A design method for the construction of hypersonic vehicle configurations

Frederick Ferguson; Suresh Chandra; Isaiah M Blankson; J. Anderson, Jr; Ajay Kothari; Mookesh Dhanasar; Unknown First Name Anderson,, Jr, John

A design method for the construction of hypersonic vehicle configurations

Frederick Ferguson
, Suresh Chandra
, Isaiah M Blankson
, J. Anderson, Jr
, Ajay Kothari
, Mookesh Dhanasar
, Unknown First Name Anderson,, Jr, John

Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Chapter

Abstract

In this paper, a new class of waverider configurations are generated by specifying an arbitrary 3-D bow shock wave shape, wing leading-edge and inlet curves. This inverse design approach makes use of a new tool based on a semi-analytical/numerical method for solving the Euler equations coupled to a special form of grid generation. In the waverider design space, the aerodynamic figure of merit (maximum C_L, minimum C_D, maximum L/D, etc.) is considered a function of the shapes of both shock wave and leading-edge curve. The shock shape is defined by eight parameters and the wing lead-edge by an additional parameter. A constrained optimization problem is then solved. Both in viscid and viscous solutions are obtained, The method yields advanced, realistic and practical vehicle shapes and acceptable volumetric efficiencies. It is computationally rapid and permits parametric studies to be done quickly. Several optimized configurations with integrated combustion chambers for flight conditions of Mach 10 and 30 km altitude are presented.

Original language	English
Title of host publication	International Aerospace Planes and Hypersonics Technologies
Pages	6009
State	Published - 1995

Cite this

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title = "A design method for the construction of hypersonic vehicle configurations",

abstract = "In this paper, a new class of waverider configurations are generated by specifying an arbitrary 3-D bow shock wave shape, wing leading-edge and inlet curves. This inverse design approach makes use of a new tool based on a semi-analytical/numerical method for solving the Euler equations coupled to a special form of grid generation. In the waverider design space, the aerodynamic figure of merit (maximum CL, minimum CD, maximum L/D, etc.) is considered a function of the shapes of both shock wave and leading-edge curve. The shock shape is defined by eight parameters and the wing lead-edge by an additional parameter. A constrained optimization problem is then solved. Both in viscid and viscous solutions are obtained, The method yields advanced, realistic and practical vehicle shapes and acceptable volumetric efficiencies. It is computationally rapid and permits parametric studies to be done quickly. Several optimized configurations with integrated combustion chambers for flight conditions of Mach 10 and 30 km altitude are presented.",

author = "Frederick Ferguson and Suresh Chandra and Blankson, \{Isaiah M\} and \{Anderson, Jr\}, J. and Ajay Kothari and Mookesh Dhanasar and \{Anderson,, Jr, John\}, \{Unknown First Name\}",

year = "1995",

language = "English",

pages = "6009",

booktitle = "International Aerospace Planes and Hypersonics Technologies",

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TY - CHAP

T1 - A design method for the construction of hypersonic vehicle configurations

AU - Ferguson, Frederick

AU - Chandra, Suresh

AU - Blankson, Isaiah M

AU - Anderson, Jr, J.

AU - Kothari, Ajay

AU - Dhanasar, Mookesh

AU - Anderson,, Jr, John, Unknown First Name

PY - 1995

Y1 - 1995

N2 - In this paper, a new class of waverider configurations are generated by specifying an arbitrary 3-D bow shock wave shape, wing leading-edge and inlet curves. This inverse design approach makes use of a new tool based on a semi-analytical/numerical method for solving the Euler equations coupled to a special form of grid generation. In the waverider design space, the aerodynamic figure of merit (maximum CL, minimum CD, maximum L/D, etc.) is considered a function of the shapes of both shock wave and leading-edge curve. The shock shape is defined by eight parameters and the wing lead-edge by an additional parameter. A constrained optimization problem is then solved. Both in viscid and viscous solutions are obtained, The method yields advanced, realistic and practical vehicle shapes and acceptable volumetric efficiencies. It is computationally rapid and permits parametric studies to be done quickly. Several optimized configurations with integrated combustion chambers for flight conditions of Mach 10 and 30 km altitude are presented.

AB - In this paper, a new class of waverider configurations are generated by specifying an arbitrary 3-D bow shock wave shape, wing leading-edge and inlet curves. This inverse design approach makes use of a new tool based on a semi-analytical/numerical method for solving the Euler equations coupled to a special form of grid generation. In the waverider design space, the aerodynamic figure of merit (maximum CL, minimum CD, maximum L/D, etc.) is considered a function of the shapes of both shock wave and leading-edge curve. The shock shape is defined by eight parameters and the wing lead-edge by an additional parameter. A constrained optimization problem is then solved. Both in viscid and viscous solutions are obtained, The method yields advanced, realistic and practical vehicle shapes and acceptable volumetric efficiencies. It is computationally rapid and permits parametric studies to be done quickly. Several optimized configurations with integrated combustion chambers for flight conditions of Mach 10 and 30 km altitude are presented.

M3 - Chapter

SP - 6009

BT - International Aerospace Planes and Hypersonics Technologies

ER -

A design method for the construction of hypersonic vehicle configurations

Abstract

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