CN101813027B - Bump air inlet method for realizing integration of unequal-strength wave system with forebody - Google Patents
Bump air inlet method for realizing integration of unequal-strength wave system with forebody Download PDFInfo
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Abstract
The invention provides a bump air inlet method for realizing integration of an unequal-strength wave system with a forebody, relating to the technical field of ultrasonic air inlet. The method comprises the following steps that: 1, an air inlet wave system adopts an external-compression double wave system structure based on an unequal-strength system, and the total pressure recovery coefficient sigma=sigma1*sigma2, wherein the sigma1 and the sigma2 are total pressure recovery coefficients of a conical shock wave and a normal shock wave; 2, a cone with a semi-cone angle delta c formed by the conical shock wave generates a second conical shock wave with second semi-cone angle beta in ultrasonic flow; 3, the bump height of the air inlet is h, the h/delta is 2-2.5 when the local boundary layer thickness is delta, the bump compressive plane generated in the step 2 is scaled to meet the requirement of an actual size; and 4, the lip of the air inlet adopts a conformal and sweepback lip design. The method realizes reduction of throat Mach number of the air inlet, improves the air inlet performance to ensure that the lip sweepback angle of the air inlet, the maximum turning angle of the bump compressive plane and the inlet normal shock wave angle are consistent, can increase the curve of the total pressure recovery coefficient, and reduces resistance coefficient.
Description
Technical field
The present invention relates to be a kind of based on do not wait high-amplitude wave system with the integrated Bump Design of Inlet of forebody, belong to the Supersonic Inlet technical field.
Background technique
The design of intake duct is one of key of fighter design.Intake duct not only will also will be considered the constraint of total arrangement and the requirement of integrated design for motor provides enough high-quality air qualities under all states when design, in addition, also must satisfy the overall stealthy requirement of fighter.For Supersonic Inlet, need by a series of shock wave, Supersonic Stream is slowed down is subsonic flow, continues deceleration diffusion, again flow direction engine in the diffuser passage.Traditional Supersonic Inlet Design generally adopts slant compression plate or compression cone to form multishock, and every road and dividing plate Fighter Inlet is lifted away from fuselage surface by boundary layer, enters intake duct to avoid the low energy air-flow in the fuselage surface boundary layer.
Every the road Supersonic Inlet, also claim the Bump intake duct without boundary layer, be by Lockheed Martin Corporation design and on the F-35 aircraft a kind of novel air inlet path of successful Application.The suction port of this intake duct does not arrange conventional fixed boundary layer every the road, but by Computer Design the projection piece (or bulge) of a three-dimension curved surface.The compression to air-flow is played in this bulge, and produces a pressure distribution that air stream on accompany surface is pushed away intake duct.Whole gas handling system does not have movable member, does not have the boundary layer isolating plate, does not have blow-off system and bypass system yet, has reduced by 300 pounds structure weight, has therefore reduced production and cost of use yet.
Because external consistent pneumatic design technology to the advanced person holds in close confidence, about the data of F-35 aircraft only has general report and disclosed aircraft picture, the external open source literature of relevant Bump Design of Inlet and performance study does not almost have.In recent years, domestic have many units to carry out research work to the Bump intake duct, wherein the Bump intake duct of Chengdu Aircraft Design ﹠ Research Institute's design and having used at domestic FC-1 " brave dragon " aircraft.
Yet, the focus of Bump intake duct mainly being concentrated on the design of three-dimensional bulge compressing surface both at home and abroad, the document of having delivered is not all paid close attention to the integrated design of Bump intake duct and aircraft forebody, does not provide relevant integrated design adopting parameters principle.
Summary of the invention
The object of the invention provides a kind of inlet throat Mach number that reduces, improve inlet characteristic, make the maximum deflection angle of inlet lip sweepback angle and bulge compressing surface, import normal shock wave angle consistent, can increase the total pressure recovery coefficient curve, reduce resistance coefficient based on not waiting high-amplitude wave system and the integrated Bump intake duct of forebody.
The present invention adopts following technological scheme for achieving the above object:
A kind of method that realizes not waiting high-amplitude wave system and the integrated Bump intake duct of forebody, Supersonic Stream produces conical shock wave one at the head of bulge compressing surface, forms one normal shock wave before inlet lip;
The first step: the intake duct wave system adopts based on the external-compression type two wave system structures that do not wait high-amplitude wave system, and the total pressure recovery coefficient of intake duct multishock is σ
s=σ
1σ
2, σ wherein
1, σ
2Be respectively the total pressure recovery coefficient of conical shock wave, normal shock wave, by waiting ripple to join by force the ripple theory analysis, total pressure recovery coefficient was the highest when the ripple of twice ripple equated by force, was best wave system;
Second step: semi-cone angle is δ
cCircular cone in supersonic flow, produce the conical shock wave that semi-cone angle is β, the circle radius of conical shock wave is R, with the plane truncated cone shape shock wave of distance cone axis linear distance d, d＜R wherein, the streamline that every bit sends backward on plane taken and the conical shock wave intersection consists of the bulge compressing surface;
The 3rd step: make that the Fighter Inlet bump height is h, local boundary layer thickness is δ, satisfy relation h/ δ=2～2.5 between Fighter Inlet bump height h and the local boundary layer thickness δ, the bulge compressing surface that second step is generated carries out convergent-divergent, satisfies the actual size requirement;
The 4th step: inlet lip adopts conformal and the design of sweepback lip, the import antelabium is most of fits with the Conical Shock Wave face, the lip sweepback angle is consistent with the maximum deflection angle of bulge compressing surface, import normal shock wave angle respectively, to increase the total pressure recovery coefficient curve, to reduce resistance coefficient.
Inflow Mach number behind the normal shock wave of the present invention is not more than 0.75.
The present invention goes to intercept the conical flow flow field with plane or the curved surface that distance generates body circular cone axis different heights h, and face is terminal identical with conical tip line and axis angle as long as institute dams, and the Waverider profile that then generates is similar.
The present invention calculates Conical Shock Wave angle β according to the import wave system of intake duct
ConeWith circular cone semi-cone angle δ
c, then determine the profile deflection angle theta, generate the bulge compressing surface according to Waverider profile similar Design principle at last.
Make that the bulge width is W, bulge width W and meet following Changing Pattern apart from the ratio W/d between the d and bulge compressing surface deflection angle theta, namely when W/d 〉=10, the profile deflection angle theta is close to circular cone semi-cone angle δ
c, δ
c-θ＜1 °.
The present invention adopts technique scheme, compared with prior art has following advantage:
1, utilizes that of the present invention not wait high-amplitude wave be design method, can reduce the inlet throat Mach number, improve inlet characteristic.
2, utilize the Waverider bulge compressing surface similar Design method based on the profile drift angle of the present invention, can design processes simplified, no longer need parameter d is compared and optimizes.
3, utilize bulge design height that the present invention sets up and the relation between the local boundary layer thickness, bulge and aircraft forebody can be carried out integrated design.
4, utilize conformal lip design of the present invention, can make the most of and shock surface applying of import antelabium, avoid the top overflow of lip cover.
5, utilize sweepback lip of the present invention design, make the maximum deflection angle of inlet lip sweepback angle and bulge compressing surface, import normal shock wave angle consistent, can increase total pressure recovery coefficient curve, reduction resistance coefficient.
Description of drawings
Fig. 1 is Bump Fighter Inlet wave system design diagram.
Fig. 2 is the Bump Fighter Inlet wave system that obtains by flow average computation Mach number and total pressure recovery coefficient figure behind Conical Shock Wave and the normal shock wave when different semi-cone angle.
Fig. 3 (a) is with schematic representation in the xoy coordinate surface of plane truncated cone shape shock wave Waverider bulge compressing surface in supersonic flow.
Fig. 3 (b) is with schematic representation in the yoz coordinate surface of plane truncated cone shape shock wave Waverider bulge compressing surface in supersonic flow.
Fig. 3 (c) is with schematic representation in the xoz coordinate surface of plane truncated cone shape shock wave Waverider bulge compressing surface in supersonic flow.
Fig. 3 (d) is the Waverider bulge compressing surface profile schematic three dimensional views of using plane truncated cone shape shock wave in supersonic flow.
Fig. 4 is bulge compressing surface deflection angle theta schematic representation.
Fig. 5 is that different distance d place cuts semi-cone angle δ
cThe bulge compressing surface deflection angle theta of the conical shock wave flow field gained that=12 ° circular cone generates and the relation of d.
Fig. 6 is the relation apart from the ratio W/d of d and bulge width W and bulge compressing surface deflection angle theta.
Fig. 7 is Waverider profile similar Design principle schematic.
Fig. 8 is bulge and boundary layer thickness schematic representation in the Fighter Inlet cross section.
Fig. 9 is that boundary layer Area Ratio and bulge/every road height relationships figure are got rid of in import cross section bulge.
Figure 10 is the conformal import of Fighter Inlet cross section and conical shock wave schematic representation.
Figure 11 (a) is the inlet total pres sure recovery coefficients comparison figure of different lips sweepback angle scheme.
Figure 11 (b) is the Inlet drag coefficients comparison figure of different lips sweepback angle scheme.
Figure 12 is that the lip sweepback angle is 20 ° intake duct moulding figure.
Among the figure: 1, Supersonic Stream, 2, bulge compressing surface, 3, conical shock wave, 4, inlet lip, 5, normal shock wave, 6, cone, 7, the plane of truncated cone shape shock wave, 8, the intersection (being the Waverider costa) of conical shock wave and plane taken, 9, bulge cross section, 10, fuselage molded line, 11, the import boundary layer/every the road height and position, 12 inlet lip costas.
Embodiment
The present invention will contrast below accompanying drawing and give more fully to illustrate, given among each figure is an application example of the present invention, only is not confined to application example described herein and should not be construed to the present invention.
(1) do not wait the design of high-amplitude wave system
Fig. 1 illustrates one and adopts Bump Fighter Inlet wave system schematic representation of the present invention.Supersonic Stream 1 produces conical shock wave 3 one at the head of bulge compressing surface 2, at one normal shock wave of inlet lip 4 front formation 5.Take design incoming flow Mach number Ma=1.6 as example, adopt the two wave systems design of " conical shock wave+normal shock wave ", the total pressure recovery coefficient of intake duct multishock is σ
s=σ
1σ
2, σ wherein
1, σ
2Be respectively the total pressure recovery coefficient of first and second road shock wave, by waiting ripple to join by force the ripple theory analysis, total pressure recovery coefficient was the highest when the ripple of twice ripple equated by force, was best wave system.
Owing to be conical flow behind the Conical Shock Wave, the flow field parameter skewness be to wait parameter line along the ray of crossing conical tip, so the average Mach number behind the Conical Shock Wave generally calculates with the mean value of minimum and maximum Mach number between the conical surface and the shock surface.Fig. 2 has provided Mach number and total pressure recovery coefficient figure, wherein M α behind Conical Shock Wave corresponding to each semi-cone angle of obtaining by the flow average computation
1, M α
2Be respectively the Mach number behind first and second road shock wave, circular cone semi-cone angle δ
cIn the time of=24 °, the highest by total pressure recovery coefficient behind the ripple that waits the design of high-amplitude wave system, reach 0.985, corresponding Angle of Shock Waves is β
Cone=49.9 °, this is best wave angle β
Opt
Be based on without viscosity flow, two dimensional surface shock theory design intake duct wave system Deng the design of high-amplitude wave system.What the present invention adopted does not wait high-amplitude wave system to design, and is based on the consideration of following several respects:
1. the viscosity of fluid
Owing to the impact of fluid viscosity, can form the boundary layer that gradually development thickens at solid wall surface, the actual deflection angle of air-flow is increased, wave system enhancing, Angle of Shock Waves are increased.
2. the heterogeneity in flow field
The heterogeneity in conical flow flow field, so that the Angle of Shock Waves of total pressure recovery coefficient when maximum be less than best wave angle, about 1 ° less than normal of corresponding semi-cone angle.
3. the low-speed performance of intake duct
Consider low-speed performance, the choosing of the semi-cone angle of circular cone should make shock wave lift-off not under each Mach number as far as possible, and therefore, the semi-cone angle of circular cone can not be excessive.Semi-cone angle is less, and corresponding lift-off Mach number is just lower, yet this moment, the off-target wave system was large, and the wave system loss is also large, so semi-cone angle can not be too little, the span of suggestion semi-cone angle is 16 °＜δ
c＜25 °.
4. import/venturi Mach number requirement
For inferior, Supersonic Inlet, General Requirements inlet throat Mach number M α
t＜0.85, otherwise can because airspeed is excessive, cause the interior conduit loss to increase.If when joining by force the design of ripple principle, then the conical shock wave ripple is bigger than normal by force, and Mach number is less than normal behind the ripple, (Fighter Inlet) Mach number is bigger than normal after causing normal shock wave, air-flow is when passing through import to this section of venturi constricted channel, and Mach number can further increase, and causes the venturi Mach number excessive.In example, Design of Inlet Mach number 1.6 is principle when carrying out the wave system design by waiting high-amplitude wave, and (Fighter Inlet) Mach number namely reaches 0.836～0.855 behind the normal shock wave, the venturi Mach number also will continue to increase, therefore, need to reduce inflow Mach number, must adopt and not wait the design of high-amplitude wave system.
, can be calculated inflow Mach number and be not more than 0.75 and can meet the demands to the throat area contraction ratio according to import, therefore choose semi-cone angle δ
c=20 °, this moment Conical Shock Wave angle β
Cone=45.8 °.
(2) based on the Waverider bulge compressing surface similar Design method of profile drift angle
Determined circular cone semi-cone angle δ
c, Bump intake duct bulge compressing surface can obtain profile according to the generation body method of finding the solution conical flow.Fig. 3 shows the schematic representation of truncated cone shape shock wave bulge compressing surface in supersonic flow, and semi-cone angle is δ
c Circular cone 6 in supersonic flow, produce the conical shock wave 3 that semi-cone angle is β, use the plane 7 truncated cone shape shock waves 3 apart from axial line distance d, the streamline that every bit sends backward on plane taken 7 and the conical shock wave intersection 8 has just consisted of bulge compressing surface 2.
All do not provide at present the selection principle of plane taken 7 and circular cone 6 axial line distance d both at home and abroad about the design of Waverider, the present invention has proposed a kind of similar Design method based on the profile angle of yaw according to the feature of conical flow.As shown in Figure 4, the profile deflection angle theta is defined as the tangent line of bulge compressing surface 2 vertical symmetry plane molded line ends and intake duct the place ahead and comes angle between the flow path direction, because profile is stream interface after the conical flow, so the profile angle of yaw is the terminal angle of yaw of streamline.
Fig. 5 shows section semi-cone angle δ at different distance d place
cThe bulge compressing surface bias angle theta of the conical shock wave flow field gained that=12 ° circular cone generates and the relation of d.The bulge compressing surface bias angle theta that different distance d place intercepts is different, along with the increase of d, δ
cReduce.Fig. 6 shows the relation apart from the ratio W/d of d and bulge width W and bulge compressing surface bias angle theta, different circular cone semi-cone angle, and W/d and profile deflection angle theta meet same Changing Pattern, and namely when W/d 〉=10, the profile deflection angle theta is close to circular cone semi-cone angle δ
c, δ
c-θ＜1 °.
Fig. 7 shows Waverider profile similar Design principle schematic.Used respectively two planar interception conical shock waves 3 of some A and some C to generate Waverider, the length of Waverider is respectively AB and CD, although the two is different apart from d apart from the circular cone axis, but it is on the ray of φ that some B and some D all were positioned at circular cone 6 summit angles, face end is identical with the angle of circular cone 6 summit lines and circular cone axis as long as institute dams, the Waverider profile that generates is just similar, and d is irrelevant with the intercepting height, and latter two profile of nondimensionalization overlaps fully.
Therefore, characteristic of the present invention is that the design Waverider no longer needs comparison and the optimization to parameter d, but the high-amplitude wave that do not wait that utilizes the present invention to propose is design, at first according to import wave system designing and calculating Conical Shock Wave angle β
ConeWith circular cone semi-cone angle δ
c, then determine the profile deflection angle theta, generate the bulge compressing surface according to Waverider profile similar Design principle at last.
(3) set up relation between bulge design height and the local boundary layer thickness
One of Main Function of bulge is to get rid of the fuselage boundary layer, owing to do not have boundary layer every the road, therefore bulge some be immersed in the fuselage boundary layer, so the design of bulge must be considered the relation with the fuselage boundary layer, i.e. relation between bump height h and the local boundary layer thickness δ.
Fig. 8 shows bulge and boundary layer thickness schematic representation in the Fighter Inlet cross section, and bulge cross section 2 is with shadow representation among the figure.On fuselage 10 surfaces, one deck boundary layer is arranged, 11 expressions (dotted line 11 positions also are commonly used for boundary layer every the position in road) of boundary layer thickness position with dashed lines, if boundary layer thickness is δ, ratio by given bump height h and δ, can be by the scaling of the given bulge compressing surface of h/ δ, the drop shadow curves of bulge in cross section of different sizes from every road and import antelabium line different intersection points is arranged.Suppose that the height after the front boundary layer of import is through the bulge surface is constant, still be δ, then because the effect of bulge the incoming flow boundary layer is moved to both sides row, so boundary layer exists only in two class delta-shaped regions of below, dotted line 11 positions, bulge top and antelabium line inboard.Use A
DiverterExpression is every the area of contour in road, A
BumpThe area of contour of expression bulge, A
FlowbyExpression correspondence boundary layer in the road area is excluded the area of part, namely uses A
DiverterDeduct the remaining area of above-mentioned two class triangle areas, the approximate A that uses
Flwby/ A
DiverterThe eliminating effect of expression boundary layer.Work as A
Flowby/ A
DiverterRepresented that boundary layer was all got rid of at=1 o'clock.
Fig. 9 has provided the bulge of import cross section and has got rid of boundary layer Area Ratio A
Flowby/ A
Diverter, bulge and every road Area Ratio A
Bump/ A
DiverterAnd bulge and the relation between road aspect ratio h/ δ.Can find out that along with h/ δ is increased to 4 from 1, the eliminating amount of boundary layer increases, but the amplitude that increases slows down h/ δ=4 o'clock A gradually
Floby/ A
Diverte=0.929, namely bump height is larger, and the boundary layer of eliminating is more.
But on the other hand, bump height is larger, and then the wind-exposuring area of bulge is also larger.Can find out, h/ δ=2 o'clock, the area of contour of bulge is close to the area of contour every the road, A
Bump/ A
Diverter=0.933.H/ δ=4 o'clock, the area of contour of bulge is 3.733 times every the road area of contour.The bulge area increases, and for satisfying the requirement of intake duct circulation area, then must raise the lip cover of intake duct, has increased again thus the wind-exposuring area of whole intake duct, and resistance also can correspondingly increase.Therefore, bump height can not be too little, and is highly too little, and then bulge major part buries in boundary layer, and the amount of getting rid of boundary layer is limited; Bump height can not be too large, and is highly too large, and then resistance is too large.
Bump height is not an independently parameter, restricted by a lot of design parameters.As design Mach number, generation body semi-cone angle δ
c, after the parameter such as profile deflection angle theta determines, the profile of bulge has determined that its length and width height is all given, can need to zoom in or out the bulge compressing surface that generates according to actual size.Analyze from Fig. 9, h/ δ=2～2.5 are comparatively suitable, boundary layer eliminating this moment amount 0.793～0.842, and the bulge area of contour is 0.933～1.458 times every the road area of contour.
(4) conformal, the design of sweepback lip
Figure 10 shows conformal import and conical shock wave schematic representation in the Fighter Inlet cross section.Lead general plane or the curved surface intercepting Conical Shock Wave of adopting of Waverider design based on the cone of conical shock wave and generate the bulge compressing surface, therefore have the mismatch problem of bulge compressing surface and fuselage surface.The present invention has considered the integrated requirement of fuselage when design, adopt fuselage 10 curved surfaces intercepting conical shock wave 3 to generate bulge compressing surface 2, so that bulge compressing surface 2 merges with fuselage 10 surface smoothing ground.
Because bulge 2 produces conical shock wave 3, and has formed a crescent shape zone between the fuselage 10, only have and when actinal surface shape and conical shock wave 3 are fitted fully, just can not cause overflow above the lip cover.As can see from Figure 10, owing to adopted the conformal import, so that the most of and conical shock wave 3 of import antelabium fits, only there is overflow the both sides such as intersecting with fuselage, and the overflow of both sides is inevitably, and the boundary layer that the bulge surface is excluded is flowed outward by two side direction imports just.
The Bump intake duct is got rid of the effect of boundary layer and is finished by bulge compressing surface and lip acting in conjunction.Figure 11 has provided the inlet characteristic comparison diagram of different lips sweepback angle scheme, and abscissa is Flow coefficient of inlet φ among the figure, and y coordinate is respectively total pressure recovery coefficient σ and resistance coefficient C
DCan find out, inlet total pres sure recovery coefficient curve under the different sweepback angle and the approximate parallel distribution of drag-coefficient curve, increase along with the lip sweepback angle, the total pressure recovery coefficient curve of intake duct rises, reach the highest when being 20 ° at the sweepback angle, the total pressure recovery coefficient curve descends again in the time of 30 °, between 10 ° and 20 °; Drag-coefficient curve then is to reduce along with the increase at lip sweepback angle, and resistance coefficient was minimum when the sweepback angle was 20 °, and curve is between 10 ° and 20 ° in the time of 30 °.It is 20 ° intake duct moulding figure that Figure 12 has provided the lip sweepback angle.
According to computational analysis, having proposed the inlet lip sweepback angle should the design principle consistent with the maximum deflection angle of bulge compressing surface, import normal shock wave angle.In the design process of Bump intake duct, the design of bulge compressing surface is relevant with the design of lip, can not be with the isolated design of these two-part.
Above-described embodiment just is used for explanation of the invention, and can not be as limitation of the present invention.Bump Design of Inlet Mach 2 ship 1.6 in this example, the present invention also is applicable to all incoming flow Mach numbers less than 2.0 Bump intake duct.Of the present inventionly do not wait high-amplitude wave system design, be applicable to the Supersonic Inlet of other type yet, comprise the different entry shapes such as binary, axisymmetric, and external-compression type, mixing compression type wave system intake duct.Waverider bulge compressing surface similar Design method based on the profile drift angle of the present invention also is applicable to any ultrasound velocity, Hypersonic waveriders design, and Waverider generates and carries can be normal cone, also can be elliptic cone or other broad sense circular cone.Conformal of the present invention, sweepback lip design, and also are applicable to ultrasound velocity, the hypersonic inlet of other type.Therefore the mode of execution that mentality of designing every and of the present invention is identical is all in protection scope of the present invention.
Claims (5)
1. a realization is based on the method that does not wait high-amplitude wave system, the integrated Bump intake duct of forebody, it is characterized in that: Supersonic Stream (1) produces one conical shock wave (3) at the head of bulge compressing surface (2), at one normal shock wave of the front formation of inlet lip (4) (5);
The first step: the intake duct wave system adopts based on the external-compression type two wave system structures that do not wait high-amplitude wave system, and the total pressure recovery coefficient of intake duct multishock is σ
s=σ
1σ
2, σ wherein
1, σ
2Be respectively the total pressure recovery coefficient of conical shock wave (3), normal shock wave (5), by waiting ripple to join by force the ripple theory analysis, total pressure recovery coefficient was the highest when the ripple of twice ripple equated by force, was best wave system;
Second step: semi-cone angle is δ
cCircular cone (6) in supersonic flow, produce the conical shock wave (3) that semi-cone angle is β, the circle radius of conical shock wave (3) is R, plane (7) truncated cone shape shock wave (3) with distance cone axis linear distance d, wherein d＜R goes up the streamline formation bulge compressing surface that every bit sends backward from plane taken (7) and conical shock wave intersection (8);
The 3rd step: make that the Fighter Inlet bump height is h, local boundary layer thickness is δ, satisfy relation h/ δ=2～2.5 between Fighter Inlet bump height h and the local boundary layer thickness δ, the bulge compressing surface that second step is generated carries out convergent-divergent, satisfies the actual size requirement;
The 4th step: inlet lip adopts conformal and the design of sweepback lip, the import antelabium is most of fits with the Conical Shock Wave face, the lip sweepback angle is consistent with the maximum deflection angle of bulge compressing surface, import normal shock wave angle respectively, to increase the total pressure recovery coefficient curve, to reduce resistance coefficient.
2. realization according to claim 1 is based on the method that does not wait high-amplitude wave system, the integrated Bump intake duct of forebody, and it is characterized in that: the inflow Mach number behind the normal shock wave is not more than 0.75.
3. realization according to claim 1 is based on the method that does not wait high-amplitude wave system, the integrated Bump intake duct of forebody, it is characterized in that: the plane or the curved surface that generate body circular cone axis different heights d with distance go to intercept the conical flow flow field, face is terminal identical with conical tip line and axis angle as long as institute dams, and the Waverider profile that then generates is similar.
4. realization according to claim 1 is characterized in that based on the method that does not wait high-amplitude wave system, the integrated Bump intake duct of forebody: the import wave system according to intake duct calculates Conical Shock Wave angle β cone and circular cone semi-cone angle δ
c, then determine the profile deflection angle theta, generate the bulge compressing surface according to Waverider profile similar Design principle at last.
According to claim 1 or 4 described realizations based on the method that does not wait high-amplitude wave system, the integrated Bump intake duct of forebody, it is characterized in that: make that the bulge width is W, bulge width W and meet following Changing Pattern apart from the ratio W/d between the d and bulge compressing surface bias angle theta, namely when W/d 〉=10, the profile deflection angle theta is close to circular cone semi-cone angle δ
c, δ
c-θ＜1 °.
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| CN102518517B (en) * | 2011-12-08 | 2014-03-05 | 南京航空航天大学 | Design method of bistable air inlet |
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| CN102996253B (en) * | 2012-12-31 | 2015-03-04 | 中国人民解放军国防科学技术大学 | Supersonic air intake duct and wall face determination method of supersonic air intake duct |
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| CN112985755B (en) * | 2021-05-20 | 2021-07-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Boundary layer similar parameter simulation method for accurately predicting cavity flow acoustic load |
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