an XOY coordinate axis, rotate counterclockwise as just, make an angle becomes θ 1 straight line with X-axis, intercepted length R1 on straight line, obtain D1 point, making the projection X1 of D1 point in X-axis, is the straight line that the former heart does that an angle is θ 2 with X1, intercepted length R2 on straight line, obtain D2 point, arrive D6 successively; By round and smooth for each point connection, the rectification profile of requirement can be met.
Wherein, the value of R, θ can obtain by following experimental formula:
(0<n≤5)
Leading portion is based on back segment rectification profile, and X value reduces by the multiplying power of 1.3, and Y value is constant.
Claims (4)
1. one kind is applicable to the radome fairing of empennage wind tunnel test, this radome fairing is divided into three sections: leading portion, stage casing, back segment, it is characterized in that: stage casing is divided into ABC tri-part, X-axis is projected in for datum length with model root chord length, i.e. B, and the length that the length of A is 1.0 ~ 1.4% of B, C is 2.16 ~ 2.56% of B;
Back segment, with the end point O of C section for initial point, build an XOY coordinate axis, rotate counterclockwise as just, make an angle becomes θ 1 straight line with X-axis, intercepted length R1 on straight line, obtains D1 point, makes the projection X1 of D1 point in X-axis, be the straight line that the former heart does that an angle is θ 2 with X1, intercepted length R2 on straight line, obtains D2 point, arrives Dn successively; By round and smooth for each point connection, the rectification profile of requirement can be met.
2. radome fairing according to claim 1, is characterized in that, the value of R, θ can obtain by following experimental formula:
(0<n≤5)。
3. radome fairing according to claim 1, is characterized in that, leading portion is based on back segment rectification profile, and X value reduces by the multiplying power of 1.1 ~ 1.3, and Y value is constant.
4. radome fairing according to claim 1, is characterized in that, the length of A is the length of 1.2%, C of B is 2.36% of B.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510586919.8A CN105181289A (en) | 2015-09-14 | 2015-09-14 | Fairing for empennage wind tunnel testing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510586919.8A CN105181289A (en) | 2015-09-14 | 2015-09-14 | Fairing for empennage wind tunnel testing |
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| CN105181289A true CN105181289A (en) | 2015-12-23 |
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| CN201510586919.8A Pending CN105181289A (en) | 2015-09-14 | 2015-09-14 | Fairing for empennage wind tunnel testing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110160738A (en) * | 2019-03-21 | 2019-08-23 | 北京机电工程研究所 | For the fairing of aerofoil wind tunnel test, design method and blended wing-body device |
| CN110844116A (en) * | 2019-10-18 | 2020-02-28 | 中国直升机设计研究所 | Parameter-adjustable vortex generator |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006208395A (en) * | 2006-03-22 | 2006-08-10 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel testing method |
| CN101398343A (en) * | 2007-09-26 | 2009-04-01 | 北京师范大学 | Wind-tunnel modelling device for sandstorm entironment and engineering |
| RU2381472C1 (en) * | 2008-08-01 | 2010-02-10 | Российская Федерация, от имени которой выступает государственный заказчик Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Method for testing of pulsating detonating engine and aerodynamic installation for its realisation |
| CN102642614A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Self-adaptive adjustable low-resistance fairing |
| CN202501972U (en) * | 2012-04-05 | 2012-10-24 | 黄帅文 | Airplane model force-measuring wind tunnel |
| CN202533242U (en) * | 2012-02-21 | 2012-11-14 | 南开大学 | Multifunctional movable type wind erosion wind tunnel |
| CN202853875U (en) * | 2012-09-24 | 2013-04-03 | 西北工业大学 | Reusable aircraft model experimental device capable of changing shape and parameters |
| CN103895868A (en) * | 2012-12-27 | 2014-07-02 | 空中客车西班牙运营有限责任公司 | Aircraft ventral fairing with an improved storage capacity |
| CN203780795U (en) * | 2014-04-18 | 2014-08-20 | 江西洪都航空工业集团有限责任公司 | Aft body blowing type rectifying device of airplane with double engines and single vertical fin |
-
2015
- 2015-09-14 CN CN201510586919.8A patent/CN105181289A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006208395A (en) * | 2006-03-22 | 2006-08-10 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel testing method |
| CN101398343A (en) * | 2007-09-26 | 2009-04-01 | 北京师范大学 | Wind-tunnel modelling device for sandstorm entironment and engineering |
| RU2381472C1 (en) * | 2008-08-01 | 2010-02-10 | Российская Федерация, от имени которой выступает государственный заказчик Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Method for testing of pulsating detonating engine and aerodynamic installation for its realisation |
| CN202533242U (en) * | 2012-02-21 | 2012-11-14 | 南开大学 | Multifunctional movable type wind erosion wind tunnel |
| CN202501972U (en) * | 2012-04-05 | 2012-10-24 | 黄帅文 | Airplane model force-measuring wind tunnel |
| CN102642614A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Self-adaptive adjustable low-resistance fairing |
| CN202853875U (en) * | 2012-09-24 | 2013-04-03 | 西北工业大学 | Reusable aircraft model experimental device capable of changing shape and parameters |
| CN103895868A (en) * | 2012-12-27 | 2014-07-02 | 空中客车西班牙运营有限责任公司 | Aircraft ventral fairing with an improved storage capacity |
| CN203780795U (en) * | 2014-04-18 | 2014-08-20 | 江西洪都航空工业集团有限责任公司 | Aft body blowing type rectifying device of airplane with double engines and single vertical fin |
Non-Patent Citations (2)
| Title |
|---|
| 姜振海等: ""超音速共形整流罩风洞试验及其光机特性"", 《光学 精密工程》 * |
| 魏群等: ""超音速光学导引头整流罩的形状优化"", 《光学 精密工程》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110160738A (en) * | 2019-03-21 | 2019-08-23 | 北京机电工程研究所 | For the fairing of aerofoil wind tunnel test, design method and blended wing-body device |
| CN110160738B (en) * | 2019-03-21 | 2020-10-23 | 北京机电工程研究所 | Rectifying device for wing surface wind tunnel test, design method and wing body fusion device |
| CN110844116A (en) * | 2019-10-18 | 2020-02-28 | 中国直升机设计研究所 | Parameter-adjustable vortex generator |
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