CN105329462A - Changeable wall surface pressure distribution rule-based osculating flow field ride precursor design method - Google Patents

Abstract

A design method for waveriding precursors of kissing flow field based on variable wall pressure distribution. rotators, respectively solve the supersonic axisymmetric flow fields around these three rotators, and use the obtained flow fields as the reference flow fields with different wall pressure distribution laws; S2, according to the performance requirements of the waverider precursor, Design the shock wave outlet profile, apply the kissing principle to solve the flow field at each kissing plane, and combine the flow fields of all the kissing planes into a three-dimensional reference flow field; The projected curve, according to the shock wave exit profile, uses the streamline tracing method in each kissing plane of S2 to generate the aerodynamic configuration of the waveriding precursor of the kissing flow field. The waverider precursor designed by this method can not only meet the requirement of high lift-to-lift ratio at the inlet of the inlet, but also fully utilize the high lift-to-drag ratio characteristic of the waverider precursor.

Description

Design method of waverider precursor for kiss-cut flow field based on variable wall pressure distribution

technical field

The invention relates to the technical field of aerodynamic shape design of a hypersonic vehicle, in particular to a design method for a waverider precursor of a kiss-cut flow field based on a variable wall surface pressure distribution law.

Background technique

An air-breathing hypersonic vehicle refers to an aircraft with a flight Mach number greater than 5, powered by an air-breathing engine or a combined engine, and capable of long-distance flight in the atmosphere and across the atmosphere. Its application forms include hypersonic cruise missiles, hypersonic Manned/unmanned aircraft and aerospace aircraft and other aircraft.

The aerodynamic shape of hypersonic vehicles mainly includes three types: axisymmetric configuration, lift body configuration and waverider configuration. Among them, the waverider configuration uses the shock wave compression principle (waverider principle) In addition to the aerodynamic requirements of high lift-to-drag ratio under high conditions, in addition to the problem of how to balance the aerodynamic thermal protection and aerodynamic performance of the leading edge, the research on this configuration has become mature.

The core of the waverider configuration design method is the selection of the reference flow field. Different reference flow fields correspond to different design methods. The existing methods are as follows: wedge guidance method, cone guidance method, wedge cone method and supersonic-based Kiss-cut class generation method for axisymmetric flow. Among them, kiss-cut design methods mainly include kiss-cut cone design theory, kiss-cut axisymmetric design theory and kiss-cut flow field design theory. The kiss-cut cone theory makes the shock line shape of the bottom cross-section of the waverider no longer limited to circular arc or straight line, but can be reasonably designed according to the shape of the inlet lip. The kissing axisymmetric theory proposes that the reference flow field in the kissing plane can no longer be limited to the conical flow field, but an appropriate axisymmetric reference flow field can be selected according to the design requirements. The waverider configuration with more uniform lateral flow can be obtained by applying the kiss-cut cone and kiss-cut axisymmetric theory, and can effectively improve the flow field quality of the waverider precursor (intake inlet), which is beneficial to the fuselage-inlet integrated design. The kissing flow field theory proposes that the reference flow field in each kissing plane is no longer limited to the same axisymmetric flow field, but can choose different axisymmetric reference flow fields in each kissing plane according to design requirements.

In 2011, He Xuzhao and others proposed a method using a curved cone with a straight line shock wave and an isentropic compression wave system as the reference flow field The design method effectively overcomes the shortcomings of insufficient compression and small volume ratio of traditional kiss-cut cone waveriders. However, this method has certain defects, that is, due to the increase of the pressure-to-lift ratio, the high lift-to-drag ratio of the waverider precursor cannot be fully utilized.

Contents of the invention

The invention provides a design method for waveriders in kiss-cut flow field based on the variable wall pressure distribution law, which solves the problem that the existing waverider body can only be designed according to the constant wall pressure distribution law. The waverider precursor designed based on this method can not only meet the requirement of high lift-to-lift ratio at the inlet of the intake port, but also give full play to the high lift-to-drag ratio characteristics of the waverider precursor.

In order to solve the above problems, the present invention adopts the following technical solutions:

A method for designing a waverider precursor in a kiss-cut flow field based on variable wall pressure distribution, comprising the following steps:

S1. Given three different curves of wall pressure distribution law, which are the curve of rising wall pressure, the curve of constant wall pressure and the curve of decreasing wall pressure, respectively, the three curves are used as the busbar of the rotating body, and three different rotating bodies are designed. , respectively solve the supersonic axisymmetric flow fields around these three rotating bodies, and use the obtained flow fields as the reference flow fields with different wall pressure distribution laws;

S2. According to the performance requirements of the waverider precursor, divide the shock wave exit profile into three sections for design, and ensure that the designed profile has continuous curvature at the junction of each section of the curve, that is, the second derivative of the curve is continuous, and then according to For the designed shock wave outlet profile, the kissing principle is applied to solve the flow field in each kissing plane, and all the kissing plane flow fields are combined into a three-dimensional reference flow field;

S3. Given the projection curve of the leading edge line of the waverider front at the bottom, according to the shock wave exit profile in step S2, use the streamline tracing method in each kissing plane in step S2 to generate the kissing flow field waveriders Precursor aerodynamic configuration.

The present invention adopts the kiss-cut flow field theory as the basis, and given the same incoming flow conditions, according to the performance requirements of different positions of the waverider, the wall pressure is selected at the inlet position of the air inlet (that is, the middle part of the waverider). The elevated reference flow field ensures the high-pressure lift ratio characteristics at the entrance of the inlet; the reference flow field with reduced wall pressure is selected at both ends of the waverider spanwise, so that the characteristics of the high lift-to-drag ratio of the waverider precursor can be fully utilized; in the above In the part between the two positions, the reference flow field with constant wall pressure is selected as the transition.

Beneficial technical effect of the present invention:

The present invention provides a new waverider design method, that is, a waverider design method based on the variable wall pressure distribution law of the kissing flow field waverider. This method can be used to select the wall pressure increase at the inlet position of the inlet (that is, the middle part of the waverider span) according to the performance requirements of different positions of the waverider spanwise. The reference flow field ensures the high-pressure lift ratio characteristics of the inlet inlet; the reference flow field with reduced wall pressure is selected at both ends of the waverider spanwise, so that the characteristics of the high lift-to-drag ratio of the waverider precursor can be fully utilized;

Description of drawings

Fig. 1 is the cross-sectional view of the reference flow field of three different wall pressure distribution laws;

Among them, the straight line 1-3-11 represents the shock wave generated by the cone generated by the bus 1-2 in the design state; 2-11 represents the left-hand characteristic line emitted by 2 points; 1-2-5, 1-2- 6. 1-2-7 represent the three gyratory generatrixes with increasing wall pressure, constant wall pressure and decreasing wall pressure respectively; Curve 3-4-8 represents the flow field generated by the gyrator generated by busbar 1-2-5 The streamline obtained by streamline tracing; curve 3-4-9 represents the streamline obtained by streamline tracing in the flow field generated by the rotator generated by bus 1-2-6; curve 3-4-10 represents the streamline obtained by the bus 1-2-6 2-7 The streamlines obtained by tracing the streamlines in the flow field generated by the gyrator; 12 represents the inclination angle of the generatrix of the gyrator at point 5 with increasing wall pressure; 13 represents the inclination angle of the generatrix of the gyrator with constant wall pressure at point 6 Inclination angle; 14 indicates the inclination angle of the generatrix of the rotary body at point 7 when the wall pressure decreases; 15 indicates the total length of the reference flow field; 16 indicates the total width of the reference flow field, that is, the radius of the shock wave exit; 17 indicates the initial compression angle of the rotary body , that is, the angle between the bus 1-2-6 and the x-axis;

Fig. 2 is a schematic diagram of a section of a shock wave outlet;

Among them, 18 is the projection line of the front edge line of the waverider body on the section of the shock wave exit, which is also the trailing edge line of the upper surface of the waverider body; 19 is the trailing edge line of the lower surface of the waverider body; 20 is the shock wave exit type line; 21 is the kissing cone corresponding to point 25; 22 is the projection point of the apex of the kissing cone corresponding to point 25 on the shock wave exit section; point 23 is the line connecting point 22 and point 25 and the trailing edge of the upper surface of the waverider precursor The intersection point of the line; point 24 is the intersection point of the line connecting point 22 and point 25 and the trailing edge line of the lower surface of the waverider precursor; 25 is any point on the shock wave exit profile line; 26 is the kissing plane passing through point 25; the curve 27-28, 28-29, 29-29', 28'-29' and 27'-28' constitute the shock wave exit profile 20; 30 is the curvature circle passing through point 25;

Figure 3 is a schematic diagram of streamline tracing in the kissing plane;

Among them, 31 is the apex of the kissing cone corresponding to point 25; 32 is the leading edge point corresponding to point 25;

detailed description

The invention provides a method for designing a waverider precursor of a kiss-cut flow field with a variable wall pressure distribution law, which includes the following steps:

Step S1, given three different curves of wall pressure distribution law, which are the curve of wall pressure increase, the curve of wall pressure constant and the curve of wall pressure decrease, respectively, the three curves are used as the generatrix of the rotary body, and three different rotary curves are designed. The supersonic axisymmetric flow fields around these three rotating bodies are respectively solved, and the obtained flow fields are used as the reference flow fields with different wall pressure distribution laws.

(1) Given a straight line segment 1-2-6, one end point of the straight line segment is point 1, the other end point of the straight line segment is point 6, point 2 is a point in the middle of the straight line segment, point 1 is located on the x-axis, and the straight line segment The included angle between 1-2-6 and the x-axis is 17, and the included angle 17 is equal to the included angle 13 of the straight line segment at point 6, and the straight line segment 1-2-6 is used as the generatrix of the revolving body, so that it circles the x-axis 360° Rotate to form a straight cone, which is a body of revolution with constant wall pressure;

(2) a point 5 is given directly above the point 6, and an outer expansion curve 2-5 is designed between the point 2 and the point 5, and the outer expansion curve 2-5 of the present invention is a curve of a parabolic form, and the curve 2-5 and The first derivative of straight line 1-2 at point 2 is continuous, and combined with the coordinates of point 2 and point 5, the formula (1) can be used to uniquely determine curve 2-5, the tangent of curve 2-5 at point 5 and the x-axis The angle is 12, and the included angle 12 is greater than the included angle 17. The curve 1-2-5 rotates 360° around the x-axis to form an outwardly expanding curved surface cone, and the formed outwardly expanding curved surface cone is a body of revolution with increased wall pressure;

y=ax ² +bx+c(1)

(3) a point 7 is given directly below point 6, and an internal expansion curve 2-7 is designed between point 2 and point 7. The internal expansion curve 2-7 of the present invention is a curve of parabolic form, and curve 2-7 and straight line 1-2 The first-order derivative at point 2 is continuous, combined with the coordinates of 2 points and 7 points, using formula (1) can uniquely determine curve 2-7, the angle between the tangent line of curve 2-7 at point 7 and the x-axis is 14, and the included angle 14 is smaller than the included angle 17; the curve 1-2-7 rotates around the x-axis 360° to form an internal expansion curved surface cone, and the formed internal expansion curved surface cone is a body of revolution with reduced wall pressure;

(4) Given the incoming flow conditions (Mach number, static pressure, and static temperature), the method of rotating characteristic lines is used to solve the supersonic axisymmetric flow field around these three rotating bodies, and three reference flow fields are obtained, which are defined as : The reference flow field with constant wall pressure, the reference flow field with increased wall pressure and the reference flow field with reduced wall pressure. The spin characteristic line method is a well-known technology in the art. For details, please refer to ""Gas Dynamics", M.J. Zocrow, J.D. Hoffman, National Defense Industry Press, 1984, p138-195".

Among them, the waverider configuration obtained by streamline tracing in the reference flow field with increased wall pressure has a high lift ratio, and the streamlines traced in the flow field with increased wall pressure correspond to curve 3-4- in Figure 1 8. The waverider configuration obtained by streamline tracing in the reference flow field with reduced wall pressure has a high lift-to-drag ratio, and the streamline traced in the flow field with reduced wall pressure corresponds to curve 3-4-10 in Figure 1 .

(Note: Pressure rise ratio = cross-sectional pressure at the bottom of the waverider precursor / incoming flow pressure)

Step S2, assembling the three axisymmetric reference flow fields obtained in step S1 into a three-dimensional reference flow field by applying the kiss cut principle;

First, design the shock wave exit profile.

The shock wave exit profile is symmetrical about the center line, and the shock wave exit profile is divided into five sections, namely, the left section 27-28 of the waverider precursor, the left transition section 28-29 of the waverider precursor, and the inlet of the inlet The position section 29-29', the right transition section 28'-29' of the waverider body, the right section 27'-28' of the waverider body, of which the left section 27-28 of the waverider body and the right section 27 of the waverider body '-28' is left-right symmetrical, and the left transition section 28-29 of the waveriding precursor and the right transition section 28'-29' of the waveriding precursor are left-right symmetrical. The left section 27-28 of the waveriding front body and the right section 27'-28' of the waveriding front body are collectively referred to as both end sections of the waveriding front body, and the left transition section 28-29 of the waveriding front body and the right transition section of the waveriding front body Sections 28'-29' are collectively referred to as the transition section of the waverider precursor, so when designing the shock wave exit profile, it is only necessary to design the two end sections 27-28 and 27'-28' of the waverider precursor, and the transition section 28 of the waverider precursor. -29 and 28'-29', the inlet position section of the air inlet 29-29' is sufficient;

As shown in Figure 2, the shock wave exit profile is divided into three sections for design, these three sections are the two end sections 27-28 and 27'-28' of the waverider precursor, and the transition section 28-29 of the waverider precursor. And 28'-29', air inlet inlet position section 29-29'. Given the coordinates of the connection points between the left section of the waverider front body, the left transition section of the waverider front body, the inlet position section, the right transition section of the waverider body and the right section of the waverider front body, that is, the given points 27, The coordinates of point 28, point 29, point 27', point 28' and point 29'. The inlet position section 29-29' of the air inlet is designed as a horizontal straight line, the two end sections 27-28 and 27'-28' of the wave front body and the transition sections 28-29 and 28'-29' of the waverider body are designed as For quartic curves, the second order derivatives at the left and right sides of the connecting points of each section of the curve are the same to ensure that the curvature between sections is continuous, that is, the designed curve has continuous second order derivatives at points 28, 29, 28', and 29'. Using the quartic curve equation (2), the coefficients in the quartic curve equation can be uniquely determined from the coordinates of the connection point and the continuity of the second order derivative at the connection point, and then the two ends of the wave front body and the transition section of the wave-riding body can be determined The corresponding quartic curve.

y=ax ⁴ +bx ² +c(2)

Among them, the design reference flow field of the two end sections 27-28 and 27'-28' of the waverider is the reference flow field of the wall pressure reduction defined in S1, which is used to increase the lift-to-drag ratio of the waverider precursor; The inlet position section 29-29' adopts the reference flow field with increased wall pressure distribution defined in S1 to ensure the high pressure lift ratio requirement at the entrance of the inlet; the waverider precursor transition sections 28-29 and 28'-29' adopt The reference flow field with constant wall pressure defined in S1;

As shown in Figure 2, the shock wave exit profile 20 is discretized, and a point is taken every 5 mm on the shock wave exit profile, which can ensure that the streamlines generated at different points can form a smooth surface; after the shock wave exit profile is discretized Randomly take a point 25 among the discrete points obtained, and obtain the curvature circle 30 passing through this point, and the curvature circle 30 is the kissing circle of the kissing surface cone corresponding to point 25 in the exit section, the axis of the kissing curved surface cone is in line with X The axes are parallel, and the plane passing through the point 25 and the cone axis of the kissing curved surface is the kissing plane 26; the point 22 is the center of the curvature circle 30;

If point 25 is located at the transition section of the waverider body, select the reference flow field with constant wall pressure in step S1 as the flow field in the kissing plane passing through point 25; if point 25 is located at both ends of the waverider, select step S1 The reference flow field with reduced wall pressure is taken as the flow field in the kissing plane passing through point 25; if point 25 is located at the entrance of the inlet, the reference flow field with increased wall pressure distribution in step S1 is selected as the kissing plane passing through point 25 Inner flow field; each point taken after discretizing the shock wave outlet profile according to this rule selects the reference flow field corresponding to the wall pressure distribution as the kiss cut flow field corresponding to the point according to the respective shock wave segment. The point 25 shown in FIG. 2 is located at the left transition section 28-29 of the waverider body. Therefore, the reference flow field with constant wall pressure in step S1 is selected as the flow field in the kissing plane passing through the point 25.

Step S3, given the projection curve of the leading edge line of the waverider precursor at the bottom, according to the shock wave outlet profile in step S2, use the streamline tracing method in each kissing plane in step S2 to generate the kissing flow field product Aerodynamic configuration of wave precursors.

(1) Firstly, the projection curve of the leading edge line of the waverider body at the bottom is given, that is, the trailing edge line of the upper surface of the waverider body. Take sufficiently dense discrete points at equal intervals from the shock wave exit profile designed in step S2. Generally, one point is taken every 5 mm to ensure that the streamlines generated by different points can form a smooth surface. For details, see Ding Feng. Hypersonic Gliding - Research on two-stage waveriding design method for cruising [D]. Changsha: University of National Defense Science and Technology (Master). 2012.

(2) As shown in Figure 2 and Figure 3, a point 25 is arbitrarily selected among the discrete points obtained after the shock wave exit profile is discrete, and the curvature circle 30 passing through point 25 is obtained from point 25, and the curvature circle passing through point 25 is is the kissing circle of the kissing cone shock corresponding to point 25 at the exit section, and the axis of the kissing cone is parallel to the x-axis (ie, the free streamline). The point 22 is the center of the curvature circle 30 passing through the point 25, and is also the projection point of the vertex 31 ( FIG. 3 ) of the kissing cone corresponding to the point 25 on the shock wave exit section. 25 o'clock, 22 o'clock and 31 o'clock constitute the kiss section 26 passing through point 25. The line connecting point 25 and point 22 intersects the rear edge line of the upper surface of the waverider at point 23, and a straight line parallel to the x-axis is drawn from point 23 to meet the tangent cone shock at point 32, and point 32 is also the kiss passing through point 25 Corresponding front edge point in the tangential plane. Tracing the streamline from the leading edge point 32 backward to the shock wave exit section, the trailing edge point 24 is obtained, and the curve 32-24 formed by connecting the leading edge point and the trailing edge point is the lower surface streamline corresponding to the point 25. Point 32 Connect with point 23 with a straight line to obtain the upper surface streamline corresponding to point 25; for all the discrete points obtained after the shock wave exit profile is discretized, use the same method to obtain the leading edge points in the respective kissing planes and the lower surface of the waverider Streamlines, streamlines on the upper surface of the waverider, and points on the trailing edge line on the lower surface.

(3) A series of leading edge points are smoothly connected to form the leading edge line of the waverider; a series of upper surface streamlines form the upper surface of the waverider; a series of lower surface streamlines form the lower surface of the waverider; a series of trailing edge lines The points above are connected smoothly to form the trailing edge line of the lower surface of the waverider; the aerodynamic configuration of the waverider front is formed by the leading edge line, the trailing edge line and the lower surface of the waverider.

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.