Practical considerations in waverider applications

Stevens, Daniel R.

doi:10.2514/6.1992-4247

Cited by 11 publications

(10 citation statements)

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“…Thus, high-pressure region of the lower surface generates compression lift, which leads to high L/D. However, waverider has several practical issues 7) , such as aerodynamic heating, off-design characteristics, longitudinal and directional stability, low-speed aerodynamic characteristics.…”

Section: Waverider Conceptmentioning

confidence: 99%

Study of Waverider-based Point-to-Point Suborbital Rocketplane

Takama

Ishimoto

2012

AEROSPACE TECHNOLOGY JAPAN

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As a high-speed manned transportation system in the future, point-to-point (P2P) suborbital rocketplane is currently studied in Japan Aerospace Exploration Agency (JAXA) space transportation mission directorate. The vehicle was designed on the basis of the concept of waverider allowing high L/D in hypersonic regime, which is required for longer flight range and smaller load factor. Compared with an ideal waverider, the designed P2P suborbital rocketplane has outer wings for the improvement of the low-speed aerodynamic performance, finite thickness in the leading edge for the reduction of the aerodynamic heating, and twin vertical tails for directional stability. The aerodynamic performance of the P2P vehicle was investigated through numerical simulation of both subsonic and hypersonic flows, and the baseline aerodynamic shape of the P2P vehicle was discussed. The L/D in the trim condition at hypersonic speed was 2.6.

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Section: Waverider Conceptmentioning

confidence: 99%

Study of Waverider-based Point-to-Point Suborbital Rocketplane

Takama

Ishimoto

2012

AEROSPACE TECHNOLOGY JAPAN

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“…However, with engine integration, the lift-to-drag ratio of the waverider is expected to be much lower than that of the pure aerodynamic configuration [8]. As a result, over the past 50 years, engine-airframe integration methodologies for the hypersonic waverider vehicle have been extensively studied by many researchers [9][10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25]. As a first step in the engine-airframe integration presented herein, inlet-airframe issues for waveriders are addressed.…”

Section: Introductionmentioning

confidence: 99%

“…There are two classes of general methodologies for utilising the waverider concept in a hypersonic vehicle design [9]. In the first class, the waverider is used only as the forebody of a vehicle, and it behaves as the pre-compression surface to efficiently provide the inlet system with the required compression flow field.…”

Section: Introductionmentioning

confidence: 99%

Novel inlet–airframe integration methodology for hypersonic waverider vehicles

et al. 2015

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“…Two classes of general theories and methods exist for using the waverider concept in the design of air-breathing hypersonic vehicles (1,4,16,17) . In the first class of methodologies, the waverider is used only as the vehicle's forebody, and it behaves as the precompression surface to efficiently provide the inlet with the required compression flow fields; therefore, this class of methodologies is termed the waverider forebody/inlet integration design methodology.…”

Section: Introductionmentioning

confidence: 99%

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

et al. 2019

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With the aims of overcoming the limitations of the existing basic flow model derived from an axisymmetric generating body and extending the aerodynamic design method of the airframe/inlet integrated waverider vehicle, this study develops an upgraded basic flow model derived from an axisymmetric shock wave. It then upgrades the design method for airframe/inlet integration of an air-breathing hypersonic waverider vehicle, which is termed the ‘full-waverider vehicle’ in this study. In this paper, first, the design principle and method for the upgraded full-waverider vehicle derived from an axisymmetric basic shock wave are described in detail. Second, an upgraded basic flow model that accounts for both internal and external flows is derived from an axisymmetric basic shock wave by use of both the streamline tracing method and the method of characteristics (MOC). Third, the upgraded full-waverider vehicle is developed from the upgraded basic flow model by the streamline tracing method. Fourth, the design theories and methodologies of both the upgraded basic flow model and the upgraded full-waverider vehicle are validated by a numerical computation method. Finally, the aerodynamic performances and viscous effects of both the upgraded basic flow model and the upgraded full-waverider vehicle are analysed by numerical computation. The obtained results show that the upgraded basic flow model and aerodynamic design method are effective for the design of the airframe/inlet integration of an air-breathing hypersonic waverider vehicle.

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Practical considerations in waverider applications

Cited by 11 publications

References 0 publications

Study of Waverider-based Point-to-Point Suborbital Rocketplane

Study of Waverider-based Point-to-Point Suborbital Rocketplane

Novel inlet–airframe integration methodology for hypersonic waverider vehicles

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

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