CN104108470A - Planar embedded type air inlet channel based on embedded type separation channel layout and design method - Google Patents

Planar embedded type air inlet channel based on embedded type separation channel layout and design method Download PDF

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Publication number
CN104108470A
CN104108470A CN201410315774.3A CN201410315774A CN104108470A CN 104108470 A CN104108470 A CN 104108470A CN 201410315774 A CN201410315774 A CN 201410315774A CN 104108470 A CN104108470 A CN 104108470A
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internal channel
profile
road
back segment
leading portion
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CN104108470B (en
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谢文忠
张东方
马广甫
葛严
林宇
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Abstract

The invention provides a planar embedded type air inlet channel based on embedded type separation channel layout and a design method, and belongs to the field of aerodynamic design of aircrafts. The planar embedded type air inlet channel is formed by an embedded type air inlet channel body and an embedded type air separation channel; an inlet of the embedded type air separation channel is located in the front edge of an air inlet of the embedded type air inlet channel body; the embedded type air separation channel is led to the two sides of a missile body from the front edge of the inlet, is in bilateral symmetry about the center longitudinal section of the missile body and is formed by a flow guide section, a left inner channel section and a right inner channel section. The embedded type air separation channel is formed in the position slightly close to the upstream of the embedded type air inlet channel body, when airflow flows through the embedded type air separation channel, the vast majority of boundary layer lower energy flow developed from a forebody of an aircraft is led to the two sides of the missile body through the embedded type air separation channel, accordingly, the proportion of the lower energy flow flowing into the embedded type air inlet channel is reduced, air inlet quality of the embedded type air inlet channel is improved, and aerodynamic performance of the planar embedded type air inlet channel is greatly promoted.

Description

Plane Submerged Inlet and method of designing based on flush type every road layout
Technical field
Of the present invention based on flush type plane Submerged Inlet and the method for designing every road layout, belong to aircraft pneumatic design field.
Background technology
Lock on has not only improved requirement to the technique and tactics performance of aircraft, and the penetration ability of aircraft self is also had higher requirement.At present, the radar exploration technique is one of Main Means of explorer vehicle, therefore, reduces the radar scattering area (RCS) of aircraft, reduces the probability of being found by radar, and the stealthy ability of electromagnetism that improves aircraft seems particularly important.Correlative study shows, inlet channel is one of strong radar scattering source of aircraft, and adopt Submerged Inlet can significantly reduce stealthy aircraft RCS (Li Tian etc. the preliminary guide of aircraft shape stealth design. the .1991.10 of scientific and technical research institute of the Ministry of Aero-Space Industry; Huang Xijun. the research of propulsion system stealth technology. international airline, 1987 (7), pp17-19; Shi Lei, Guo Rongwei. the Electromagnetic Scattering Characteristics of plane Submerged Inlet. aviation journal .2008,29 (5)).
Submerged Inlet is the special inlet channel that a class is different from traditional Pitot inlet, S curved intake port.Its import is imbedded among fuselage or wing conventionally, without any jut.The benefit of design is like this: can actv. reduce the wind area of aircraft, reduce frontal resistance and Radar Cross Section, have the overall pneumatic and Stealth Fighter of good aircraft, and be conducive to laying, carrying and box transmitting of aircraft.Above many advantages makes Submerged Inlet more and more receive domestic and international researcher's concern, and in some models, has obtained application, as the cruise missile AGM-129 of the U.S., harpoon etc.
Yet, because the admission port of Submerged Inlet is placed in the boundary 1ayer on fuselage/bomb body surface completely, cannot as common inlet channel, make full use of incoming flow punching press air inlet.Research shows, plane Submerged Inlet is mainly utilized front lip meiobar and import incline to entrainment whirlpool induction main flow and is entered inlet channel (remaining Anyuan, Guo Rongwei etc. the air inlet mechanism of Submerged Inlet and low speed experimental study under a kind of Stealth shape body. aerodynamic force journal, 2003,21 (2): 182-188).But, owing to there being thicker fuselage/bomb body boundary 1ayer (Sun S before Submerged Inlet import, Guo R W.Numerical analysis and experimental validation of a submerged inlet on the plane surface.Chinese Journal of Aeronautics, 2005,18 (3): 199-205), Submerged Inlet is when induction main flow enters, also this precursor boundary 1ayer low energy stream is introduced to internal channel, brought larger air-flow pitot loss, make the degree of irregularity in flow field larger, flow field is difficult to tissue.In addition, under higher flight Mach number, air-flow will speed up hyprsonic in import leading edge part, form critical shock wave and with the fluidised form of boundary 1ayer phase mutual interference, will further worsen the aeroperformance of Submerged Inlet.
Therefore, a kind of flow field control technology that is applicable to plane Submerged Inlet is proposed, obtain a kind of high-performance plane Submerged Inlet of stable operation range broadness, there is higher learning value and important realistic meaning, for technical foundation is established in the engineering application of Submerged Inlet and even the development of advanced aircraft.
Summary of the invention
Order of the present invention is in conjunction with the plane Submerged Inlet distribution form every road with flush type, design plan and the method for designing of flush type every road profile proposed, by plane Submerged Inlet flow field, downstream is control effectively, significantly promote the aeroperformance of inlet channel, make the stealthy high fighting efficiency of this height aerodynamic arrangement reach Practical level.
Parameter annotation:
D air intake port diameter
D eair intake port equivalent diameter
δ does not offer flush type 1D before the prototype scheme middle distance plane Submerged Inlet admission port in road ethe boundary layer thickness at place
Maximum half width of L plane Submerged Inlet import
L 1flush type is every road actinal surface half width
L 2flush type is every road actinal surface reference position
L 3axial distance behind Yu Ge road, venturi lower end between lip
L 4axial distance between lip behind batten wall end Yu Ge road outside internal channel back segment
L 5axial distance between lip behind batten wall end Yu Ge road inside internal channel back segment
L 6internal channel leading portion lateral wall initiating terminal is apart from the distance of bomb body side
H 1distance between venturi lower end and bomb body lower surface
H 2every road height
H tventuri height
R actinal surface is led radius of circle
α 1actinal surface ramp angle
β 1the angle in internal channel leading portion lateral wall plane and elevation profile
β 2the end corner cut of batten wall outside internal channel back segment
β 3the angle in internal channel leading portion madial wall plane and elevation profile
β 4the end corner cut of batten wall inside internal channel back segment
Technical scheme of the present invention is as follows:
Plane Submerged Inlet and a method of designing based on flush type every road layout, the three-dimensional modeling in conjunction with flush type every road and plane Submerged Inlet layout, describes every the pneumatic profile in road and design thereof the flush type in Submerged Inlet forward position emphatically.
One kind based on flush type the plane Submerged Inlet every road layout
It is characterized in that: by Submerged Inlet and flush type, every road, formed;
Flush type is positioned at Submerged Inlet admission port forward position every the import in road, flush type leads to bomb body both sides and symmetrical about bomb body central lateral plane every road by import forward position, flush type is comprised of diversion section and left and right two internal channel sections every road, wherein diversion section is positioned at lip upstream behind road, and internal channel section is positioned at lip downstream behind road; Diversion section profile consists of upper profile and two side walls, wherein goes up the slope of profile for adopting arc-shaped transitional surface and bomb body horizontal surface to join; Behind two internal channel Duan Congge roads, left and right, lip is separately and about the symmetrical "eight" shape channel architecture that is in elevation profile.
According to claim 1 based on flush type the plane Submerged Inlet every road layout, it is characterized in that:
Above-mentioned flush type is as follows every the concrete geometric configuration in road and characterising parameter, due to symmetry, for convenience of choosing half bomb body He Bange road below describing, is described:
One, diversion section geometric configuration:
1-1, diversion section import are opened in the slightly bomb body surface of upstream of Submerged Inlet, and its geometric description parameter is actinal surface half width L 1with actinal surface reference position L 2, actinal surface reference position refers to that lip, from the axial distance of Fighter Inlet, meets L≤L behind road 1≤ 2.55L, 0.6D e≤ L 2≤ 3D e; L refers to maximum half width of plane Submerged Inlet import; D erefer to the outlet equivalent diameter of Submerged Inlet;
On 1-2, diversion section, profile geometric description parameter is actinal surface ramp angle α 1lead radius of circle R with actinal surface, meet 20 °≤α 1≤ 25 °, D e≤ R≤1.5D e; Actinal surface ramp angle refers to the angle of the straight section place slopes such as use and bomb body horizontal surface gained intersection;
Two, how much overall configurations of internal channel:
2-1, single internal channel section consist of top profile, below profile, interior sidewall surface and outer side surface, and shape of cross section is rectangle, and internal channel section is divided into internal channel leading portion and internal channel back segment with venturi cross-sectional plane;
2-2, throat design are at the intersection of internal channel leading portion and internal channel back segment, and its geometric description parameter is the axial distance L between lip behind Yu Ge road, venturi lower end 3, the distance H between venturi lower end and bomb body lower surface 1with venturi height H t, meet 0.2D e≤ L 3≤ 0.3D e, 0.12D e≤ H 1≤ 0.15D e, 0.5 δ≤H t≤ 1.5 δ; δ refers to and does not offer flush type 1D before the prototype scheme middle distance plane Submerged Inlet admission port in road ethe boundary layer thickness at place;
Three, internal channel leading portion geometric configuration:
3-1, internal channel leading portion are the passage that cross-sectional area shrinks, its internal channel leading portion top profile is the continuity profile of profile slope on diversion section, internal channel leading portion below profile is that elevation profile hatching is the batten profile of same SPL, the plane that internal channel leading portion interior sidewall surface horizontal profile is same linear portion, the plane that internal channel leading portion outer side surface horizontal profile is same linear portion;
The angle in 3-2, internal channel leading portion lateral wall plane and elevation profile is β 1, the angle in internal channel leading portion madial wall plane and elevation profile is β 3, meet 3 °≤β 1≤ 5 °, 6 °≤β 3≤ 8 °;
Four, internal channel back segment geometric configuration:
4-1, internal channel back segment top profile are that elevation profile hatching is the batten profile of same SPL, internal channel back segment below profile is that elevation profile hatching is the batten profile of same SPL, the batten profile that internal channel back segment interior sidewall surface horizontal profile is same SPL, the batten profile that internal channel back segment outer side surface horizontal profile is same SPL;
Outside 4-2, internal channel back segment, batten wall and upstream internal channel leading portion outer side surface are tangent, the end corner cut β of batten wall outside internal channel back segment 2, behind batten wall end Yu Ge road, the axial distance between lip is L outside internal channel back segment 4; Inside internal channel back segment, batten wall and upstream internal channel leading portion interior sidewall surface are tangent, the end corner cut β of batten wall inside internal channel back segment 4, behind batten wall end Yu Ge road, the axial distance between lip is L inside internal channel back segment 5.Meet 10 °≤β 2≤ 20 °, 30 °≤β 4≤ 40 °, 7L 6≤ L 4≤ 8L 6, L 4+ 1.3L 1≤ L 5≤ L 4+ 1.5L 1.L 6refer to that internal channel leading portion lateral wall initiating terminal is apart from the distance of bomb body side;
4-3, internal channel back segment export center on elevation profile from the geometric distance characterising parameter Wei Ge road height H on bomb body surface 2, meet 0.8D e≤ H 2≤ D e; The design of internal channel back segment is expansion pipeline, and its geometric description parameter is area divergence ratio A d, meet 1.1≤A d≤ 1.3; Area divergence ratio refers to the ratio of internal channel back segment outlet effective cross sectional area and venturi import effective cross sectional area.
According to claim 1 based on flush type the method for designing every the plane Submerged Inlet of road layout, it is characterized in that comprising the following steps:
Step 1, based on bomb body surface design plane Submerged Inlet prototype according to a conventional method;
Step 2, on plane Submerged Inlet prototype basis, design according to the following steps flush type every road profile;
Step 2-1, design internal channel leading portion:
Step 2-1-1, design internal channel leading portion below profile SPL: according to actinal surface reference position L 2, the axial distance L behind Yu Ge road, venturi lower end between lip 3and the distance H between venturi lower end and bomb body lower surface 1determine internal channel leading portion below profile SPL on elevation profile, guarantee that batten stops corner cut and actinal surface ramp angle α 1unanimously; 0.6D wherein e≤ L 2≤ 3D e, 0.2D e≤ L 3≤ 0.3D e, 0.12D e≤ H 1≤ 0.15D e, 20 °≤α 1≤ 25 °;
Step 2-1-2, design internal channel leading portion top profile molded line: again according to venturi height H twith actinal surface ramp angle α 1determine internal channel leading portion top profile linear portion on elevation profile; 0.5 δ≤H wherein t≤ 1.5 δ;
Step 2-1-3, design internal channel leading portion sidewall plane are at the linear portion on bomb body surface: according to actinal surface half width L 1, the axial distance L behind Yu Ge road, venturi lower end between lip 3, internal channel leading portion lateral wall plane and elevation profile angle β 1angle β with internal channel leading portion madial wall plane and elevation profile 3on bomb body surface, make by admission port forward position and lead to two, downstream linear portion; L≤L wherein 1≤ 2.55L, 0.2D e≤ L 3≤ 0.3D e, 3 °≤β 1≤ 5 °, 6 °≤β 3≤ 8 °;
Step 2-2, design diversion section:
Profile on step 2-2-1, design diversion section: extend internal channel leading portion top profile linear portion and obtain profile slope on diversion section, then it is tangent by arc transition section and bomb body surface to lead radius of circle R according to actinal surface, thereby obtain on elevation profile profile on diversion section; D wherein e≤ R≤1.5D e;
Step 2-3, design internal channel back segment:
Step 2-3-1, design internal channel back segment sidewall batten wall are at the nurbs curve on bomb body surface: tangent according to batten wall outside internal channel back segment and upstream internal channel leading portion outer side surface, and the end corner cut β of batten wall outside internal channel back segment 2, behind batten wall end Yu Ge road, the axial distance between lip is L outside internal channel back segment 4; Inside internal channel back segment, batten wall and upstream internal channel leading portion interior sidewall surface are tangent, the end corner cut β of batten wall inside internal channel back segment 4, behind batten wall end Yu Ge road, the axial distance between lip is L inside internal channel back segment 5on bomb body surface, make two nurbs curves that lead to bomb body both sides, downstream by internal channel leading portion bomb body surface linear portion; 10 °≤β wherein 2≤ 20 °, 7L 6≤ L 4≤ 8L 6, 30 °≤β 4≤ 40 °, L 4+ 1.3L 1≤ L 5≤ L 4+ 1.5L 1;
Effective import cross section of step 2-3-2 design internal channel back segment and effectively outlet, effective import cross section of internal channel back segment refers to the cross section that on sidewall batten, the tangent line of its two-end-point equates with this cross section angle excessively, effectively outlet is as the same, and center, outlet is H from the distance Ji Ge road height of bomb body place plane 2, meet 0.8D e≤ H 2≤ D e;
Step 2-3-3 internal channel back segment is designed to expand pipeline, and its geometric description parameter is area divergence ratio A d, the ratio of effective discharge area and venturi import effective cross sectional area, meets 1.1≤A d≤ 1.3.
Principle of work of the present invention is, due to Submerged Inlet slightly upstream position offer flush type every road, this flush type of airflow passes is when road, the boundary 1ayer low energy stream overwhelming majority developing from aircraft precursor is embedded in guiding bomb body both sides, Shi Ge road, thereby reduced and entered low energy in Submerged Inlet air-flow and flow shared ratio, improved the air inlet quality of Submerged Inlet, the aeroperformance of plane Submerged Inlet is increased dramatically.
Accompanying drawing explanation
Fig. 1-1st, the three-dimensional modeling band of full bomb body such as plays up at the axle diagram;
Fig. 1-2 is the axle diagrams such as three-dimensional modeling of full bomb body;
Fig. 2-1st, the band of full bomb body is played up lateral plan;
Fig. 2-2nd, the lateral plan of full bomb body;
Fig. 3-1st, the band of full bomb body is played up upward view;
Fig. 3-2nd, the upward view of full bomb body;
Fig. 4-1st, the band of full bomb body is played up front elevation;
Fig. 4-2nd, the front elevation of full bomb body;
Fig. 5-1 is that the three-dimensional modeling band of half bomb body such as plays up at the axle diagram;
Fig. 5-2 are axle diagrams such as three-dimensional modeling of half bomb body;
Fig. 6-1 is that the band of half bomb body is played up lateral plan;
Fig. 6-2 are lateral plans of half bomb body;
Fig. 7-1 is that the band of half bomb body is played up upward view;
Fig. 7-2 are upward views of half bomb body;
Fig. 8-1 is that the band of half bomb body is played up front elevation;
Fig. 8-2 are front elevations of half bomb body;
Fig. 9 is near flush type profile partial enlarged view road;
Figure 10 is that flush type is every road geometric parameter mark figure (with Fig. 9 opposite direction).
Figure 11 is that flush type is every road actinal surface geometric parameter mark figure;
Figure 12 is that flush type is every road nurbs curve geometric parameter mark figure;
Figure 13 is plane Submerged Inlet three-dimensional modeling figure;
The streamline distribution that Figure 14 Shi Ge road import the place ahead height H=0.5 δ sends and along journey total pressure recovery coefficient distribution graph;
Number in the figure title: 1. bomb body, 2. flush type is every road, 3. plane Submerged Inlet, 4.Ge road diversion section, profile on 5.Ge road diversion section, 6.Ge road internal channel leading portion, 7.Ge road internal channel back segment, 8. internal channel back segment import free area, 9. internal channel back segment outlet free area, lip behind 10.Ge road, 11. internal channel leading portion top profiles, 12. internal channel leading portion below profiles, 13.Ge road venturi, α 1. actinal surface ramp angle, β 1. angle, the β in internal channel leading portion lateral wall plane and elevation profile 2. end corner cut, the β of batten wall outside internal channel back segment 3. angle, the β in internal channel leading portion madial wall plane and elevation profile 4. the end corner cut of batten wall inside internal channel back segment, H t. venturi height, maximum half width of L. plane Submerged Inlet import, L 1. actinal surface half width, L 2. actinal surface reference position, L 3. the axial distance behind Yu Ge road, venturi lower end between lip, H 1. the distance between venturi lower end and bomb body lower surface, H 2. every road height, L 4. the axial distance between lip behind batten wall end Yu Ge road outside internal channel back segment, L 5. the axial distance between lip behind batten wall end Yu Ge road inside internal channel back segment, L 6. internal channel leading portion lateral wall initiating terminal is apart from the distance of bomb body side.
The specific embodiment
Plane Submerged Inlet and a method of designing based on flush type every road 2 layouts, in conjunction with integral layout three-dimensional modeling Fig. 9, describe every road 2 profiles and design thereof inlet channel forward position flush type emphatically.
One kind based on flush type the plane Submerged Inlet 3 every road 2 layouts
It is characterized in that: by Submerged Inlet 3 and flush type, every road 2, formed;
Flush type is positioned at Submerged Inlet 3 admission port forward positions every the import in road 2, flush type leads to bomb body both sides and symmetrical about bomb body central lateral plane every road 2 by import forward position, flush type is comprised of diversion section 4 and left and right two internal channel sections every road 2, wherein diversion section 4 is positioned at lip 10 upstreams behind road, and internal channel section is positioned at lip 10 downstreams behind road; Diversion section 4 profiles consist of upper profile 5 and two side walls, wherein go up the slope of profile for adopting arc-shaped transitional surface and bomb body horizontal surface 1 to join; Behind two internal channel Duan Congge roads, left and right, lip 10 is separately and about the symmetrical "eight" shape channel architecture that is in elevation profile.
According to claim 1 based on flush type the plane Submerged Inlet 3 every road 2 layouts, it is characterized in that:
Above-mentioned flush type is as follows every the concrete geometric configuration in road 2 and characterising parameter, due to symmetry, for convenience of choosing half bomb body He Bange road below describing, is described:
One, diversion section geometric configuration:
1-1, diversion section 4 imports are opened in the slightly bomb body surface 1 of upstream of Submerged Inlet, and its geometric description parameter is actinal surface half width L 1with actinal surface reference position L 2, actinal surface reference position refers to that lip 10, from the axial distance of Fighter Inlet, meets L≤L behind road 1≤ 2.55L, 0.6D e≤ L 2≤ 3D e; L refers to maximum half width of plane Submerged Inlet import; D erefer to the outlet equivalent diameter of Submerged Inlet;
On 1-2, diversion section, profile 5 geometric description parameters are actinal surface ramp angle α 1lead radius of circle R with actinal surface, meet 20 °≤α 1≤ 25 °, D e≤ R≤1.5D e; Actinal surface ramp angle refers to the angle of the straight section place slopes such as use and bomb body horizontal surface 1 gained intersection;
Two, how much overall configurations of internal channel:
2-1, single internal channel section consist of top profile, below profile, interior sidewall surface and outer side surface, and shape of cross section is rectangle, and internal channel section is divided into internal channel leading portion 6 and internal channel back segment 7 with venturi 13 cross-sectional planes;
The intersection that 2-2, venturi 13 design at internal channel leading portion 6 and internal channel back segment 7, its geometric description parameter is the axial distance L between lip 10 behind Yu Ge road, venturi lower end 3, the distance H between venturi lower end and bomb body lower surface 1 1with venturi height H t, meet 0.2D e≤ L 3≤ 0.3D e, 0.12D e≤ H 1≤ 0.15D e, 0.5 δ≤H t≤ 1.5 δ; δ refers to and does not offer flush type 1D before prototype scheme middle distance plane Submerged Inlet 3 admission ports in road ethe boundary layer thickness at place;
Three, internal channel leading portion geometric configuration:
The passage that 3-1, internal channel leading portion 6 shrink for cross-sectional area, its internal channel leading portion top profile 11 is the continuity profile of profile 5 slopes on diversion section, the batten profile that internal channel leading portion below profile 12 is same SPL for elevation profile hatching, the plane that internal channel leading portion 6 interior sidewall surface horizontal profiles are same linear portion, the plane that internal channel leading portion 6 outer side surface horizontal profiles are same linear portion;
The angle in 3-2, internal channel leading portion 6 lateral wall planes and elevation profile is β 1, the angle in internal channel leading portion 6 madial wall planes and elevation profile is β 3, meet 3 °≤β 1≤ 5 °, 6 °≤β 3≤ 8 °;
Four, internal channel back segment geometric configuration:
4-1, internal channel back segment 7 top profiles are that elevation profile hatching is the batten profile of same SPL, internal channel back segment below profile is that elevation profile hatching is the batten profile of same SPL, the batten profile that internal channel back segment interior sidewall surface horizontal profile is same SPL, the batten profile that internal channel back segment outer side surface horizontal profile is same SPL;
4-2, internal channel back segment 7 outside batten walls and upstream internal channel leading portion outer side surface are tangent, the end corner cut β of batten wall outside internal channel back segment 2, behind batten wall end Yu Ge road, the axial distance between lip is L outside internal channel back segment 4; Inside internal channel back segment, batten wall and upstream internal channel leading portion interior sidewall surface are tangent, the end corner cut β of batten wall inside internal channel back segment 4, behind batten wall end Yu Ge road, the axial distance between lip 10 is L inside internal channel back segment 5.Meet 10 °≤β 2≤ 20 °, 30 °≤β 4≤ 40 °, 7L 6≤ L 4≤ 8L 6, L 4+ 1.3L 1≤ L 5≤ L 4+ 1.5L 1.L 6refer to that internal channel leading portion 6 lateral wall initiating terminals are apart from the distance of bomb body side;
4-3, internal channel back segment 7 export center on elevation profile from the geometric distance characterising parameter Wei Ge road height H on bomb body surface 1 2, meet 0.8D e≤ H 2≤ D e; The design of internal channel back segment is expansion pipeline, and its geometric description parameter is area divergence ratio A d, meet 1.1≤A d≤ 1.3; Area divergence ratio refers to the ratio of internal channel back segment outlet effective cross sectional area 9 and venturi import effective cross sectional area 8.
According to claim 1 based on flush type the method for designing every the plane Submerged Inlet 3 of road 2 layouts, it is characterized in that comprising the following steps:
Step 1, based on bomb body surface 1 design plane Submerged Inlet prototype 3 according to a conventional method;
Step 2, on plane Submerged Inlet 3 prototype bases, design according to the following steps flush type every road 2 profiles;
Step 2-1, design internal channel leading portion 6:
Step 2-1-1, design internal channel leading portion below profile 12 SPLs: according to actinal surface reference position L 2, the axial distance L behind venturi 13 Yu Ge roads, lower end between lip 10 3and the distance H between venturi 13 lower ends and bomb body lower surface 1 1determine internal channel leading portion below profile 12 SPLs on elevation profile, guarantee that batten stops corner cut and actinal surface ramp angle α 1unanimously; 0.6D wherein e≤ L 2≤ 3D e, 0.2D e≤ L 3≤ 0.3D e, 0.12D e≤ H 1≤ 0.15D e, 20 °≤α 1≤ 25 °;
Step 2-1-2, design internal channel leading portion top profile 11 molded line: again according to venturi height H twith actinal surface ramp angle α 1determine internal channel leading portion top profile 11 linear portions on elevation profile; 0.5 δ≤H wherein t≤ 1.5 δ;
Step 2-1-3, design internal channel leading portion 6 sidewall planes are at the linear portion on bomb body surface 1: according to actinal surface half width L 1, the axial distance L behind venturi 12 Yu Ge roads, lower end between lip 10 3, internal channel leading portion lateral wall plane and elevation profile angle β 1angle β with internal channel leading portion madial wall plane and elevation profile 3on bomb body surface 1, make by admission port forward position and lead to two, downstream linear portion; L≤L wherein 1≤ 2.55L, 0.2D e≤ L 3≤ 0.3D e, 3 °≤β 1≤ 5 °, 6 °≤β 3≤ 8 °;
Step 2-2, design diversion section 4:
Profile 5 on step 2-2-1, design diversion section: extend internal channel leading portion top profile 11 linear portions and obtain profile 5 slopes on diversion section, according to actinal surface, lead radius of circle R more surperficial 1 tangent with arc transition section and bomb body, thereby obtain on elevation profile profile 5 on diversion section; D wherein e≤ R≤1.5D e;
Step 2-3, design internal channel back segment 7:
Step 2-3-1, design internal channel back segment 7 sidewall batten walls are at the nurbs curve on bomb body surface 1: tangent according to internal channel back segment 7 outside batten walls and upstream internal channel leading portion 6 outer side surfaces, and the end corner cut β of batten wall outside internal channel back segment 2, behind batten wall end Yu Ge road, the axial distance between lip 10 is L outside internal channel back segment 4; Inside internal channel back segment, batten wall and upstream internal channel leading portion interior sidewall surface are tangent, the end corner cut β of batten wall inside internal channel back segment 4, behind batten wall end Yu Ge road, the axial distance between lip is L inside internal channel back segment 5on bomb body surface 1, make two nurbs curves that lead to bomb body both sides, downstream by internal channel leading portion bomb body surface linear portion; 10 °≤β wherein 2≤ 20 °, 7L 6≤ L 4≤ 8L 6, 30 °≤β 4≤ 40 °, L 4+ 1.3L 1≤ L 5≤ L 4+ 1.5L 1;
Effective import cross section of step 2-3-2 design internal channel back segment 7 and effectively outlet, effective import cross section 8 of internal channel back segment refers to the cross section that on sidewall batten, the tangent line of its two-end-point equates with this cross section angle excessively, effectively outlet 9 is as the same, and center, outlet is H from the distance Ji Ge road height of bomb body place plane 2, meet 0.8D e≤ H 2≤ D e;
Step 2-3-3 internal channel back segment 7 is designed to expand pipeline, and its geometric description parameter is area divergence ratio A d, the ratio of effective discharge area 9 and venturi import effective cross sectional area 8, meets 1.1≤A d≤ 1.3.
In conjunction with Figure 14, principle of work of the present invention is, due to Submerged Inlet slightly upstream position offer flush type every road, this flush type of airflow passes (provide in Figure 14 only have half flow field) when road, the boundary 1ayer low energy stream overwhelming majority developing from aircraft precursor is embedded in guiding bomb body both sides, Shi Ge road, thereby reduced and entered low energy in Submerged Inlet air-flow and flow shared ratio, improved the air inlet quality of Submerged Inlet, the aeroperformance of plane Submerged Inlet is increased dramatically.
Application example 1
1. technical index
Cruise Mach number: 0.5
Outlet Mach number: 0.32
2. scheme introduction
Scheme 1: in conjunction with Fig. 9, the plane Submerged Inlet profile by prior art design, with the closely-related design parameters of the present invention is: actinal surface incident nose angle α 1=23 °, venturi height H t=1 δ, actinal surface half width L 1=2.55L, area divergence ratio A d=1.1, actinal surface reference position L 2=0.6D e, the axial distance L behind Yu Ge road, venturi lower end between lip 3=0.29D e, the distance H between venturi lower end and bomb body lower surface 1=0.15D e, venturi height H 2=0.95D e, the axial distance L between lip behind batten wall end Yu Ge road outside internal channel back segment 4=7.72L 6, the axial distance L between lip behind batten wall end Yu Ge road inside internal channel back segment 5=L 4+ 1.4L 1, the angle β in internal channel leading portion lateral wall plane and elevation profile 1=4 °, the end corner cut β of batten wall outside internal channel back segment 2=15 °, the angle β in internal channel leading portion madial wall plane and elevation profile 3=6 °, the end corner cut β of batten wall inside internal channel back segment 4=36 °, every road actinal surface, lead radius of circle R=1.4D e.Other main geometry design parameter are as following table (D efor air intake port equivalent diameter):
The collapsible rotor aircraft Parameter of Overall Design that places an order of table 1
Scheme 2: in conjunction with Fig. 9, the plane Submerged Inlet profile by prior art design, with the closely-related design parameters of the present invention is: actinal surface incident nose angle α 1=23 °, venturi height H t=0.2 δ, actinal surface half width L 1=2.55L, area divergence ratio A d=1.1, actinal surface reference position L 2=0.6D e, the axial distance L behind Yu Ge road, venturi lower end between lip 3=0.29D e, the distance H between venturi lower end and bomb body lower surface 1=0.15D e, venturi height H 2=0.95D e, the axial distance L between lip behind batten wall end Yu Ge road outside internal channel back segment 4=7.72L 6, the axial distance L between lip behind batten wall end Yu Ge road inside internal channel back segment 5=L 4+ 1.4L 1, the angle β in internal channel leading portion lateral wall plane and elevation profile 1=4 °, the end corner cut β of batten wall outside internal channel back segment 2=15 °, the angle β in internal channel leading portion madial wall plane and elevation profile 3=6 °, the end corner cut β of batten wall inside internal channel back segment 4=36 °, every road actinal surface, lead radius of circle R=1.4D e.Other main geometry design parameter and table 1 are in full accord.
Scheme 3: the plane Submerged Inlet prototype of prior art design, other main geometry design parameter are consistent with table 1.
3. numerical simulation result
Numerical simulation result shows, as incoming flow Mach number M 0=0.5, angle of attack=0 °, during angle of side slip β=0 °, midplane Submerged Inlet of the present invention is meeting under the condition of driving engine traffic demand, the various performance parameters in air intake port cross section is: in scheme 1: total pressure recovery coefficient σ=0.977, stable state circumferential distortion index reached Practical level; In scheme 2: total pressure recovery coefficient σ=0.957, stable state circumferential distortion index reached Practical level; In scheme 3: total pressure recovery coefficient σ=0.949, stable state circumferential distortion index scheme 2, because partial design parameter is outside institute of the present invention claimed range, causes performance to decline to some extent as can be seen here, but is all better than scheme 3 prototype schemes.
Application example 2
1. technical index
Cruise Mach number: 0.5
Outlet Mach number: 0.32
2. scheme introduction
In conjunction with Fig. 9, the plane Submerged Inlet profile by prior art design, with the closely-related design parameters of the present invention is: actinal surface incident nose angle α 1=20 °, venturi height H t=0.5 δ, actinal surface half width L 1=2.55L, area divergence ratio A d=1.1, actinal surface reference position L 2=0.6D e, the axial distance L behind Yu Ge road, venturi lower end between lip 3=0.3D e, the distance H between venturi lower end and bomb body lower surface 1=0.15D e, venturi height H 2=1D e, the axial distance L between lip behind batten wall end Yu Ge road outside internal channel back segment 4=8L 6, the axial distance L between lip behind batten wall end Yu Ge road inside internal channel back segment 5=L 4+ 1.4L 1, the angle β in internal channel leading portion lateral wall plane and elevation profile 1=3 °, the end corner cut β of batten wall outside internal channel back segment 2=10 °, the angle β in internal channel leading portion madial wall plane and elevation profile 3=6 °, the end corner cut β of batten wall inside internal channel back segment 4=36 °, every road actinal surface, lead radius of circle R=1.4D e.Table one in other main geometry design parameter and example 1 is in full accord.
3. numerical simulation result
Numerical simulation result shows, as incoming flow Mach number M 0=0.5, angle of attack=0 °, during angle of side slip β=0 °, the various performance parameters in midplane Submerged Inlet of the present invention air intake port cross section under the condition that meets driving engine traffic demand is: total pressure recovery coefficient σ=0.967, stable state circumferential distortion index reached Practical level.The various performance parameters of plane Submerged Inlet prototype outlet under similarity condition is: total pressure recovery coefficient σ=0.949, stable state circumferential distortion index
Application example 3
1. technical index
Cruise Mach number: 0.5
Outlet Mach number: 0.32
2. scheme introduction
In conjunction with Fig. 9, the plane Submerged Inlet profile by prior art design, with the closely-related design parameters of the present invention is: actinal surface incident nose angle α 1=25 °, venturi height H t=1 δ, actinal surface half width L 1=1L, area divergence ratio A d=1.1, actinal surface reference position L 2=0.6D e, the axial distance L behind Yu Ge road, venturi lower end between lip 3=0.2D e, the distance H between venturi lower end and bomb body lower surface 1=0.15D e, venturi height H 2=0.8D e, the axial distance L between lip behind batten wall end Yu Ge road outside internal channel back segment 4=7L 6, the axial distance L between lip behind batten wall end Yu Ge road inside internal channel back segment 5=L 4+ 1.5L 1, the angle β in internal channel leading portion lateral wall plane and elevation profile 1=5 °, the end corner cut β of batten wall outside internal channel back segment 2=15 °, the angle β in internal channel leading portion madial wall plane and elevation profile 3=8 °, the end corner cut β of batten wall inside internal channel back segment 4=40 °, every road actinal surface, lead radius of circle R=1.5D e.Table one in other main geometry design parameter and example 1 is in full accord.
3. numerical simulation result
Numerical simulation result shows, as incoming flow Mach number M 0=0.5, angle of attack=0 °, during angle of side slip β=0 °, the various performance parameters in midplane Submerged Inlet of the present invention air intake port cross section under the condition that meets driving engine traffic demand is: total pressure recovery coefficient σ=0.964, stable state circumferential distortion index reached Practical level.The various performance parameters of plane Submerged Inlet prototype outlet under similarity condition is: total pressure recovery coefficient σ=0.949, stable state circumferential distortion index
Application example 4
1. technical index
Cruise Mach number: 0.5
Outlet Mach number: 0.32
2. scheme introduction
In conjunction with Fig. 9, the plane Submerged Inlet profile by prior art design, with the closely-related design parameters of the present invention is: actinal surface incident nose angle α 1=23 °, venturi height H t=1.5 δ, actinal surface half width L 1=1.4L, area divergence ratio A d=1.3, actinal surface reference position L 2=3D e, the axial distance L behind Yu Ge road, venturi lower end between lip 3=0.2D e, the distance H between venturi lower end and bomb body lower surface 1=0.12D e, venturi height H 2=1D e, the axial distance L between lip behind batten wall end Yu Ge road outside internal channel back segment 4=7L 6, the axial distance L between lip behind batten wall end Yu Ge road inside internal channel back segment 5=L 4+ 1.3L 1, the angle β in internal channel leading portion lateral wall plane and elevation profile 1=4 °, the end corner cut β of batten wall outside internal channel back segment 2=20 °, the angle β in internal channel leading portion madial wall plane and elevation profile 3=6 °, the end corner cut β of batten wall inside internal channel back segment 4=30 °, every road actinal surface, lead radius of circle R=1D e.Table one in other main geometry design parameter and example 1 is in full accord.
3. numerical simulation result
Numerical simulation result shows, as incoming flow Mach number M 0=0.5, angle of attack=0 °, during angle of side slip β=0 °, the various performance parameters in midplane Submerged Inlet of the present invention air intake port cross section under the condition that meets driving engine traffic demand is: total pressure recovery coefficient σ=0.975, stable state circumferential distortion index reached Practical level.The various performance parameters of plane Submerged Inlet prototype outlet under similarity condition is: total pressure recovery coefficient σ=0.949, stable state circumferential distortion index
Note: 1. in literary composition, parameter is all chosen from half bomb body He Bange road.
2. in literary composition, related SPL is all quoted the Piegl from Les, Wayne Tiller work, Mu Guowang etc. translate. < < non-uniform rational B-spline > >. and Beijing, press of Tsing-Hua University, 2010.
3. patent CN101994570 discloses the Submerged Inlet based on vortex excretion and has used the aircraft of this inlet channel, on the wall of Submerged Inlet internal channel, arrange along flowing to or vertical air bleed slot, by air bleed slot, the vortex in internal channel and low energy are banished out, improve largely the total pressure recovery coefficient of Submerged Inlet, reduced the flow distortion of outlet.Please note that this patent is that the precursor boundary 1ayer that Submerged Inlet had been sucked is already discharged from the bomb body surface at Submerged Inlet import place at vortex and the low energy stream thereof of internal channel generation.The present invention is different from its principle, bomb body surface in Submerged Inlet import forward position arranges flush type every road, by flush type, every road, the most boundary 1ayer low energy streams that develop from aircraft precursor are arranged to the admission port from Submerged Inlet, by flush type every road guiding bomb body both sides, thereby reduced and entered low energy in Submerged Inlet air-flow and flow shared ratio, improved the air inlet quality of Submerged Inlet, the aeroperformance of plane Submerged Inlet is increased dramatically.

Claims (3)

  1. One kind based on flush type the plane Submerged Inlet every road layout
    It is characterized in that: by Submerged Inlet and flush type, every road, formed;
    Flush type is positioned at Submerged Inlet admission port forward position every the import in road, flush type leads to bomb body both sides and symmetrical about bomb body central lateral plane every road by import forward position, flush type is comprised of diversion section and left and right two internal channel sections every road, wherein diversion section is positioned at lip upstream behind road, and internal channel section is positioned at lip downstream behind road; Diversion section profile consists of upper profile and two side walls, wherein goes up the slope of profile for adopting arc-shaped transitional surface and bomb body horizontal surface to join; Behind two internal channel Duan Congge roads, left and right, lip is separately and about the symmetrical "eight" shape channel architecture that is in elevation profile.
  2. According to claim 1 based on flush type the plane Submerged Inlet every road layout, it is characterized in that:
    Above-mentioned flush type is as follows every the concrete geometric configuration in road and characterising parameter, due to symmetry, for convenience of choosing half bomb body He Bange road below describing, is described:
    One, diversion section geometric configuration:
    1-1, diversion section import are opened in the slightly bomb body surface of upstream of Submerged Inlet, and its geometric description parameter is actinal surface half width L 1with actinal surface reference position L 2, actinal surface reference position refers to that lip, from the axial distance of Fighter Inlet, meets L≤L behind road 1≤ 2.55L, 0.6D e≤ L 2≤ 3D e; L refers to maximum half width of plane Submerged Inlet import; D erefer to the outlet equivalent diameter of Submerged Inlet;
    On 1-2, diversion section, profile geometric description parameter is actinal surface ramp angle α 1lead radius of circle R with actinal surface, meet 20 °≤α 1≤ 25 °, D e≤ R≤1.5D e; Actinal surface ramp angle refers to the angle of the straight section place slopes such as use and bomb body horizontal surface gained intersection;
    Two, how much overall configurations of internal channel:
    2-1, single internal channel section consist of top profile, below profile, interior sidewall surface and outer side surface, and shape of cross section is rectangle, and internal channel section is divided into internal channel leading portion and internal channel back segment with venturi cross-sectional plane;
    2-2, throat design are at the intersection of internal channel leading portion and internal channel back segment, and its geometric description parameter is the axial distance L between lip behind Yu Ge road, venturi lower end 3, the distance H between venturi lower end and bomb body lower surface 1with venturi height H t, meet 0.2D e≤ L 3≤ 0.3D e, 0.12D e≤ H 1≤ 0.15D e, 0.5 δ≤H t≤ 1.5 δ; δ refers to and does not offer flush type 1D before the prototype scheme middle distance plane Submerged Inlet admission port in road ethe boundary layer thickness at place;
    Three, internal channel leading portion geometric configuration:
    3-1, internal channel leading portion are the passage that cross-sectional area shrinks, its internal channel leading portion top profile is the continuity profile of profile slope on diversion section, internal channel leading portion below profile is that elevation profile hatching is the batten profile of same SPL, the plane that internal channel leading portion interior sidewall surface horizontal profile is same linear portion, the plane that internal channel leading portion outer side surface horizontal profile is same linear portion;
    The angle in 3-2, internal channel leading portion lateral wall plane and elevation profile is β 1, the angle in internal channel leading portion madial wall plane and elevation profile is β 3, meet 3 °≤β 1≤ 5 °, 6 °≤β 3≤ 8 °;
    Four, internal channel back segment geometric configuration:
    4-1, internal channel back segment top profile are that elevation profile hatching is the batten profile of same SPL, internal channel back segment below profile is that elevation profile hatching is the batten profile of same SPL, the batten profile that internal channel back segment interior sidewall surface horizontal profile is same SPL, the batten profile that internal channel back segment outer side surface horizontal profile is same SPL;
    Outside 4-2, internal channel back segment, batten wall and upstream internal channel leading portion outer side surface are tangent, the end corner cut β of batten wall outside internal channel back segment 2, behind batten wall end Yu Ge road, the axial distance between lip is L outside internal channel back segment 4; Inside internal channel back segment, batten wall and upstream internal channel leading portion interior sidewall surface are tangent, the end corner cut β of batten wall inside internal channel back segment 4, behind batten wall end Yu Ge road, the axial distance between lip is L inside internal channel back segment 5.Meet 10 °≤β 2≤ 20 °, 30 °≤β 4≤ 40 °, 7L 6≤ L 4≤ 8L 6, L 4+ 1.3L 1≤ L 5≤ L 4+ 1.5L 1.L 6refer to that internal channel leading portion lateral wall initiating terminal is apart from the distance of bomb body side;
    4-3, internal channel back segment export center on elevation profile from the geometric distance characterising parameter Wei Ge road height H on bomb body surface 2, meet 0.8D e≤ H 2≤ D e; The design of internal channel back segment is expansion pipeline, and its geometric description parameter is area divergence ratio A d, meet 1.1≤A d≤ 1.3; Area divergence ratio refers to the ratio of internal channel back segment outlet effective cross sectional area and venturi import effective cross sectional area.
  3. According to claim 1 based on flush type the method for designing every the plane Submerged Inlet of road layout, it is characterized in that comprising the following steps:
    Step 1, based on bomb body surface design plane Submerged Inlet prototype according to a conventional method;
    Step 2, on plane Submerged Inlet prototype basis, design according to the following steps flush type every road profile;
    Step 2-1, design internal channel leading portion:
    Step 2-1-1, design internal channel leading portion below profile SPL: according to actinal surface reference position L 2, the axial distance L behind Yu Ge road, venturi lower end between lip 3and the distance H between venturi lower end and bomb body lower surface 1determine internal channel leading portion below profile SPL on elevation profile, guarantee that batten stops corner cut and actinal surface ramp angle α 1unanimously; 0.6D wherein e≤ L 2≤ 3D e, 0.2D e≤ L 3≤ 0.3D e, 0.12D e≤ H 1≤ 0.15D e, 20 °≤α 1≤ 25 °;
    Step 2-1-2, design internal channel leading portion top profile molded line: again according to venturi height H twith actinal surface ramp angle α 1determine internal channel leading portion top profile linear portion on elevation profile; 0.5 δ≤H wherein t≤ 1.5 δ;
    Step 2-1-3, design internal channel leading portion sidewall plane are at the linear portion on bomb body surface: according to actinal surface half width L 1, the axial distance L behind Yu Ge road, venturi lower end between lip 3, internal channel leading portion lateral wall plane and elevation profile angle β 1angle β with internal channel leading portion madial wall plane and elevation profile 3on bomb body surface, make by admission port forward position and lead to two, downstream linear portion; L≤L wherein 1≤ 2.55L, 0.2D e≤ L 3≤ 0.3D e, 3 °≤β 1≤ 5 °, 6 °≤β 3≤ 8 °;
    Step 2-2, design diversion section:
    Profile on step 2-2-1, design diversion section: extend internal channel leading portion top profile linear portion and obtain profile slope on diversion section, then it is tangent by arc transition section and bomb body surface to lead radius of circle R according to actinal surface, thereby obtain on elevation profile profile on diversion section; D wherein e≤ R≤1.5D e;
    Step 2-3, design internal channel back segment:
    Step 2-3-1, design internal channel back segment sidewall batten wall are at the nurbs curve on bomb body surface: tangent according to batten wall outside internal channel back segment and upstream internal channel leading portion outer side surface, and the end corner cut β of batten wall outside internal channel back segment 2, behind batten wall end Yu Ge road, the axial distance between lip is L outside internal channel back segment 4; Inside internal channel back segment, batten wall and upstream internal channel leading portion interior sidewall surface are tangent, the end corner cut β of batten wall inside internal channel back segment 4, behind batten wall end Yu Ge road, the axial distance between lip is L inside internal channel back segment 5on bomb body surface, make two nurbs curves that lead to bomb body both sides, downstream by internal channel leading portion bomb body surface linear portion; 10 °≤β wherein 2≤ 20 °, 7L 6≤ L 4≤ 8L 6, 30 °≤β 4≤ 40 °, L 4+ 1.3L 1≤ L 5≤ L 4+ 1.5L 1;
    Effective import cross section of step 2-3-2 design internal channel back segment and effectively outlet, effective import cross section of internal channel back segment refers to the cross section that on sidewall batten, the tangent line of its two-end-point equates with this cross section angle excessively, effectively outlet is as the same, and center, outlet is H from the distance Ji Ge road height of bomb body place plane 2, meet 0.8D e≤ H 2≤ D e;
    Step 2-3-3 internal channel back segment is designed to expand pipeline, and its geometric description parameter is area divergence ratio A d, the ratio of effective discharge area and venturi import effective cross sectional area, meets 1.1≤A d≤ 1.3.
CN201410315774.3A 2014-07-03 2014-07-03 Based on flush type every the planar hexagonal crystal of road layout and method of designing Active CN104108470B (en)

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CN104386255A (en) * 2014-11-26 2015-03-04 江西洪都航空工业集团有限责任公司 Aircraft employing embedded air inlet channel
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CN106438047A (en) * 2015-08-04 2017-02-22 北京机电工程研究所 Buried gas inlet channel inner channel design method
CN106553760A (en) * 2015-09-25 2017-04-05 北京机电工程研究所 The method for designing of Submerged Inlet lip
CN107298180A (en) * 2017-06-09 2017-10-27 南京航空航天大学 A kind of aircraft and pneumatic adaptation design method for possessing one flowing control
CN113062802A (en) * 2021-04-09 2021-07-02 北京航空航天大学 Suction type air inlet channel for separating boundary layer and modeling method thereof
CN113120244A (en) * 2021-04-27 2021-07-16 成都飞机工业（集团）有限责任公司 Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage
CN113895636A (en) * 2021-11-18 2022-01-07 北京机电工程研究所 Embedded type invisible air inlet channel

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Cited By (12)

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Publication number Priority date Publication date Assignee Title
CN104386255A (en) * 2014-11-26 2015-03-04 江西洪都航空工业集团有限责任公司 Aircraft employing embedded air inlet channel
CN106438047A (en) * 2015-08-04 2017-02-22 北京机电工程研究所 Buried gas inlet channel inner channel design method
CN106438047B (en) * 2015-08-04 2018-04-10 北京机电工程研究所 The design method of Submerged Inlet internal channel
CN105109698A (en) * 2015-09-24 2015-12-02 江西洪都航空工业集团有限责任公司 Submerged air inlet of aircraft based on diverter air introduction
CN106553760A (en) * 2015-09-25 2017-04-05 北京机电工程研究所 The method for designing of Submerged Inlet lip
CN106553760B (en) * 2015-09-25 2019-03-22 北京机电工程研究所 The design method of Submerged Inlet lip
CN105905306A (en) * 2016-06-02 2016-08-31 江西洪都航空工业集团有限责任公司 Aircraft with submerged inlet using incoming flow for impacting
CN107298180A (en) * 2017-06-09 2017-10-27 南京航空航天大学 A kind of aircraft and pneumatic adaptation design method for possessing one flowing control
CN113062802A (en) * 2021-04-09 2021-07-02 北京航空航天大学 Suction type air inlet channel for separating boundary layer and modeling method thereof
CN113120244A (en) * 2021-04-27 2021-07-16 成都飞机工业（集团）有限责任公司 Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage
CN113895636A (en) * 2021-11-18 2022-01-07 北京机电工程研究所 Embedded type invisible air inlet channel
CN113895636B (en) * 2021-11-18 2024-01-05 北京机电工程研究所 Buried type stealth air inlet channel

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