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
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
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
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 e...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
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
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
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
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
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.
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 (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.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.
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.
