CN105329462A - Changeable wall surface pressure distribution rule-based osculating flow field ride precursor design method - Google Patents
Changeable wall surface pressure distribution rule-based osculating flow field ride precursor design method Download PDFInfo
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Abstract
The invention discloses a changeable wall surface pressure distribution rule-based osculating flow field ride precursor design method comprising the following steps: S1, determining curves having three kinds of different wall surface pressure distribution rules, wherein the three curves are taken as revolution body generatrices, designing three kinds of different revolution bodies, and solving supersonic velocity axially symmetric flow fields of the three kinds of different revolution bodies, wherein the solved flow fields are taken as standard flow fields having three kinds of different wall surface pressure distribution rules; S2, designing a shock wave outlet line according to the performance requirements of a ride precursor, performing flow field solving in each osculating plane by applying an osculating principle, and combining a three-dimensional standard flow field by all osculating plane flow fields; and S3, determining a projection curve of the edge line of the ride precursor on the bottom, and generating an osculating floe field ride precursor aerodynamic configuration by performing a flow tracking method line in each osculating plane obtained in S2 according to the shock wave outlet line. The ride precursor designed by the method can be used for meeting air inlet channel inlet high pressure rising ratio and can also be used for fully playing a high resistance rising ratio character.
Description
Technical field
The present invention relates to the technical field of hypersonic aircraft Design of Aerodynamic Configuration, be specifically related to a kind of osculating flow field waverider forebody derived method of designing based on the variable wall surface pressure regularity of distribution.
Background technology
Air-breathing hypersonic vehicle refer to flight Mach number be greater than 5, with airbreathing motor or its combination engine be major impetus, can at atmospheric envelope and the aircraft across the flight of atmospheric envelope medium-long range, its application form comprises hypersonic cruise missile, hypersonicly has multiple aircraft such as people/unmanned aerial vehicle and aerospace plane etc.
The aerodynamic configuration of hypersonic aircraft, mainly contain rotational symmetry configuration, lifting body configuration and waverider-derived three major types, wherein waverider-derived utilizes shock wave compression principle (rider principle) to achieve the pneumatic requirement of high lift-drag ratio under hypersonic flight condition, except how taking into account the problem of the protection of leading edge Aerodynamic Heating and aeroperformance, the research of this configuration is tending towards ripe.
The core of waverider-derived method of designing is the selection in benchmark flow field, the method for designing that different benchmark flow fields is corresponding different, and existing method has following several: wedge inducing defecation by enema and suppository, cone inducing defecation by enema and suppository, wedge cone method and the osculating class generation method based on supersonic speed axial symmetry flow.Wherein, osculating class method of designing mainly comprises osculating cone design theory, osculating axisymmetry design theory and osculating flow Field Design theory.Osculating cone theazy makes the shock line shape in Waverider bottom transverse cross section no longer be confined to circular arc or straight line, but can carry out appropriate design according to inlet lip profile.The benchmark flow field that osculating axisymmetry theory proposes in osculating plane can no longer be confined to taper flow field, but can need to select suitable rotational symmetry benchmark flow field according to design.Application osculating cone and osculating axisymmetry theoretical can obtain transverse flow evenly waverider-derived, and effectively can improve waverider forebody derived (inlet mouth) flow field quality, be conducive to fuselage-inlet channel integrated design.The benchmark flow field that osculating flow field theory proposes in each osculating plane is no longer confined to same axisymmetric flow field, but can need in each osculating plane, select different rotational symmetry benchmark flow fields according to design.
2011, the people such as He Xuzhao propose curved surface that a kind of employing has straight line shock wave and an isentropic compression wave system and bores method of designing as benchmark flow field in document " close curved surface cone Waverider---method of designing and performance analysis " (mechanics journal), effectively overcome traditional osculating cone Waverider amount of compression deficiency and plot ratio shortcoming less than normal.But the method exists certain defect, namely due to the raising of voltage rise ratio, waverider forebody derived high lift-drag ratio characteristic is caused to be not in full use.
Summary of the invention
The invention provides a kind of osculating flow field waverider forebody derived method of designing based on the variable wall surface pressure regularity of distribution, solving existing waverider forebody derived can only carry out by the constant regularity of distribution of wall pressure the deficiency that designs.Waverider forebody derived based on this method design can either meet the requirement of inlet mouth height voltage rise ratio, can give full play to again the high lift-drag ratio characteristic of waverider forebody derived.
For solving the problem, the present invention adopts following technical scheme:
Based on an osculating flow field waverider forebody derived method of designing for the variable wall surface pressure regularity of distribution, comprise the following steps:
S1, the different curve of given three kinds of wall pressure distribution rules, be respectively the curve that the constant curve of curve, wall pressure that wall pressure raises and wall pressure reduce, using three curves as gyro-rotor bus, design three kinds of different gyro-rotors, solve the supersonic speed axisymmetric flow field around these three kinds of gyro-rotors respectively, and will the flow field that obtains be solved as the different benchmark flow field of three kinds of wall pressure distribution rules;
S2, performance requriements according to waverider forebody derived, shock wave being exported molded line is divided into three sections to design, and ensure the junction continual curvature of molded line at every section of curve of design, namely the second derivative of curve is continuous, then according to designed shock wave outlet molded line, application osculating principle carries out flow field calculation at each osculating plane, all osculating plane group of flow fields synthesis three-dimensional references flow fields;
S3, the given drop shadow curve of waverider forebody derived costa in bottom, according to the shock wave outlet molded line of step S2, use streamlined impeller method, generate osculating flow field waverider forebody derived aerodynamic configuration in each osculating plane of step S2.
The present invention adopts based on the theory of osculating flow field, given identical inlet flow conditions, according to the requirement of Waverider exhibition to diverse location performance, choose the benchmark flow field of wall pressure rising in inlet mouth position (namely Waverider exhibition is to middle part), ensure inlet mouth height voltage rise ratio characteristic; Choose the benchmark flow field of wall pressure reduction in Waverider exhibition to two ends, the characteristic of waverider forebody derived high lift-drag ratio is not fully exerted; Part between above-mentioned two positions chooses the constant benchmark flow field of wall pressure, as transition.
Advantageous Effects of the present invention:
The invention provides a kind of new Waverider method of designing, namely, based on the osculating flow field waverider forebody derived method of designing of the variable wall surface pressure regularity of distribution, this method overcomes traditional osculating cone Waverider and only takes a kind of benchmark flow field of wall pressure distribution rule to carry out the deficiency designed, the method can according to the requirement of Waverider exhibition to diverse location performance, choose the benchmark flow field of wall pressure rising in inlet mouth position (namely Waverider exhibition is to middle part), ensure inlet mouth height voltage rise ratio characteristic; Choose the benchmark flow field of wall pressure reduction in Waverider exhibition to two ends, the characteristic of waverider forebody derived high lift-drag ratio is not fully exerted;
Accompanying drawing explanation
Fig. 1 is the benchmark flow field section-drawing of three kinds of different wall pressure distribution rules;
Wherein, straight line 1-3-11 represents the shock wave that the circular cone generated by bus 1-2 produces under design point; 2-11 represents the left lateral characteristic curve sent by 2; 1-2-5,1-2-6,1-2-7 represent three gyro-rotor buses that wall pressure raises, wall pressure is constant, wall pressure reduces respectively; Curve 3-4-8 represents the streamline that in the flow field that the gyro-rotor generated at bus 1-2-5 produces, streamlined impeller obtains; Curve 3-4-9 represents the streamline that in the flow field that the gyro-rotor generated at bus 1-2-6 produces, streamlined impeller obtains; Curve 3-4-10 represents the streamline that in the flow field that the gyro-rotor generated at bus 1-2-7 produces, streamlined impeller obtains; 12 represent that wall pressure raises the leaning angle of gyro-rotor bus at point 5 place; 13 represent the leaning angle of the constant gyro-rotor bus of wall pressure at point 6 place; 14 represent that wall pressure reduces the leaning angle of gyro-rotor bus at point 7 place; The overall length in 15 expression benchmark flow fields; The beam overall in 16 expression benchmark flow fields, i.e. shock wave exit radius; The initial compression angle of 17 expression gyro-rotors, i.e. the angle of bus 1-2-6 and x-axis;
Fig. 2 is shock wave outlet schematic diagram;
Wherein, 18 is the projection line of waverider forebody derived costa in shock wave outlet, is also waverider forebody derived upper surface trailing edge line; 19 is waverider forebody derived lower surface trailing edge line; 20 is shock wave outlet molded line; 21 for putting the osculating cone of 25 correspondences; 22 for putting the subpoint of osculating conic node in shock wave outlet of 25 correspondences; 23 is point 22 and the intersection point putting 25 lines and waverider forebody derived upper surface trailing edge line; Point 24 is the intersection point of point 22 and point 25 lines and waverider forebody derived lower surface trailing edge line; 25 is the at a point on shock wave outlet molded line; 26 be a little 25 osculating plane; Curve 27-28,28-29,29-29 ＇, 28 ＇-29 ＇ and 27 ＇-28 ＇ form shock wave outlet molded line 20; 30 be a little 25 the circle of curvature;
Fig. 3 is streamlined impeller schematic diagram in osculating face;
Wherein, 31 is the osculating conic node putting 25 correspondences; 32 for putting the leading edge point of 25 correspondences;
Detailed description of the invention
The invention provides a kind of osculating flow field waverider forebody derived method of designing of the variable wall surface pressure regularity of distribution, comprise the following steps:
Step S1, the different curve of given three kinds of wall pressure distribution rules, be respectively the curve that the constant curve of curve, wall pressure that wall pressure raises and wall pressure reduce, using three curves as gyro-rotor bus, design three kinds of different gyro-rotors, solve the supersonic speed axisymmetric flow field around these three kinds of gyro-rotors respectively, and will the flow field that obtains be solved as the different benchmark flow field of three kinds of wall pressure distribution rules.
(1) given linear portion 1-2-6, one end points of linear portion is point 1, another end points of linear portion is point 6, point 2 is a bit in the middle of linear portion, and point 1 is positioned in x-axis, and the angle of linear portion 1-2-6 and x-axis is 17, angle 17 equals the angle 13 of linear portion at point 6 place, using linear portion 1-2-6 as gyro-rotor bus, make its around x-axis 360 ° rotate formed straight circular cone, become straight circular cone to be the constant gyro-rotor of wall pressure;
(2) directly over point 6 given 1: 5, design one outer dilation curve 2-5 between point 2 and point 5, the outer dilation curve 2-5 of the present invention is the curve of parabolic, curve 2-5 and straight line 1-2 is continuous in point 2 place first derivative, and in conjunction with the coordinate of 2 and 5, formula (1) is utilized can uniquely to determine curve 2-5, the tangent line of curve 2-5 at point 5 place and x-axis angle are 12, angle 12 is greater than angle 17, rotated to be formed around x-axis 360 ° by curve 1-2-5 and extend out a formula curved surface and bore, institute becomes outer expanding curved surface cone to be the gyro-rotor of wall pressure rising;
y＝ax
2+bx+c(1)
(3) immediately below point 6 given 1: 7, expansion curve 2-7 in design one between point 2 and point 7, in the present invention, expansion curve 2-7 is the curve of parabolic, curve 2-7 and straight line 1-2 is continuous in point 2 place first derivative, and in conjunction with the coordinate of 2 and 7, utilize formula (1) can uniquely determine curve 2-7, curve 2-7 is 14 at 7 tangent lines located and x-axis angle, and angle 14 is less than angle 17; By curve 1-2-7 around x-axis 360 ° rotate is formed inner intumescence type curved surface bore, institute become inner intumescence type curved surface cone be wall pressure reduction gyro-rotor;
(4) given inlet flow conditions (Mach number, static pressure and static temperature), employing has revolves characteristic line method, solve the supersonic speed axisymmetric flow field around these three kinds of gyro-rotors, obtain three kinds of benchmark flow fields, be defined as respectively: the benchmark flow field that the benchmark flow field that wall pressure is constant, wall pressure raise and the benchmark flow field that wall pressure reduces.Have and revolve the known technology that characteristic line method is this area, specifically can see " " gas kinetics ", the left Crow of M.J., J.D. Huffman, National Defense Industry Press, p138-195 in 1984 ".
Wherein, in the benchmark flow field that wall pressure raises, carry out the waverider-derived that streamlined impeller obtains there is high voltage rise ratio, curve 3-4-8 in the streamline corresponding diagram 1 of following the trail of in the flow field that wall pressure raises; In the benchmark flow field that wall pressure reduces, carry out the waverider-derived that streamlined impeller obtains there is high lift-drag ratio, the curve 3-4-10 in the streamline corresponding diagram 1 of following the trail of in the flow field that wall pressure reduces.
(note: voltage rise ratio=waverider forebody derived bottom transverse sectional pressure/incoming-flow pressure)
Obtain in step S1 three rotational symmetry benchmark flow fields are assembled into three-dimensional references flow field by step S2, application osculating principle;
First, shock wave outlet molded line is designed.
Shock wave outlet molded line is symmetrical with its center line, shock wave is exported molded line and be divided into five sections, be respectively waverider forebody derived left section of 27-28, waverider forebody derived left transition phase 28-29, inlet mouth position section 29-29 ＇, waverider forebody derived right transition phase 28 ＇-29 ＇, waverider forebody derived right section of 27 ＇-28 ＇, wherein waverider forebody derived left section of 27-28 and waverider forebody derived right section of 27 ＇-28 ＇ is symmetrical, and waverider forebody derived left transition phase 28-29 and waverider forebody derived right transition phase 28 ＇-29 ＇ is symmetrical.Left for waverider forebody derived section 27-28 and waverider forebody derived right section of 27 ＇-28 ＇ is referred to as waverider forebody derived two ends section, left for waverider forebody derived transition phase 28-29 and waverider forebody derived right transition phase 28 ＇-29 ＇ is referred to as waverider forebody derived transition phase, when therefore designing shock wave outlet molded line, only need designs waverider forebody derived two ends section 27-28 and 27 ＇-28 ＇, waverider forebody derived transition phase 28-29 and 28 ＇-29 ＇, inlet mouth position section 29-29 ＇;
As shown in Figure 2, shock wave is exported molded line and be divided into three sections to design, these three sections is waverider forebody derived two ends section 27-28 and 27 ＇-28 ＇, waverider forebody derived transition phase 28-29 and 28 ＇-29 ＇, inlet mouth position section 29-29 ＇ respectively.Left section of given waverider forebody derived, the left transition phase of waverider forebody derived, inlet mouth position section, the coordinate of point of connection between the right transition phase of waverider forebody derived and right section of waverider forebody derived, i.e. set point 27, point 28, point 29, the coordinate putting 27 ＇, put 28 ＇ and point 29 ＇.Inlet mouth position section 29-29 ＇ is designed to horizontal linear, wavefront body two ends section 27-28 and 27 ＇-28 ＇ and waverider forebody derived transition phase 28-29 and 28 ＇-29 ＇ is all designed to quartic curve, each section of curve point of connection place left and right sides second derivative is identical to ensure continual curvature between section and section, and the curve namely designed is continuous in point 28,29,28 ＇, 29 ＇ place second derivatives.Utilize quartic curve equation and formula (2), uniquely can be determined the coefficient in quartic curve equation by the coordinate of point of connection and point of connection second derivative continuously, and then determine wavefront body two ends section and quartic curve corresponding to waverider forebody derived transition phase.
y＝ax
4+bx
2+c(2)
Wherein, the benchmark flow field of design Waverider two ends section 27-28 and 27 ＇-28 ＇ is the benchmark flow field that the wall pressure defined in S1 reduces, and is used for improving waverider forebody derived 1ift-drag ratio; The benchmark flow field that design inlet mouth position section 29-29 ＇ adopts the wall pressure distribution defined in S1 to raise, to ensure the requirement of inlet mouth height voltage rise ratio; The benchmark flow field that the wall pressure defined in waverider forebody derived transition phase 28-29 and 28 ＇-29 ＇ employing S1 is constant;
As shown in Figure 2, carry out discrete to shock wave outlet molded line 20, on shock wave outlet molded line, every 5mm gets a point, can ensure that the streamline that difference produces can form smooth surface; 1: 25 is got arbitrarily in the discrete rear acquired discrete point of shock wave outlet molded line, the circle of curvature 30 of this point must be, the circle of curvature 30 is the osculating circle of osculating curved surface cone in outlet of a little 25 correspondences, the axis of this osculating curved surface cone is parallel with X-axis, and the plane crossing point 25 and osculating curved surface axis of cone line is osculating plane 26; Point 22 is the center of circle of the circle of curvature 30;
As fruit dot 25 is positioned at waverider forebody derived transition phase, then the benchmark flow field that in selection step S1, wall pressure is constant is as the osculating face flow field crossing point 25; As fruit dot 25 is positioned at Waverider two ends section, then select the benchmark flow field of wall pressure reduction in step S1 as the osculating face flow field crossing point 25; As fruit dot 25 is positioned at inlet mouth position section, then select the benchmark flow field of wall pressure distribution rising in step S1 as the osculating face flow field crossing point 25; Select the benchmark flow field of corresponding wall pressure distribution as the osculating flow field of this some correspondence to discrete rear each the got point of shock wave outlet molded line according to shock wave section residing separately using this rule.Point 25 shown in Fig. 2 is positioned at the left transition phase 28-29 of waverider forebody derived, and therefore, the benchmark flow field that in selection step S1, wall pressure is constant is as the osculating face flow field crossing point 25.
Step S3, the given drop shadow curve of waverider forebody derived costa in bottom, according to the shock wave outlet molded line of step S2, use streamlined impeller method, generate osculating flow field waverider forebody derived aerodynamic configuration in each osculating plane of step S2.
(1) the first given drop shadow curve of waverider forebody derived costa in bottom, i.e. Waverider upper surface trailing edge line.Enough close discrete point is taken out with exporting the first-class spacing of molded line from the shock wave of step S2 design, general every 5mm gets a point, can ensure that the streamline that difference produces can form smooth surface, specifically can see fourth peak. hypersonic glide-two-stage of cruising rider method of designing research [D]. Changsha: defense science and technology university (master) .2012.
(2) as shown in Figures 2 and 3,1: 25 is got arbitrarily in the discrete rear acquired discrete point of shock wave outlet molded line, the circle of curvature 30 of a little 25 was obtained by point 25, the circle of curvature crossing at 25 is 25 the corresponding osculating circles of osculating cone shock wave in outlet, and the axis being parallel of osculating cone is in x-axis (i.e. free streamlines).Point 22 was the center of circle of the circle of curvature 30 of a little 25, was also osculating conic node 31 (Fig. 3) subpoint in shock wave outlet of point 25 correspondences.25 points, 22 and 31 formed a little 25 osculating face 26.The line of point 25 and point 22 hands over Waverider upper surface trailing edge line in point 23, does the straight line being parallel to x-axis hand over osculating to bore shock wave in point 32 by point 23, point 32 be also a little 25 osculating face in the leading edge point of correspondence.Carry out streamlined impeller backward to shock wave outlet from leading edge point 32, obtain trailing edge point 24, leading edge point and the curve 32-24 that trailing edge point is linked to be are a little 25 corresponding lower surface streamlines, will put 32 and be connected with straight line with point 23, and obtain the upper surface streamline putting 25 correspondences; The discrete rear acquired all discrete points of shock wave outlet molded line are adopted to the point on the leading edge point obtained in the same way in respective osculating face, Waverider lower surface streamline, Waverider upper surface streamline and lower surface trailing edge line.
(3) a series of leading edge point smooth connection forms the costa of Waverider; A series of upper surface streamline forms Waverider upper surface; A series of lower surface streamline forms Waverider lower surface; Point smooth connection on a series of trailing edge line forms Waverider lower surface trailing edge line; Waverider forebody derived aerodynamic configuration is formed by costa, trailing edge line and Waverider lower surface.
Claims (5)
1., based on an osculating flow field waverider forebody derived method of designing for the variable wall surface pressure regularity of distribution, it is characterized in that, comprise the following steps:
S1, the different curve of given three kinds of wall pressure distribution rules, be respectively the curve that the constant curve of curve, wall pressure that wall pressure raises and wall pressure reduce, using three curves as gyro-rotor bus, design three kinds of different gyro-rotors, solve the supersonic speed axisymmetric flow field around these three kinds of gyro-rotors respectively, and will the flow field that obtains be solved as the different benchmark flow field of three kinds of wall pressure distribution rules;
S2, performance requriements according to waverider forebody derived, shock wave being exported molded line is divided into three sections to design, and ensure the junction continual curvature of molded line at every section of curve of design, namely the second derivative of curve is continuous, then according to designed shock wave outlet molded line, application osculating principle carries out flow field calculation at each osculating plane, all osculating plane group of flow fields synthesis three-dimensional references flow fields;
S3, the given drop shadow curve of waverider forebody derived costa in bottom, according to the shock wave outlet molded line of step S2, use streamlined impeller method, generate osculating flow field waverider forebody derived aerodynamic configuration in each osculating plane of step S2.
2. the osculating flow field waverider forebody derived method of designing based on the variable wall surface pressure regularity of distribution according to claim 1, it is characterized in that, the concrete grammar of step S1 is:
The given linear portion 1-2-6 of S1.1, one end points of linear portion is point 1, another end points of linear portion is point 6, point 2 is a bit in the middle of linear portion, and point 1 is positioned in x-axis, and the angle of linear portion 1-2-6 and x-axis is 17, angle 17 equals the angle 13 of linear portion at point 6 place, using linear portion 1-2-6 as gyro-rotor bus, make its around x-axis 360 ° rotate formed straight circular cone, become straight circular cone to be the constant gyro-rotor of wall pressure;
S1.2 is directly over point 6 given 1: 5, design one outer dilation curve 2-5 between point 2 and point 5, curve 2-5 and straight line 1-2 is continuous in point 2 place first derivative, and in conjunction with the coordinate of 2 and 5, can uniquely determine curve 2-5, the tangent line of curve 2-5 at point 5 place and x-axis angle are 12, and angle 12 is greater than angle 17, rotated to be formed around x-axis 360 ° by curve 1-2-5 and extend out a formula curved surface and bore, institute becomes outer expanding curved surface cone to be the gyro-rotor of wall pressure rising;
S1.3 is immediately below point 6 given 1: 7, expansion curve 2-7 in design one between point 2 and point 7, curve 2-7 and straight line 1-2 is continuous in point 2 place first derivative, and in conjunction with the coordinate of 2 and 7, can uniquely determine curve 2-7, curve 2-7 is 14 at 7 tangent lines located and x-axis angle, and angle 14 is less than angle 17; By curve 1-2-7 around x-axis 360 ° rotate is formed inner intumescence type curved surface bore, institute become inner intumescence type curved surface cone be wall pressure reduction gyro-rotor;
The given inlet flow conditions of S1.4, employing has revolves characteristic line method, solve the supersonic speed axisymmetric flow field around these three kinds of gyro-rotors, obtain three kinds of benchmark flow fields, be defined as respectively: the benchmark flow field that the benchmark flow field that wall pressure is constant, wall pressure raise and the benchmark flow field that wall pressure reduces.
3. the osculating flow field waverider forebody derived method of designing based on the variable wall surface pressure regularity of distribution according to claim 2, is characterized in that, outer dilation curve 2-5 and interior expansion curve 2-7 is the curve of parabolic.
4. the osculating flow field waverider forebody derived method of designing based on the variable wall surface pressure regularity of distribution according to claim 3, it is characterized in that, the concrete grammar of described S2 is:
S2.1 designs shock wave outlet molded line;
Shock wave outlet molded line is symmetrical with its center line, shock wave is exported molded line and be divided into five sections, be respectively left section of waverider forebody derived, the left transition phase of waverider forebody derived, inlet mouth position section, the right transition phase of waverider forebody derived, right section of waverider forebody derived, wherein left section of waverider forebody derived and right section of waverider forebody derived are symmetrical, the left transition phase of waverider forebody derived and the right transition phase of waverider forebody derived are symmetrical, left for waverider forebody derived section and right section of waverider forebody derived are referred to as waverider forebody derived two ends section, left for waverider forebody derived transition phase and the right transition phase of waverider forebody derived are referred to as waverider forebody derived transition phase;
Left section of given waverider forebody derived, the left transition phase of waverider forebody derived, inlet mouth position section, the coordinate of point of connection between the right transition phase of waverider forebody derived and right section of waverider forebody derived, inlet mouth position section is designed to horizontal linear, wavefront body two ends section and waverider forebody derived transition phase are designed to quartic curve, each section of curve point of connection place left and right sides second derivative is identical to ensure continual curvature between section and section, and the point of connection namely between waverider forebody derived two ends section and waverider forebody derived transition phase, point of connection place second derivative between waverider forebody derived transition phase and inlet mouth position section are continuous;
Utilize quartic curve equation, uniquely can be determined the coefficient in quartic curve equation by the coordinate of point of connection and point of connection second derivative continuously, and then determine wavefront body two ends section and quartic curve corresponding to waverider forebody derived transition phase; Wherein quartic curve equation is as follows:
y＝ax
4+bx
2+c
Wherein, the benchmark flow field designing Waverider two ends section is the benchmark flow field that the wall pressure defined in S1 reduces; The benchmark flow field that design inlet mouth position section adopts the wall pressure distribution defined in S1 to raise; The benchmark flow field that the wall pressure defined in waverider forebody derived transition phase employing S1 is constant;
S2.2 obtains three-dimensional references flow field;
Carry out discrete to shock wave outlet molded line, on shock wave outlet molded line, every 5mm gets a point, can ensure that the streamline that difference produces can form smooth surface; 1: 25 is got arbitrarily in the discrete rear acquired discrete point of shock wave outlet molded line, the circle of curvature 30 of this point must be, the circle of curvature 30 is the osculating circle of osculating curved surface cone in outlet of a little 25 correspondences, the axis of this osculating curved surface cone is parallel with X-axis, cross a little 25 and the plane of osculating curved surface axis of cone line be osculating plane 26, point 22 is the center of circle of the circle of curvature 30;
As fruit dot 25 is positioned at waverider forebody derived transition phase, then the benchmark flow field that in selection step S1, wall pressure is constant is as the osculating face flow field crossing point 25; As fruit dot 25 is positioned at Waverider two ends section, then select the benchmark flow field of wall pressure reduction in step S1 as the osculating face flow field crossing point 25; As fruit dot 25 is positioned at inlet mouth position section, then select the benchmark flow field of wall pressure distribution rising in step S1 as the osculating face flow field crossing point 25; Select the benchmark flow field of corresponding wall pressure distribution as the osculating flow field of this some correspondence to discrete rear each the got point of shock wave outlet molded line according to shock wave section residing separately using this rule.
5. the osculating flow field waverider forebody derived method of designing based on the variable wall surface pressure regularity of distribution according to claim 3, it is characterized in that, the concrete grammar of described S3 is:
The first given drop shadow curve of waverider forebody derived costa in bottom of S3.1, i.e. Waverider upper surface trailing edge line; Take out enough close discrete point with exporting the first-class spacing of molded line from the shock wave of step S2 design, on shock wave outlet molded line, every 5mm gets a point, to ensure that the streamline that difference produces can form smooth surface;
S3.2 gets arbitrarily 1: 25 in the discrete rear acquired discrete point of shock wave outlet molded line, the circle of curvature 30 of a little 25 was obtained by point 25, the circle of curvature crossing at 25 is the osculating circle of osculating cone shock wave in outlet of a little 25 correspondences, the axis being parallel of osculating cone is in x-axis, point 22 was the center of circle of the circle of curvature 30 of a little 25, and point 22 is also the subpoint of osculating conic node 31 in shock wave outlet of point 25 correspondences; Point 25, point 22 and point 31 formed the osculating face 26 of a little 25; The line of point 25 and point 22 hands over Waverider upper surface trailing edge line in point 23, and the straight line being made to be parallel to x-axis by point 23 hands over osculating to bore shock wave in point 32, point 32 be also a little 25 osculating face in the leading edge point of correspondence; Carry out streamlined impeller backward to shock wave outlet from leading edge point 32, obtain trailing edge point 24, leading edge point and the curve 32-24 that trailing edge point is linked to be are a little 25 corresponding lower surface streamlines, will put 32 and be connected with straight line with point 23, and obtain the upper surface streamline putting 25 correspondences; The discrete rear acquired all discrete points of shock wave outlet molded line are adopted to the point on the leading edge point obtained in the same way in respective osculating face, Waverider lower surface streamline, Waverider upper surface streamline and lower surface trailing edge line;
The a series of leading edge point smooth connection of S3.3 forms the costa of Waverider; A series of upper surface streamline forms Waverider upper surface; A series of lower surface streamline forms Waverider lower surface; Point smooth connection on a series of trailing edge line forms Waverider lower surface trailing edge line; Waverider forebody derived aerodynamic configuration is formed by costa, trailing edge line and Waverider lower surface.
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| CN112765725B (en) * | 2020-12-30 | 2023-04-07 | 四川京航天程科技发展有限公司 | Analytic Riemann resolving method for multi-dimensional Euler equation |
| CN112949199A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Method and system for optimizing longitudinal stability of power waverider |
| CN112948976A (en) * | 2021-03-15 | 2021-06-11 | 中国科学院力学研究所 | Plane front edge lifting body front edge line optimization method and system and lifting body |
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