The optimization of the waverider is constrained by the reversely designed leading edge and the constant shock angle distribution. This paper proposes a design method called the variable Leading-Edge Cone (vLEC) metho...The optimization of the waverider is constrained by the reversely designed leading edge and the constant shock angle distribution. This paper proposes a design method called the variable Leading-Edge Cone (vLEC) method to address these limitations. In the vLEC method, the waverider is directly designed from the preassigned leading edge and the variable shock angle distribution based on the Leading-Edge Cone (LEC) concept. Since the vLEC method is an approximate method, two test waveriders are designed and evaluated using numerical simulations to validate the shock design accuracy and the effectiveness of the vLEC method. The results show that the shocks of the test waveriders coincide well with the preassigned positions. Furthermore, four specifically designed application cases are conducted to analyze the performance benefits of the vLEC waveriders. The results of these cases indicate that, due to their variable shock angle distributions, the vLEC waveriders exhibit higher lift-to-drag ratios and better longitudinal static stability than conventional waveriders. Additionally, the vLEC waveriders demonstrate superior volumetric capacities near the symmetry plane, albeit with a minor decrease in volumetric efficiency.展开更多
A new internal waverider inlet with a rectangular shape of entrance and exit in front view is designed at Ma=6.0.The design is based on a better basic flowfield ICFC than traditional one and derived with the technolog...A new internal waverider inlet with a rectangular shape of entrance and exit in front view is designed at Ma=6.0.The design is based on a better basic flowfield ICFC than traditional one and derived with the technology of stream tracing and shock cutting.Comparison between the newly designed inlet and a typical sidewall compression inlet is given.The design Mach number and entrance shape of this new inlet are chosen according to the sidewall compression inlet.Numerical results show that most of the performance parameters of the internal waverider inlet are a bit higher than the sidewall inlet,such as the flow capture coefficient,total pressure recovery and the kinetic efficiency.The performances of these two inlets at off-design points are compared.The internal waverider inlet can capture more than 91% of incoming flow under all simulated conditions.Results show that internal waverider inlet using 3-D compression and high flow capture coefficient is a kind of fixed-geometry inlet with better performance.展开更多
A design method based on tip to tail streamline tracing and osculating inward cone methods is discussed for designing the integrated Osculating Inward Cone Waverider Inlet（OICWI）. A practical geometrical constrained...A design method based on tip to tail streamline tracing and osculating inward cone methods is discussed for designing the integrated Osculating Inward Cone Waverider Inlet（OICWI）. A practical geometrical constrained experimental model of OICWI is designed based on the validated design method. It has a total contraction ratio of 4.61 and inner contraction ratio is 2.0. Wind-tunnel tests have been conducted for the OICWI model at free stream Mach number（Ma） of 4.0, 3.5 and 3.0 respectively. The experimental results show that the OICWI has high flow capture ratio and compression abilities. It can self-start at Ma= 3.5 and 4.0 and its flow capture ratio is 0.73 at Ma= 4.0, and Angle of Attack（AOA） 0°. The research results show that the OICWI has advantages of inward cone waverider and streamline tracing inlet. Present OICWI is a novel approach for waverider inlet integration studies and it will promote the use of waverider inlet integration configuration in the studies of airbreathing hypersonic vehicles.展开更多
A method based on the computational fluid dynamics （CFD） is presented for a flexible waverider＇s design. The generating bodies of this method could be any cones. In addition, either the leading edge or the profile ...A method based on the computational fluid dynamics （CFD） is presented for a flexible waverider＇s design. The generating bodies of this method could be any cones. In addition, either the leading edge or the profile of the scramjet＇s inlet is used as the waverider＇s definition curve, parameterized by the quadric function, the sigmoid function or the B-spline function. Furthermore, several numerical examples are carried out to validate the method and the relevant codes. The CFD results of the configurations show that all the designs are successful. Moreover, primary suggestions are proposed for practical design by comparing the geometrical and aerodynamic performances of the conederived waveriders at Mach 6.展开更多
Intensive studies have been carried out on generations of waverider geometry and hypersonic inlet geometry. However, integration efforts of waverider and related air-intake system are restricted majorly around the X43...Intensive studies have been carried out on generations of waverider geometry and hypersonic inlet geometry. However, integration efforts of waverider and related air-intake system are restricted majorly around the X43A-like or conical flow field induced configuration, which adopts mainly the two-dimensional air-breathing technology and limits the judicious visions of developing new aerodynamic profiles for hypersonic designers. A novel design approach for integrating the inward turning inlet with the traditional parameterized waverider is proposed. The proposed method is an alternative means to produce a compatible configuration by linking the off-the-shelf results on both traditional waverider techniques and inward turning inlet techniques. A series of geometry generations and optimization solutions is proposed to enhance the lift-to-drag ratio. A quantitative but efficient aerodynamic performance evaluation approach （the hypersonic flow panel method） with lower computational cost is employed to play the role of objective function for opti- mization purpose. The produced geometry compatibility with a computational fluid dynamics （CFD） solver is also verified for detailed flow field investigation. Optimization results and other numerical validations are obtained for the feasibility demonstration of the proposed method.展开更多
When considering the practical engineering application of a waverider,the on-design and off-design aerodynamic characteristics of the design conditions,especially the lift-to-drag ratio and the stability,deserve atten...When considering the practical engineering application of a waverider,the on-design and off-design aerodynamic characteristics of the design conditions,especially the lift-to-drag ratio and the stability,deserve attention.According to recently studies,the planform and rear sight shape of a waverider are closely related to the above aerodynamic performance.Thus,the planform leading-edge profile curve used to design the planform shape of a vehicle is applied to designing an osculating cone waverider.Two key parameters concerned in planform and rear sight shape,namely the plan view sweep angle of the leading edge and the dihedral angle of the underside are introduced to the waverider design process.Each parameter is inserted in the control curve equation.Especially,a parameterization scheme is put forward for the free adjustment of the sweep angle along the leading edge.Finally,three examples are generated for verification and investigation.After the verification process based on the inviscid flow field of one case,the influences of the sweep and dihedral angles on the lift-to-drag ratio and the lateral static stability are evaluated,and meaningful results are obtained.Based on these results,we can conclude that,considering the maximum lift-to-drag ratio,the sweep angle plays a role on the lift-to-drag ratio only at subsonic and trans/supersonic speed as a negligible effect is observed at hypersonic speeds,whereas the dihedral angle is seem to produce a relevant difference at hypersonic speeds.Considering the lateral static stability,the dihedral angles have more influence on the waverider than the sweep angles.展开更多
An experiment of a hypersonic vehicle configuration was conducted. The pressure difference of forbody precornpress surface is small. Pressure difference of three monitor points are 25.2%, 20. 5% and 17.29% respectivel...An experiment of a hypersonic vehicle configuration was conducted. The pressure difference of forbody precornpress surface is small. Pressure difference of three monitor points are 25.2%, 20. 5% and 17.29% respectively in the design condition. It indicates that there is crosswise flow in forebody boundary layer. Pressure difference at Ma = 6. 971 is lower than those of two other Mach number conditions. It indicates that the tested configuration has good aerodynamic performance in high Maeh number. Angle of attack has no great influence on the pressure difference. In almost all the angle of attack conditions, the pressure difference at Ma =6. 971 is slightly smaller than that in Ma =5. 993. The difference in the third precompress surface is slightly smaller than those in two others.展开更多
Developing the waverider based hypersonic vehicles is an inverse design process in which shape is developed from a known flow field by tracing of streamlines to form a stream surface. The flow field can be based on a ...Developing the waverider based hypersonic vehicles is an inverse design process in which shape is developed from a known flow field by tracing of streamlines to form a stream surface. The flow field can be based on a solution of Taylor Maccoll equation for a specified shock or cone angle. This Paper discusses the development of waverider shapes for hypersonic reentry vehicles.展开更多
Compared with conventional vehicles,waverider is expected to overcome the limitations of lift-to-drag ratio in hypersonic conditions and considered one of the most promising configurations for hypersonic vehicles.Typi...Compared with conventional vehicles,waverider is expected to overcome the limitations of lift-to-drag ratio in hypersonic conditions and considered one of the most promising configurations for hypersonic vehicles.Typically,waverider exhibits good aerodynamic performance under the design condition.However,maintaining such performance under off-design condition is challenging,leading to insufficient aerodynamic performance across a wide range of speed.This paper first proposes a novel design method for double swept waverider,where lift exhibits nonlinear growth with an increasing angle of attack and generates strong surface vortex lift at low speeds.These characteristics effectively accommodate both high-speed and low-speed conditions,improving waverider performance under off-design condition across a wide range of speed.The curvedcone-derived waverider design based on the projection approach enables simultaneous control of the basic flow field and planform contour,addressing the limited design space issue of conventional methods while enhancing aerodynamic performance under the design condition.Furthermore,to achieve optimal wide-speed-range performance,an aerodynamic estimation method is developed and combined with an improved multi-objective cuckoo search algorithm for optimization.Subsequently,the numerical method is applied to the optimized representative configurations under the hypersonic condition and the expected aerodynamic performance is obtained.The subsonic aerodynamic performance of waverider is also investigated.The double swept waverider in this research generates strong vortex lift and ideal longitudinal static stability performance at subsonic speed,which optimizes the wide-speed-range aerodynamic performance.展开更多
Waverider design based on osculating theory presents two critical issues:robust specification of design curves and accurate solution of the basic flowfield.Although the existing parametric approaches have advanced rap...Waverider design based on osculating theory presents two critical issues:robust specification of design curves and accurate solution of the basic flowfield.Although the existing parametric approaches have advanced rapid configuration generation through geometric parameterization frameworks,they critically neglect the inherent coupling between aerodynamic constraints and geometric design parameters.To overcome this limitation,an Aerodynamics-Informed Parametric(AIP)method is developed by analytically deriving three waverider design curves and integrating them with the second-order curved shock theory.This method enables rapid waverider surface design while accounting for inflow conditions and shock wave geometry.Three typical waveriders,each featuring distinct combinations of design curves as inputs,are constructed and evaluated through inviscid and viscous numerical simulations to validate the applicability and accuracy of the AIP method.The results indicate that waveriders derived using the AIP method successfully reproduce the preassigned shock waves and original flowfields.Compared to traditional waverider design techniques based on the method of characteristics,the AIP method reduces computation time by approximately 94%,while maintaining errors in the inviscid lift-to-drag ratio,viscous lift-to-drag ratio,and volumetric efficiency below 0.1%,4.0%,and 0.1%,respectively.Additionally,a specially designed model is fabricated for the wind-tunnel tests to analyze the hypersonic aerodynamic performance of the waverider.Both numerical and experimental results confirm the feasibility of the AIP method,making it a promising candidate for waverider design and optimization.展开更多
A new hypersonic inlet named three-dimensional section controllable internal waverider inlet is presented in this paper to achieve the goal of section shape geometric transition and complete capture of the upstream ma...A new hypersonic inlet named three-dimensional section controllable internal waverider inlet is presented in this paper to achieve the goal of section shape geometric transition and complete capture of the upstream mass. On the basis of the association between hypersonic waverider airframe and streamtraced hypersonic inlet, the waverider concept is extended to yield results for the internal flows, namely internal waverider concept. It is proven theoretically that not osculating cones but osculating axisymmetric theory is appropriate for the design of section controllable internal waverider inlet. And two design methods out of the internal waverider concept are proposed subsequently to construct two inlets with specific section shape request, triangle to ellipse and rectangle to ellipse ones. The calculation results show that the inlets are capable of keeping their shock structures and the main flow characteristics exactly as their derived flowfield. Further, the inlets successfully capture all the upstream mass despite their complicated cross-section transitions. It is believed that the concept proposed ex- plores a new way of designing three-dimensional hypersonic inlets with special demand of section shape transition. However, the detailed flow characteristic and the performance of the internal waverider inlets are still under investigation.展开更多
Waverider generated from a given flow field has a high lift-to-drag ratio because of attached bow shock on leading edge. However, leading edge blunt and off-design condition can make bow shock off leading edge and hav...Waverider generated from a given flow field has a high lift-to-drag ratio because of attached bow shock on leading edge. However, leading edge blunt and off-design condition can make bow shock off leading edge and have unfavorable influence on aerodynamic characteristics. So these two problems have always been concerned as important engineering science issues by aeronautical engineering scientists. In this paper, through respectively using low speed and high speed waverider design principles, a wide-speed rang vehicle is designed, which can level takeoff and accelerate to hypersonic speed for cruise. In addition, sharp leading edge is blunted to alleviated aeroheating. Theoretical study and wind tunnel test show that this vehicle has good aerodynamic performance in wide-speed range of subsonic, transonic, supersonic and hypersonic speeds.展开更多
Wide-speed-range gliding vehicle(WSRGV) is designed to adapt to the variable cruising environment that hypersonic vehicles will encounter during the mission implementation. Based on the cone-derived theory, a novel de...Wide-speed-range gliding vehicle(WSRGV) is designed to adapt to the variable cruising environment that hypersonic vehicles will encounter during the mission implementation. Based on the cone-derived theory, a novel design technique of WSRGV has been developed. Theoretically, the functional relationship between cone-derived waverider’s volumetric efficiency and its design Mach number can be built through sampling approach as long as the geometries of design conical shock wave and the upper base curve are fixed. Based on the functional relationship, a cone-derived waverider that owns the same volumetric efficiency with a giving WSRGV can be acquired. This paper compared the aerodynamic performance between WSRGV and the cone-derived waverider sharing the same volumetric efficiency in a wide Mach number range. Their aerodynamic properties versus angle of attack have also been compared under the waverider’s design Mach number. The obtained result shows that WSRGV shares similar aerodynamic performance with the cone-derived waverider with the same volumetric efficiency. The aero-surfaces in the margin area of this kind of configuration have a larger contribution to the lift-to-drag ratio in comparison with the aero-surfaces in the central area. The configuration with a thick central body and thin margin place owns not only better aerodynamic performance but also better loading property.展开更多
For its outstanding aerodynamic capabilities,the integrated design of the waverider and inlet is widely accepted in hypersonic aircraft.Three aspects of the integrated design of the waverider and inlet since 2020 are ...For its outstanding aerodynamic capabilities,the integrated design of the waverider and inlet is widely accepted in hypersonic aircraft.Three aspects of the integrated design of the waverider and inlet since 2020 are mainly described in this paper.Firstly,the advantages and shortcomings of the conventional integrated design are examined.Then,different layouts of integrated design are proposed,and the aerodynamic perfor-mance optimization methods of the waverider,inlet,and their coupling are introduced.Besides,a series of methods for increasing the calculating accuracy of the waverider and inlet are presented,and the focus of attention is to consider the lateral flow problem.展开更多
In the future,aircraft will have both high flight speed and high stealth characteristics,and its detection will become a complex problem.However,the disturbance generated by the high-speed aircraft is evident in its t...In the future,aircraft will have both high flight speed and high stealth characteristics,and its detection will become a complex problem.However,the disturbance generated by the high-speed aircraft is evident in its tail flow field,which can be treated as a new feature.In this paper,the flow field of a Waverider at different attitudes and speeds is investigated.By observing the deflection of a 532 nm light beam incident in different directions,the relationship between deflection magnitude and the Waverider’s attitude is established.As a result,the light will deflect most(8.82×10^(−5) rad/s)whenWaverider with a 6 Ma flying speed and 0 angle of attack.While the mini deflection occurs whenWaverider flies at 4 Ma speed and with a 10◦angle of attack.By analyzing different conditions,this paper points out that the traveling length of light and magnitude of the scalar gradient in wake most positive correlate to the light deflection angle.As speed goes up,the wake becomes narrow,but the scalar gradient rises so that the light deflects most atMa6.As the incident of light goes closer to horizon direction,its traveling length in wake rises,the max deflection usually with a corresponding incident direction of 20◦.展开更多
An inverse method of characteristics was introduced into the design concept of using osculating cones (OC) in the supersonic flow, which can extend the domain of options for generating the aerospace vehicle configura...An inverse method of characteristics was introduced into the design concept of using osculating cones (OC) in the supersonic flow, which can extend the domain of options for generating the aerospace vehicle configurations with supersonic leading edge as well as inlet diffusers. Some more practical waverider shapes with higher volumetric efficiency can be obtained through using the concept of osculating axisymmetric (OA) flows with rotationality in the post shock flow field by inputting curved shocks.展开更多
To aim at design requirements of high lift-to-drag ratio as well as high volumetric efficiency of next generation hypersonic airplanes,a body-wing-blending configuration with double flanking air inlets layout is prese...To aim at design requirements of high lift-to-drag ratio as well as high volumetric efficiency of next generation hypersonic airplanes,a body-wing-blending configuration with double flanking air inlets layout is presented.Moreover,a novel forebody design methodology which by rotating and assembling two waverider-based surfaces is firstly introduced in this paper.Some typical configurations are designed and their aerodynamic performances are evaluated by computational fluid dynamics.The results for forebodies analysis show that large volumetric efficiency,high lift-to-drag ratio,and uniformly distributed flowfield at the inlet cross section can be assured simultaneously.Furthermore,results of numerical simulation of four integrated configurations with various leading edge shapes,including three power-law curves and a cosine curve clearly show the advantage of high lift-to-drag ratio.Besides,the high pressure generated by the side wall of the airframe can be partly captured by the reasonably designed wings in the condition of small flight attack angle.Then the order of lift-to-drag ratio of four configurations at 0 degree flight attack angle is completely different from the condition of 4-degree flight attack angle.This result demonstrates that the curve shape of the leading edge is very important for the lift-to-drag ratio of the aircraft,and it should be further optimized under the cruising attack angle in future work.展开更多
基金supported by grants from the National Natural Science Foundation of China(No.U20B2006)the Guangdong Basic and Applied Basic Research Foundation(No.2022A1515110145)Young Elite Scientists Sponsorship Program by China Association for Science and Technology(No.2022QNRC001).
文摘The optimization of the waverider is constrained by the reversely designed leading edge and the constant shock angle distribution. This paper proposes a design method called the variable Leading-Edge Cone (vLEC) method to address these limitations. In the vLEC method, the waverider is directly designed from the preassigned leading edge and the variable shock angle distribution based on the Leading-Edge Cone (LEC) concept. Since the vLEC method is an approximate method, two test waveriders are designed and evaluated using numerical simulations to validate the shock design accuracy and the effectiveness of the vLEC method. The results show that the shocks of the test waveriders coincide well with the preassigned positions. Furthermore, four specifically designed application cases are conducted to analyze the performance benefits of the vLEC waveriders. The results of these cases indicate that, due to their variable shock angle distributions, the vLEC waveriders exhibit higher lift-to-drag ratios and better longitudinal static stability than conventional waveriders. Additionally, the vLEC waveriders demonstrate superior volumetric capacities near the symmetry plane, albeit with a minor decrease in volumetric efficiency.
文摘A new internal waverider inlet with a rectangular shape of entrance and exit in front view is designed at Ma=6.0.The design is based on a better basic flowfield ICFC than traditional one and derived with the technology of stream tracing and shock cutting.Comparison between the newly designed inlet and a typical sidewall compression inlet is given.The design Mach number and entrance shape of this new inlet are chosen according to the sidewall compression inlet.Numerical results show that most of the performance parameters of the internal waverider inlet are a bit higher than the sidewall inlet,such as the flow capture coefficient,total pressure recovery and the kinetic efficiency.The performances of these two inlets at off-design points are compared.The internal waverider inlet can capture more than 91% of incoming flow under all simulated conditions.Results show that internal waverider inlet using 3-D compression and high flow capture coefficient is a kind of fixed-geometry inlet with better performance.
基金supported by the National Natural Science Foundation of China (Nos. 51376192 and 91216303)
文摘A design method based on tip to tail streamline tracing and osculating inward cone methods is discussed for designing the integrated Osculating Inward Cone Waverider Inlet（OICWI）. A practical geometrical constrained experimental model of OICWI is designed based on the validated design method. It has a total contraction ratio of 4.61 and inner contraction ratio is 2.0. Wind-tunnel tests have been conducted for the OICWI model at free stream Mach number（Ma） of 4.0, 3.5 and 3.0 respectively. The experimental results show that the OICWI has high flow capture ratio and compression abilities. It can self-start at Ma= 3.5 and 4.0 and its flow capture ratio is 0.73 at Ma= 4.0, and Angle of Attack（AOA） 0°. The research results show that the OICWI has advantages of inward cone waverider and streamline tracing inlet. Present OICWI is a novel approach for waverider inlet integration studies and it will promote the use of waverider inlet integration configuration in the studies of airbreathing hypersonic vehicles.
基金the National Natural Science Foundation of China （10502053, 10372106 , 10402043）, K. C. Wong Education Foundation of Hong Kongthe Key Laboratory of High Temperature Gas Dynamics of Chinese Academy of Sciences the State Key Laboratory of Structural Analysis for Industrial Equipment of Dalian University of Technology.
文摘A method based on the computational fluid dynamics （CFD） is presented for a flexible waverider＇s design. The generating bodies of this method could be any cones. In addition, either the leading edge or the profile of the scramjet＇s inlet is used as the waverider＇s definition curve, parameterized by the quadric function, the sigmoid function or the B-spline function. Furthermore, several numerical examples are carried out to validate the method and the relevant codes. The CFD results of the configurations show that all the designs are successful. Moreover, primary suggestions are proposed for practical design by comparing the geometrical and aerodynamic performances of the conederived waveriders at Mach 6.
基金supported by the National Natural Science Foundation of China (Grant No.61004089)
文摘Intensive studies have been carried out on generations of waverider geometry and hypersonic inlet geometry. However, integration efforts of waverider and related air-intake system are restricted majorly around the X43A-like or conical flow field induced configuration, which adopts mainly the two-dimensional air-breathing technology and limits the judicious visions of developing new aerodynamic profiles for hypersonic designers. A novel design approach for integrating the inward turning inlet with the traditional parameterized waverider is proposed. The proposed method is an alternative means to produce a compatible configuration by linking the off-the-shelf results on both traditional waverider techniques and inward turning inlet techniques. A series of geometry generations and optimization solutions is proposed to enhance the lift-to-drag ratio. A quantitative but efficient aerodynamic performance evaluation approach （the hypersonic flow panel method） with lower computational cost is employed to play the role of objective function for opti- mization purpose. The produced geometry compatibility with a computational fluid dynamics （CFD） solver is also verified for detailed flow field investigation. Optimization results and other numerical validations are obtained for the feasibility demonstration of the proposed method.
基金Project supported by the National Natural Science Foundation of China(No.11702322)the Natural Science Foundation of Hunan Province,China(No.2018JJ3589)。
文摘When considering the practical engineering application of a waverider,the on-design and off-design aerodynamic characteristics of the design conditions,especially the lift-to-drag ratio and the stability,deserve attention.According to recently studies,the planform and rear sight shape of a waverider are closely related to the above aerodynamic performance.Thus,the planform leading-edge profile curve used to design the planform shape of a vehicle is applied to designing an osculating cone waverider.Two key parameters concerned in planform and rear sight shape,namely the plan view sweep angle of the leading edge and the dihedral angle of the underside are introduced to the waverider design process.Each parameter is inserted in the control curve equation.Especially,a parameterization scheme is put forward for the free adjustment of the sweep angle along the leading edge.Finally,three examples are generated for verification and investigation.After the verification process based on the inviscid flow field of one case,the influences of the sweep and dihedral angles on the lift-to-drag ratio and the lateral static stability are evaluated,and meaningful results are obtained.Based on these results,we can conclude that,considering the maximum lift-to-drag ratio,the sweep angle plays a role on the lift-to-drag ratio only at subsonic and trans/supersonic speed as a negligible effect is observed at hypersonic speeds,whereas the dihedral angle is seem to produce a relevant difference at hypersonic speeds.Considering the lateral static stability,the dihedral angles have more influence on the waverider than the sweep angles.
文摘An experiment of a hypersonic vehicle configuration was conducted. The pressure difference of forbody precornpress surface is small. Pressure difference of three monitor points are 25.2%, 20. 5% and 17.29% respectively in the design condition. It indicates that there is crosswise flow in forebody boundary layer. Pressure difference at Ma = 6. 971 is lower than those of two other Mach number conditions. It indicates that the tested configuration has good aerodynamic performance in high Maeh number. Angle of attack has no great influence on the pressure difference. In almost all the angle of attack conditions, the pressure difference at Ma =6. 971 is slightly smaller than that in Ma =5. 993. The difference in the third precompress surface is slightly smaller than those in two others.
文摘Developing the waverider based hypersonic vehicles is an inverse design process in which shape is developed from a known flow field by tracing of streamlines to form a stream surface. The flow field can be based on a solution of Taylor Maccoll equation for a specified shock or cone angle. This Paper discusses the development of waverider shapes for hypersonic reentry vehicles.
基金co-supported by the Foundation of Science and Technology on Space Physics Laboratory,China(No.SPL2025002)the Key R&D Projects of Hunan Province,China(No.2023GK2022)。
文摘Compared with conventional vehicles,waverider is expected to overcome the limitations of lift-to-drag ratio in hypersonic conditions and considered one of the most promising configurations for hypersonic vehicles.Typically,waverider exhibits good aerodynamic performance under the design condition.However,maintaining such performance under off-design condition is challenging,leading to insufficient aerodynamic performance across a wide range of speed.This paper first proposes a novel design method for double swept waverider,where lift exhibits nonlinear growth with an increasing angle of attack and generates strong surface vortex lift at low speeds.These characteristics effectively accommodate both high-speed and low-speed conditions,improving waverider performance under off-design condition across a wide range of speed.The curvedcone-derived waverider design based on the projection approach enables simultaneous control of the basic flow field and planform contour,addressing the limited design space issue of conventional methods while enhancing aerodynamic performance under the design condition.Furthermore,to achieve optimal wide-speed-range performance,an aerodynamic estimation method is developed and combined with an improved multi-objective cuckoo search algorithm for optimization.Subsequently,the numerical method is applied to the optimized representative configurations under the hypersonic condition and the expected aerodynamic performance is obtained.The subsonic aerodynamic performance of waverider is also investigated.The double swept waverider in this research generates strong vortex lift and ideal longitudinal static stability performance at subsonic speed,which optimizes the wide-speed-range aerodynamic performance.
基金supported by the National Natural Science Foundation of China(Nos.U21B6003,U20A2069,and 12202372)the China Postdoctoral Science Foundation(No.2022M712653)。
文摘Waverider design based on osculating theory presents two critical issues:robust specification of design curves and accurate solution of the basic flowfield.Although the existing parametric approaches have advanced rapid configuration generation through geometric parameterization frameworks,they critically neglect the inherent coupling between aerodynamic constraints and geometric design parameters.To overcome this limitation,an Aerodynamics-Informed Parametric(AIP)method is developed by analytically deriving three waverider design curves and integrating them with the second-order curved shock theory.This method enables rapid waverider surface design while accounting for inflow conditions and shock wave geometry.Three typical waveriders,each featuring distinct combinations of design curves as inputs,are constructed and evaluated through inviscid and viscous numerical simulations to validate the applicability and accuracy of the AIP method.The results indicate that waveriders derived using the AIP method successfully reproduce the preassigned shock waves and original flowfields.Compared to traditional waverider design techniques based on the method of characteristics,the AIP method reduces computation time by approximately 94%,while maintaining errors in the inviscid lift-to-drag ratio,viscous lift-to-drag ratio,and volumetric efficiency below 0.1%,4.0%,and 0.1%,respectively.Additionally,a specially designed model is fabricated for the wind-tunnel tests to analyze the hypersonic aerodynamic performance of the waverider.Both numerical and experimental results confirm the feasibility of the AIP method,making it a promising candidate for waverider design and optimization.
基金Supported by the National Natural Science Foundation of China(Grant No.90405009)
文摘A new hypersonic inlet named three-dimensional section controllable internal waverider inlet is presented in this paper to achieve the goal of section shape geometric transition and complete capture of the upstream mass. On the basis of the association between hypersonic waverider airframe and streamtraced hypersonic inlet, the waverider concept is extended to yield results for the internal flows, namely internal waverider concept. It is proven theoretically that not osculating cones but osculating axisymmetric theory is appropriate for the design of section controllable internal waverider inlet. And two design methods out of the internal waverider concept are proposed subsequently to construct two inlets with specific section shape request, triangle to ellipse and rectangle to ellipse ones. The calculation results show that the inlets are capable of keeping their shock structures and the main flow characteristics exactly as their derived flowfield. Further, the inlets successfully capture all the upstream mass despite their complicated cross-section transitions. It is believed that the concept proposed ex- plores a new way of designing three-dimensional hypersonic inlets with special demand of section shape transition. However, the detailed flow characteristic and the performance of the internal waverider inlets are still under investigation.
基金Supported by the National Natural Science Foundation of China (Grant No. 10772186)the Key Foundation of National Natural Science Foundation of China (Grant No. 90505016)
文摘Waverider generated from a given flow field has a high lift-to-drag ratio because of attached bow shock on leading edge. However, leading edge blunt and off-design condition can make bow shock off leading edge and have unfavorable influence on aerodynamic characteristics. So these two problems have always been concerned as important engineering science issues by aeronautical engineering scientists. In this paper, through respectively using low speed and high speed waverider design principles, a wide-speed rang vehicle is designed, which can level takeoff and accelerate to hypersonic speed for cruise. In addition, sharp leading edge is blunted to alleviated aeroheating. Theoretical study and wind tunnel test show that this vehicle has good aerodynamic performance in wide-speed range of subsonic, transonic, supersonic and hypersonic speeds.
基金supported by the National Natural Science Foundation of China(Grant No.11502291)
文摘Wide-speed-range gliding vehicle(WSRGV) is designed to adapt to the variable cruising environment that hypersonic vehicles will encounter during the mission implementation. Based on the cone-derived theory, a novel design technique of WSRGV has been developed. Theoretically, the functional relationship between cone-derived waverider’s volumetric efficiency and its design Mach number can be built through sampling approach as long as the geometries of design conical shock wave and the upper base curve are fixed. Based on the functional relationship, a cone-derived waverider that owns the same volumetric efficiency with a giving WSRGV can be acquired. This paper compared the aerodynamic performance between WSRGV and the cone-derived waverider sharing the same volumetric efficiency in a wide Mach number range. Their aerodynamic properties versus angle of attack have also been compared under the waverider’s design Mach number. The obtained result shows that WSRGV shares similar aerodynamic performance with the cone-derived waverider with the same volumetric efficiency. The aero-surfaces in the margin area of this kind of configuration have a larger contribution to the lift-to-drag ratio in comparison with the aero-surfaces in the central area. The configuration with a thick central body and thin margin place owns not only better aerodynamic performance but also better loading property.
基金This study was supported in part by the National Natural Science Foundation of China(No.61903146).
文摘For its outstanding aerodynamic capabilities,the integrated design of the waverider and inlet is widely accepted in hypersonic aircraft.Three aspects of the integrated design of the waverider and inlet since 2020 are mainly described in this paper.Firstly,the advantages and shortcomings of the conventional integrated design are examined.Then,different layouts of integrated design are proposed,and the aerodynamic perfor-mance optimization methods of the waverider,inlet,and their coupling are introduced.Besides,a series of methods for increasing the calculating accuracy of the waverider and inlet are presented,and the focus of attention is to consider the lateral flow problem.
基金support of the National Natural Science Foundation of China(No.11672183).
文摘In the future,aircraft will have both high flight speed and high stealth characteristics,and its detection will become a complex problem.However,the disturbance generated by the high-speed aircraft is evident in its tail flow field,which can be treated as a new feature.In this paper,the flow field of a Waverider at different attitudes and speeds is investigated.By observing the deflection of a 532 nm light beam incident in different directions,the relationship between deflection magnitude and the Waverider’s attitude is established.As a result,the light will deflect most(8.82×10^(−5) rad/s)whenWaverider with a 6 Ma flying speed and 0 angle of attack.While the mini deflection occurs whenWaverider flies at 4 Ma speed and with a 10◦angle of attack.By analyzing different conditions,this paper points out that the traveling length of light and magnitude of the scalar gradient in wake most positive correlate to the light deflection angle.As speed goes up,the wake becomes narrow,but the scalar gradient rises so that the light deflects most atMa6.As the incident of light goes closer to horizon direction,its traveling length in wake rises,the max deflection usually with a corresponding incident direction of 20◦.
文摘An inverse method of characteristics was introduced into the design concept of using osculating cones (OC) in the supersonic flow, which can extend the domain of options for generating the aerospace vehicle configurations with supersonic leading edge as well as inlet diffusers. Some more practical waverider shapes with higher volumetric efficiency can be obtained through using the concept of osculating axisymmetric (OA) flows with rotationality in the post shock flow field by inputting curved shocks.
基金supported by the National Natural Science Foundation of China (Grant No. 90916013)the guidance and help from Academician Li Tian and peer reviewers are gratefully acknowledged
文摘To aim at design requirements of high lift-to-drag ratio as well as high volumetric efficiency of next generation hypersonic airplanes,a body-wing-blending configuration with double flanking air inlets layout is presented.Moreover,a novel forebody design methodology which by rotating and assembling two waverider-based surfaces is firstly introduced in this paper.Some typical configurations are designed and their aerodynamic performances are evaluated by computational fluid dynamics.The results for forebodies analysis show that large volumetric efficiency,high lift-to-drag ratio,and uniformly distributed flowfield at the inlet cross section can be assured simultaneously.Furthermore,results of numerical simulation of four integrated configurations with various leading edge shapes,including three power-law curves and a cosine curve clearly show the advantage of high lift-to-drag ratio.Besides,the high pressure generated by the side wall of the airframe can be partly captured by the reasonably designed wings in the condition of small flight attack angle.Then the order of lift-to-drag ratio of four configurations at 0 degree flight attack angle is completely different from the condition of 4-degree flight attack angle.This result demonstrates that the curve shape of the leading edge is very important for the lift-to-drag ratio of the aircraft,and it should be further optimized under the cruising attack angle in future work.
