A new method for the design of inviscid waverider configurations with more general shock geometries than previously possible is presented. An arbitrary three-dimensional shock shape is specified as input, and a new inverse method, utilizing a cross-stream marching scheme for solving the Euler equations, is used to generate the postshock flowfield. Unlike most previous studies, this approach allows for the use of nonaxisymmetric shock topologies with nonconstant shock strengths. The problem's ill-posedness is suppressed by reformulating the problem in the proper curvilinear coordinate system. The inverse marching approach is briefly summarized, and details of the waverider design procedure are given. Comparisons of individual waveriders and their flowfields generated by the new algorithm in a few seconds on a workstation with flowfields computed by a direct Euler solver, requiring on the order of an hour of Cray 2 CPU time, demonstrate the accuracy and efficiency of the new approach.
[1]
George S. Springer,et al.
Hypersonic waverider configurations from the 1950's to the 1990's
,
1990
.
[2]
Kevin D. Jones,et al.
Hypersonic Waverider Design from Given Shock Waves.
,
1990
.
[3]
Kevin D. Jones,et al.
Hypersonic waverider analysis - A comparison of numerical and experimental results
,
1991
.
[4]
The Aerodynamic Design of Aircraft: A Detailed Introduction to the Current Aerodynamic Knowledge and Practical Guide to the Solution of Aircraft Design Problems
,
1978
.
[5]
Kevin D. Jones,et al.
Numerical simulations of high-speed flows about waveriders with sharp leading edges
,
1992
.
[6]
J. Steger,et al.
Numerical simulation of unsteady, viscous, high-angle-of-attack flows using a partially flux-split algorithm
,
1986
.
[7]
J. G. Jones.
A method for designing lifting configurations for high supersonic speeds using the flow fields of non-lifting cones
,
1963
.
[8]
T. R. F. Nonweiler,et al.
Aerodynamic Problems of Manned Space Vehicles
,
1959,
The Journal of the Royal Aeronautical Society.