CN109598062B - Design method of osculating flow field waverider with variable wall surface pressure distribution rule - Google Patents
Design method of osculating flow field waverider with variable wall surface pressure distribution rule Download PDFInfo
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Abstract
The invention provides a design method of osculating flow field waverider with variable wall pressure distribution rule, which comprises the steps of firstly setting the width W of a given waverider configuration, the rear edge line of the upper surface and the shock wave outlet molded line, then designing a revolving body bus of an axisymmetric reference flow field, then dispersing the shock wave outlet molded line into a plurality of points, and solving osculating plane corresponding to each discrete point and axisymmetric reference flow field corresponding to each osculating plane. In an axisymmetric reference flow field corresponding to each osculating plane, a leading edge point is obtained by a free flow line method, and then a flow line is traced from the leading edge point to the rear edge point, so that a flow line in each osculating plane is obtained. Finally, generating the osculating flow field waverider pneumatic configuration with variable wall surface pressure distribution rule. The invention widens the design freedom degree of the wave rider in the spanwise direction, and can design the axisymmetric flow field with continuously changed wall surface pressure distribution rule as the reference flow field in different osculating planes according to the performance requirements of the wave rider at different positions in the spanwise direction.
Description
Technical Field
The invention relates to the technical field of aerodynamic shape design of hypersonic aircrafts, in particular to an improved design method of osculating flow field waverider with variable wall pressure distribution rule.
Background
The concept of the waverider is firstly proposed in 1950, the core of the design method of the waverider configuration is the selection of a reference flow field, different reference flow fields correspond to different design methods, and the existing design methods comprise a wedge guide method, a cone guide method and a osculating method (comprising an osculating cone method, an osculating axisymmetric method and an osculating flow field method). The method is characterized in that on the basis of a osculating cone and osculating axisymmetric design method, any axisymmetric flow field is used as a reference flow field of each osculating plane, different axisymmetric flow fields can be selected from different osculating planes as the reference flow fields, and the osculating flow field method greatly widens the spanwise design freedom of the waverider.
The distribution rule of the flow direction wall surface pressure of the axisymmetric reference flow field reference body is an important factor influencing the appearance and the performance of the wave multiplier, the increase of the wall surface pressure of the reference flow field is beneficial to improving the internal loading capacity and the pre-compressed air flow characteristic of the wave multiplier, and the decrease of the wall surface pressure of the reference flow field is beneficial to improving the lift-drag ratio characteristic and the drag reduction design of the wave multiplier. Therefore, when the osculating flow field theory is applied to design the waverider, the design and optimization space of the waverider can be expanded by selecting the reference flow field with different wall surface pressure distribution rules in the osculating plane of the waverider in different spreading positions according to the design requirements on the internal loading capacity and the lift-drag ratio of the aircraft, and the waverider configuration with higher practicability can be generated.
The invention patent application with publication number CN105329462A and publication date 2016, 02 and 17 discloses a method for designing a osculating flow field waverider precursor based on a variable wall pressure distribution rule. The method comprises the steps of designing a shock wave outlet molded line in a segmented mode, designing an axial symmetric flow field with raised wall surface pressure at the middle position in the spanwise direction as a reference flow field, designing axial symmetric flow fields with lowered wall surface pressure at two ends in the spanwise direction as reference flow fields, and designing a reference flow field with constant wall surface pressure at the part between the two positions. The design method realizes that the axisymmetric reference flow field with different wall surface pressure distribution rules is designed in the osculating plane of different spanwise areas, but the method has the defect that the wall surface pressure distribution rules of the reference flow field in different spanwise areas cannot be continuously changed. The improved design method provided by the invention can solve the defect.
Fig. 1 is a schematic diagram of parameterization definition of a revolving body bus of an axisymmetric reference flow field, wherein a curve 0-1-2 is a revolving body bus, 0-1 is a straight line segment of the revolving body bus, 1-2 is a curved line segment of the revolving body, 3 is an inclination angle of a point 1 on the revolving body bus, 4 is an inclination angle of a point 2 on the revolving body bus, 5 is the length of the straight line segment of the revolving body bus, and 6 is the length of the curved line segment of the revolving body bus. When the inclination angle 3 of the point 1 is larger than the inclination angle 4 of the point 2, the wall surface pressure of the reference flow field is reduced; when the inclination angle 3 of the point 1 is equal to the inclination angle 4 of the point 2, the wall surface pressure of the reference flow field is constant; when the inclination angle 3 of the point 1 is smaller than the inclination angle 4 of the point 2, the wall surface pressure of the reference flow field rises.
As shown in FIG. 1, input parameters of a straight line segment 0-1 of a revolving body generatrix of an axisymmetric reference flow field are given, and comprise a length 5 of the straight line segment 0-1 and an inclination angle 3 of a point 1. The curve equation for a given rotor generatrix curve segment 1-2 is as follows:
F wall ＝a 12 x 2 +b 12 x+c 12
the coefficients in the equation are solved by geometric relations to obtain:
a 12 ＝(T 2 -T 1 )/[2(x 2 -x 1 )]
b 12 ＝(x 2 ×T 1 -x 1 ×T 2 )/(x 2 -x 1 )
in the equation, T 2 ＝tan(δ 2 )，T 1 ＝tan(δ 1 )，y 1 ＝y 0 +T 1 ×(x 1 -x 0 )。
Wherein, delta 1 Represents the angle of inclination, delta, of the wall point 1 2 Represents the angle of inclination of the wall point 2, (x) 0 ，y 0 ) A coordinate value (x) representing wall point 0 1 ，y 1 ) Coordinate values, x, representing wall points 1 2 The x-direction coordinate value of the wall point 2 is shown.
Fig. 2 is a schematic cross-sectional view of the bottom of a wave rider in a osculating flow field wave rider precursor design method based on a variable wall pressure distribution rule in the prior art, wherein curves 7-8, 8-9, 9-9 ', 9 ' -8 ', 8 ' -7 ' form a shock wave outlet profile, i.e., points 8, 9 ', 8 ' divide the shock wave outlet profile into five sections; the shock wave outlet molded line is divided into two end sections, a transition section and an air inlet channel inlet position section, and then a wall surface pressure distribution rule of a reference flow field in a corresponding osculating plane is designed according to the positions of discrete points on the shock wave shaped line so as to realize the osculating flow field design idea. In the existing method, an axisymmetric reference flow field with raised, constant and lowered wall pressure is respectively selected in different areas according to a shock wave molded line after sectional design, but the wall pressure distribution rule of the reference flow field in adjacent osculating planes cannot realize continuous change from raising to lowering.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a design method of osculating flow field waverider with variable wall surface pressure distribution rule. The invention solves the technical problem that the osculating flow field method in the prior art cannot adopt an axisymmetric reference flow field with continuously changed wall surface pressure distribution rule in each osculating plane when designing the waverider, so that the freedom of designing the osculating flow field waverider in the shape and the extension direction is limited.
In order to realize the technical purpose of the invention, the following technical scheme is adopted:
the design method of osculating flow field waverider with variable wall surface pressure distribution rule includes the following steps:
s100: the method comprises the steps of giving the width W of a wave multiplier configuration, giving a projection molded line (namely an upper surface rear edge line) of a front edge line of the wave multiplier on the bottom section of the wave multiplier, giving a shock wave outlet molded line, and giving the height H between the upper surface rear edge line and the shock wave outlet molded line. Wherein the given upper surface trailing edge line and the shock wave outlet profile are bilaterally symmetrical about respective centerlines.
S200: designing a revolving body generatrix of the axisymmetric reference flow field.
The revolving body generatrix of the axisymmetric reference flow field is formed by connecting a section of straight line segment and a section of curved line segment.
And (3) giving input parameters of a straight line segment of a revolving body generating line of the axisymmetric reference flow field, wherein the input parameters comprise the length and the inclination angle of the straight line segment.
A curve equation of a curve section of a revolving body bus of the axisymmetric reference flow field is given, and a change rule curve delta of the inclination angle of a wall surface point (namely a point on the curve section of the revolving body bus) along the spanwise direction of the waverider is designed 2 (z) is represented by formula (1):
δ 2 (z)＝m*z 2 +n(n＞0) (1)
wherein, delta 2 Indicating the inclination of a design wall pointThe angle, z is the position coordinate of the spreading direction of the wave multiplier, and m and n represent the coefficients of the change curve of the inclination angle; m and n can be selected according to design requirements. m is a positive number and represents delta 2 Increasing curve along the spanwise direction, m being negative number represents delta 2 The curve is a decreasing curve along the spanwise direction, n represents the inclination angle of the wall surface point of the datum flow field datum body corresponding to the middle section of the wave body in the spanwise direction, and therefore n is larger than 0.
S300: dispersing the shock wave outlet molded line into a plurality of points, solving the osculating plane corresponding to each discrete point, and solving the delta corresponding to each discrete point according to the formula (1) 2 And (z) solving an axisymmetric reference flow field corresponding to each osculating plane by combining given inflow conditions.
S400: in the axisymmetric reference flow field corresponding to each osculating plane obtained by the solution in S300, a leading edge point is obtained by a free flow line method, and then a flow line is traced from the leading edge point backward to a trailing edge point, thereby obtaining a flow line in each osculating plane.
S500: and finally, the upper surface, the lower surface and the bottom surface jointly form a variable wall surface pressure distribution rule osculating flow field waverider pneumatic configuration.
In the invention, the implementation method of S300 is as follows:
s310: uniformly dispersing the shock wave outlet profile into a plurality of points;
s320: optionally selecting a point i from discrete points on the shock wave outlet molded line to obtain a curvature circle tangent to the point i with the shock wave outlet molded line and the center of the curvature circle, wherein the plane of the curvature circle is the osculating plane corresponding to the point i, and the radius of the curvature circle is the radius R of the original reference flow field corresponding to the osculating plane corresponding to the point i i ；
S330: coordinate Z of point i in Z direction i Substituting the formula (1) to obtain the inclination angle delta of the wall surface point corresponding to the point i 2 (z i ) And in conjunction with a given incoming horseHerz number, incoming flow static pressure and incoming flow static pressure, solving an axisymmetric reference flow field corresponding to the discrete point i, wherein the shock wave radius of the reference flow field is R si ；
S340: with R i /R si Scaling the reference flow field in the step S320 to obtain a real reference flow field corresponding to the discrete point i;
s350: and (4) repeating the steps S320-S340 for all the discrete points on the shock wave outlet molded line respectively to obtain a osculating plane and a reference flow field corresponding to each discrete point on the shock wave outlet molded line.
The implementation method of S400 is as follows: for any point i in discrete points on the shock wave outlet molded line, in the axisymmetric reference flow field corresponding to the point i obtained by solving in the S300, a connecting line between the point i and the circle center of the curvature circle corresponding to the point i intersects with the upper surface rear edge line at one point, the intersection point is a point on the upper surface rear edge molded line, and a front edge point corresponding to the point i is obtained by solving in the axisymmetric reference flow field corresponding to the point i according to a free streamline method; and (4) tracing the streamline from the front edge point corresponding to the point i, namely obtaining the rear edge point corresponding to the point i, wherein the front edge point corresponding to the point i and the rear edge point corresponding to the point i form the streamline in the osculating plane corresponding to the point i. By analogy, the solution is carried out in the axisymmetric reference flow field corresponding to the discrete point on each shock wave outlet molded line, so that a series of front edge points, rear edge points and flow lines can be obtained, the front edge points are in smooth connection to form a front edge line of the variable wall surface pressure distribution rule osculating flow field waverider, and the rear edge points are in smooth connection to form a lower surface rear edge molded line of the variable wall surface pressure distribution rule osculating flow field waverider.
Compared with the prior art, the invention can produce the following technical effects:
the improved design method of the osculating flow field waverider with the variable wall surface pressure distribution rule widens the design freedom of the spreading direction of the waverider, so that the axisymmetric flow field with the continuously variable wall surface pressure distribution rule can be designed as the reference flow field in different osculating planes according to the performance requirements of the waverider at different positions in the spreading direction. The method ensures that the designed osculating flow field waverider appearance has more practicability.
Drawings
FIG. 1 is a schematic diagram of a parametric definition of a reference body generatrix of an axisymmetric reference flow field;
FIG. 2 is a schematic bottom cross-sectional view of a osculating flow field waverider based on a variable wall pressure distribution rule in the prior art;
fig. 3 is a schematic diagram of the definition of the basic geometric profile of the bottom section of the osculating flow field waverider with a variable wall pressure distribution rule, wherein 10 is a shock wave outlet profile of the osculating flow field waverider with a variable wall pressure distribution rule, 11 is an upper surface trailing edge profile, 12 is the width of the waverider, 13 is the intersection point of the upper surface trailing edge and the shock wave outlet profile, and 14 is the midpoint of the upper surface trailing edge;
FIG. 4 is a diagram showing the tilt angle delta of the datum wall surface point of the axisymmetric datum flow field 2 A change rule curve along the expansion direction of the waverider;
FIG. 5 is a schematic bottom cross-sectional view of a variable wall pressure distribution law osculating flow field wave multiplier of the present invention, wherein a point 16 is any discrete point on a shock wave outlet profile, 21 is a curvature circle passing through the point 16, 19 and 20 are respectively the center and radius of the curvature circle, AA ' is an osculating plane passing through the point 16, 18 is an intersection point of a straight line 16-19 in the osculating plane AA ' and a top surface trailing edge line, 17 is a trailing edge point obtained by solving in the osculating plane AA ', and 15 is a trailing edge osculating line of the variable wall pressure distribution law osculating flow field wave multiplier;
FIG. 6 shows the angle of inclination delta 2 (z i ) The axial symmetry reference flow field 22 is the bottom radius of the axial symmetry reference flow field;
FIG. 7 is a schematic view of any osculating plane and a scaled axisymmetric reference flow field in the osculating plane, wherein 23 is a leading edge point corresponding to the osculating plane;
FIG. 8 is an isometric view of a variable wall pressure distribution law osculating flow field waverider of the present invention;
FIG. 9 is a three-view of osculating flow field waverider with variable wall pressure distribution rule of the present invention;
fig. 10 is a pressure distribution cloud chart of the bottom cross section of the variable wall pressure distribution rule osculating flow field waverider of the present invention, wherein the black dotted line is the design shape and position of the shock wave outlet profile;
fig. 11 is a definition of osculating planes of osculating flow field wavelets with variable wall surface pressure distribution rules and a pressure distribution cloud chart of each osculating plane, a) the definition of osculating planes; b) A pressure distribution cloud picture of the osculating plane 1; c) A pressure distribution cloud picture of the kiss-cut plane 2; d) A pressure distribution cloud picture of the kiss-cut plane 3; e) A pressure distribution cloud picture of the kiss-cut plane 4; f) Pressure distribution cloud picture of osculating plane 5.
Detailed Description
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
The invention provides a design method of a variable wall pressure distribution rule osculating flow field waverider, which is an improvement on the existing design method of the variable wall pressure distribution rule osculating flow field waverider precursor, and further improves the unfolding design freedom of the waverider, so that the designed waverider appearance has higher practicability.
Referring to fig. 3, the design method of osculating the flow field waverider with a variable wall pressure distribution rule comprises the following steps:
s100: given the width W and basic geometric profile of the waverider configuration. Wherein, the given basic geometric profile comprises a projection profile (namely an upper surface back edge line) of a wave rider leading edge line on the bottom section of the wave rider and a shock wave outlet profile.
As shown in fig. 3, the width 12 of the waverider configuration is given. And giving an upper surface rear edge line 11 and a shock wave outlet molded line 10 of the wave multiplying body, wherein the upper surface rear edge line 11 and the shock wave outlet molded line 10 are bilaterally symmetrical by respective center lines, and giving a height H between the upper surface rear edge line and the shock wave outlet molded line. The curve equation of the upper surface trailing edge line 11 is shown in formula (2), and the curve equation of the shock wave exit profile 10 is shown in formula (3).
y＝a×z 3 +b×z 2 +c×z+d (2)
Coefficient a = y of (3) in equation 13 /(z 13 -L s ) 4 ，L s ＝0.1*W，z 13 ＝0.5*W，y 13 =0.1 × h. The coefficients d = H, c = tan (T) in equation (2) 14 )，b＝(3.0*(y 13 -d-c*z 13 )-z 13 *tan(T 13 )+z 13 *c)/z 13 2 ，a＝(y 13 -d-c*z 13 -b*z 13 2 )/z 13 3 . Wherein (y) 13 ,z 13 ) Is a coordinate value of the intersection point 13 of the upper surface trailing edge line and the shock wave outlet profile line, T 13 The inclination angle at the intersection point 13 of the upper surface rear edge line and the shock wave outlet molded line is shown; t is a unit of 14 Is the angle of inclination at the midpoint 14 of the upper surface trailing edge line.
S200: designing a revolving body generatrix of the axisymmetric reference flow field.
Input parameters of a straight line segment of a revolving body bus of the axisymmetric reference flow field are given, and the input parameters comprise the length and the inclination angle of the straight line segment. A curve equation of a revolving body generatrix curve section of the axisymmetric reference flow field is given, and an inclination angle delta of a wall surface point is designed 2 The curve of the change rule along the spanwise direction of the waverider is shown in fig. 4.
As shown in FIG. 5, the present invention provides a method for expressing a curve δ representing a variation law of a tilt angle of a wall point in a spanwise direction in an incremental parabolic manner (as shown in equation (1)) 2 And (z), so that the designed waverider is ensured to select an axisymmetric reference flow field with reduced wall surface pressure in the osculating plane at the two ends in the spanwise direction, and select an axisymmetric reference flow field with increased wall surface pressure in the osculating plane at the middle position in the spanwise direction.
δ 2 (z)＝m*z 2 +n(n＞0) (1)
Wherein, delta 2 The inclination angle of the wall surface point of the reference flow field reference body is shown, z is the spanwise position coordinate of the waverider, and m and n are the inclination angles delta 2 A variable coefficient along a spanwise variation curve; m and n can be reasonably selected according to specific requirements. m is positive to denote delta 2 Increasing curve along the spanwise direction, m is negative and represents delta 2 A decreasing curve is formed along the spanwise direction, and n represents the spanwise direction of the multiplicative wave bodyThe inclined angle of the datum flow field datum wall surface point corresponding to the middle section is larger than 0. The present invention will be specifically described by taking m > 0 as an example.
S300: dispersing the shock wave outlet molded line into a plurality of points, solving the osculating plane corresponding to each discrete point, and calculating the osculating plane according to delta 2 (z) solving the delta corresponding to each discrete point by the curve equation 2 And then solving an axisymmetric reference flow field corresponding to each osculating plane by combining inflow conditions.
Preferably, S300 includes the steps of:
s310: as shown in fig. 6, the shock wave exit profile 10 is uniformly dispersed into a plurality of points, and it is ensured that the streamline generated at different points can form a smooth curved surface.
S320: randomly taking a point i from discrete points on the shock wave outlet molded line to obtain a curvature circle of the point i, the center of the curvature circle and the radius R of the original reference flow field corresponding to the osculating plane i ；
S330: coordinate Z of point i in Z direction i Substituting the formula (1) to obtain the inclination angle delta of the wall surface point corresponding to the point i 2 (z i ) And combining the given incoming flow Mach number, the incoming flow static temperature and the incoming flow static pressure to solve the axisymmetric reference flow field corresponding to the discrete point i, wherein the shock wave radius of the reference flow field is R si ；
S340: with R i /R si Scaling the reference flow field in the step S320 to obtain a real reference flow field corresponding to the discrete point i;
s350: and (5) repeating the steps S320-S340 for all discrete points on the shock wave outlet molded line respectively to obtain a osculating plane and a reference flow field corresponding to each discrete point on the shock wave outlet molded line.
Examples are as follows: as shown in fig. 5, by arbitrarily selecting one discrete point 16 from the discrete points on the shock wave exit profile 10, a circle of curvature 21 of the discrete point 16 is obtained, and further, a center 19 and a radius 20 of the circle of curvature 21 are obtained, and the radius 20 of the circle of curvature 21 is R i . The z-direction coordinate z of the discrete point 16 i Substituting the obtained values into the formula (1) to obtain the inclination angle delta of the datum body wall surface point of the datum flow field corresponding to the discrete point 16 2 (z i ). The reference flow field corresponding to the discrete point 16 can be obtained by combining the given incoming flow mach number, incoming flow static temperature and incoming flow static pressure, and the input parameters of the revolving body generatrix in S200. The reference flow field corresponding to the discrete point 16 is an axisymmetric reference flow field, as shown in fig. 6, the shock wave radius of the axisymmetric reference flow field is 22, and the radius 22 is R si . With R i /R si And scaling the axisymmetric reference flow field corresponding to the discrete point 16 for scaling, wherein the scaled flow field is the axisymmetric reference flow field corresponding to the discrete point 16.
By analogy, the solution is carried out on each discrete point on the shock wave outlet molded line, and the osculating plane corresponding to each discrete point and the corresponding axisymmetric reference flow field can be obtained.
S400: in the axisymmetric reference flow field corresponding to each osculating plane obtained by the solution in S300, a leading edge point is obtained by a free flow line method, and then a flow line is traced from the leading edge point to a trailing edge point backward, thereby obtaining a flow line in each osculating plane.
As shown in fig. 5, for any discrete point 16 on the shock wave exit profile 10, in the axisymmetric reference flow field corresponding to the osculating plane AA' corresponding to the discrete point 16 obtained by the solution in S300, a connecting line between the discrete point 16 and the point 16 intersects with the upper surface trailing edge line at a point 18, as shown in fig. 7. Knowing a point 18 on the rear edge line of the upper surface, solving according to a free flow line method in an axisymmetric reference flow field corresponding to the osculating plane AA', and obtaining a front edge point 23; the streamline tracing is carried out from the point 23, so that the trailing edge point 17 in the osculating plane AA 'can be obtained, and the streamline in the osculating plane AA' is formed by the point 23 and the point 17.
By analogy, the solution is carried out in the axisymmetric reference flow field corresponding to the discrete point on each shock wave outlet molded line, so that a series of front edge points, rear edge points and flow lines can be obtained, the front edge points are in smooth connection to form a front edge line of the variable wall surface pressure distribution rule osculating flow field waverider, and the rear edge points are in smooth connection to form a lower surface rear edge molded line of the variable wall surface pressure distribution rule osculating flow field waverider.
S500: and finally, the upper surface, the lower surface and the bottom surface jointly form a variable wall surface pressure distribution rule osculating flow field waverider pneumatic configuration.
As shown in fig. 8, the leading edge line and the upper surface trailing edge molded line obtained in step S400 are lofted to generate an upper surface of the variable wall pressure distribution law osculating flow field waverider, a series of flow lines generated in step S400 are lofted to generate a lower surface of the variable wall pressure distribution law osculating flow field waverider, and the upper surface trailing edge molded line and the lower surface trailing edge molded line generate a bottom surface of the variable wall pressure distribution law osculating flow field waverider. And finally, the upper surface, the lower surface and the bottom surface jointly form a variable wall surface pressure distribution rule osculating flow field waver pneumatic configuration. And finally, generating the flow field waverider pneumatic configuration according to the variable wall surface pressure distribution rule. Fig. 9 is a three-view of the wave-rider configuration of the designed osculating flow field with a variable wall pressure distribution rule.
The variable wall surface pressure distribution rule osculating flow field waverider can design the inclination angle delta of the bus end point of the revolving body according to the requirement of the flight mission on the waverider 2 The change rule curve of the wave multiplier realizes that the wall surface pressure distribution rule of the axisymmetric reference flow field in the adjacent osculating plane can be continuously changed, further widens the freedom degree of the wave multiplier in the spanwise design, and simultaneously ensures that the designed appearance has higher practicability.
The method of the present invention will be described in detail with reference to specific examples.
As shown in fig. 10, on the cross section of the bottom of the osculating flow field waverider with a variable wall pressure distribution rule, the calculated shape and position of the shock wave outlet profile are well matched with the design values; as shown in fig. 11, in each osculating plane, the calculation result of the pressure distribution law is well matched with the design result. The above numerical simulation results all verify the correctness of the invention.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The design method of osculating the flow field waverider with a variable wall surface pressure distribution rule is characterized by comprising the following steps of:
s100: giving the width W of the wave multiplier configuration, giving an upper surface rear edge line, giving a shock wave outlet molded line, and giving the height H between the upper surface rear edge line and the shock wave outlet molded line;
s200: designing a revolving body bus of an axisymmetric reference flow field;
the revolving body bus of the axisymmetric reference flow field is formed by connecting a section of straight line segment and a section of curve segment; input parameters of a straight line segment of a revolving body bus of the axisymmetric reference flow field are given, wherein the input parameters comprise the length and the inclination angle of the straight line segment; a curve equation of a curve section of a revolving body bus of the axisymmetric reference flow field is given, and a change rule curve delta of the inclination angle of a wall surface point along the wave multiplying body span direction is designed 2 (z) is represented by formula (1):
δ H (z)＝a*z 2 +b(b＞0) (1)
wherein, delta 2 Representing the inclination angle of a designed wall surface point, wherein z is the spanwise position coordinate of the waverider, and m and n represent coefficients of an inclination angle change curve; m is a positive number and represents delta 2 The curve is gradually increased along the spanwise direction, m is a negative number and represents delta 2 The spanwise direction is a decreasing curve, n represents the inclination angle of the wall surface point of the datum flow field datum body corresponding to the middle section in the spanwise direction of the wave-multiplying body, and n is greater than 0;
s300: dispersing the shock wave outlet molded line into a plurality of points, solving the osculating plane corresponding to each discrete point, and solving the delta corresponding to each discrete point according to the formula (1) 2 (z), then, solving an axisymmetric reference flow field corresponding to each osculating plane by combining given inflow conditions;
s400: in the axisymmetric reference flow field corresponding to each osculating plane obtained by the solution in S300, firstly obtaining a front edge point by a free flow line method, and then tracking a flow line from the front edge point to a rear edge point backwards to obtain a flow line in each osculating plane;
s500: and finally, the upper surface, the lower surface and the bottom surface jointly form a variable wall surface pressure distribution rule osculating flow field waverider pneumatic configuration.
2. The design method of the variable wall pressure distribution rule osculating flow field wave-rider according to claim 1, wherein in S100, the given upper surface trailing edge line and the given shock wave outlet profile are bilaterally symmetrical about their respective centerlines.
3. The design method of the osculating flow field waverider with the variable wall pressure distribution rule according to claim 2, wherein in S100, a curve equation of an upper surface trailing edge line is shown in formula (2), and a curve equation of a shock wave outlet profile is shown in formula (3):
y＝a×z 3 +b×z 2 +c×z+d (2)
coefficient a = y of (3) in equation 13 /(z 13 -L s ) 4 ，L s ＝0.1*W，z 13 ＝0.5*W，y 13 =0.1 × h; the coefficients d = H, c = tan (T) in equation (2) 14 )，b＝(3.0*(y 13 -d-c*z 13 )-z 13 *tan(T 13 )+z 13 *c)/z 13 2 ，a＝(y 13 -d-c*z 13 -b*z 13 2 )/z 13 3 (ii) a Wherein (y) 13 ,z 13 ) Is a coordinate value of the intersection point of the upper surface trailing edge line and the shock wave outlet profile, T 13 The inclination angle of the intersection point of the upper surface rear edge line and the shock wave outlet molded line is shown; t is a unit of 14 Is the angle of inclination at the midpoint of the trailing edge line of the upper surface.
4. The design method of the osculating flow field waverider with the variable wall surface pressure distribution rule according to claim 2 is characterized in that the implementation method of S300 is as follows:
s310: uniformly dispersing the shock wave outlet profile into a plurality of points;
s320: randomly selecting a point i from discrete points on the shock wave outlet molded line to obtain a curvature circle tangent to the point i with the shock wave outlet molded line and the center of the curvature circle, wherein the plane of the curvature circle is the osculating plane corresponding to the point i, and the radius of the curvature circle is the radius R of the original reference flow field corresponding to the osculating plane corresponding to the point i i ；
S330: the Z-direction coordinate Z of the point i i Substituting the formula (1) to obtain the inclination angle delta of the wall surface point corresponding to the point i 2 (z i ) And combining the given incoming flow Mach number, the incoming flow static temperature and the incoming flow static pressure to solve the axisymmetric reference flow field corresponding to the discrete point i, wherein the shock wave radius of the reference flow field is R si ；
S340: with R i /R si Scaling the reference flow field in step S320 for scaling, where the scaled flow field is the axisymmetric reference flow field corresponding to the point i;
s350: and (5) repeating the steps S320-S340 for all discrete points on the shock wave outlet molded line respectively to obtain a osculating plane and a reference flow field corresponding to each discrete point on the shock wave outlet molded line.
5. The design method of the variable wall pressure distribution rule osculating flow field waverider according to claim 4, characterized in that the implementation method of S400 is as follows:
for any point i in discrete points on the shock wave outlet molded line, in the axisymmetric reference flow field corresponding to the point i obtained by solving in the S300, a connecting line between the point i and the circle center of the curvature circle corresponding to the point i intersects with the upper surface rear edge line at one point, the intersection point is a point on the upper surface rear edge molded line, and a front edge point corresponding to the point i is obtained by solving in the axisymmetric reference flow field corresponding to the point i according to a free streamline method; performing streamline tracing from the front edge point corresponding to the point i to obtain a rear edge point corresponding to the point i, wherein the front edge point corresponding to the point i and the rear edge point corresponding to the point i form a streamline in the osculating plane corresponding to the point i; by analogy, the solution is carried out in the axisymmetric reference flow field corresponding to the discrete point on each shock wave outlet molded line, so that a series of front edge points, rear edge points and flow lines can be obtained, the front edge points are in smooth connection to form a front edge line of the variable wall surface pressure distribution rule osculating flow field waverider, and the rear edge points are in smooth connection to form a lower surface rear edge molded line of the variable wall surface pressure distribution rule osculating flow field waverider.
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