TY - CHAP
T1 - A design method for the construction of hypersonic vehicle configurations
AU - Ferguson, Frederick
AU - Chandra, Suresh
AU - Blankson, Isaiah
AU - Anderson,, Jr, John, Unknown First Name
AU - Kothari, Ajay
N1 - Publisher Copyright:
© 1995 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
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 -