Explore hypersonic waverider geometries using two inverse design methods. Configure flow conditions, visualize in 3D, and export starting geometries for further optimization, directly in your browser.
Cone Derived (SHADOW) · Mach 6.0 · β 12°A waverider is a hypersonic vehicle designed so that its bow shockwave attaches along the entire leading edge, trapping high pressure air beneath the vehicle. This eliminates flow spillage from the lower to upper surface, producing exceptionally high lift to drag ratios at hypersonic speeds.
First proposed by Nonweiler in 1959, the concept has been central to programs like the Boeing X-51 Waverider, which demonstrated scramjet powered flight at Mach 5+. Designing these vehicles requires an inverse approach: define the desired shockwave first, then derive the geometry that produces it.
This tool implements two such inverse design methods, allowing you to generate and compare waverider configurations across a range of flow conditions, with STEP and STL export for further analysis.
Switch between methods to explore different regions of the design space. Each implements a distinct inverse design approach from published research.
Approximates the 3D flow field as a spanwise combination of local conical flows, each defined on its own osculating plane. This enables arbitrary shockwave cross sections and greater design freedom than a single cone allows. The implementation uses a Bezier parameterized approach with four design variables (X1 to X4) controlling shockwave curvature and upper surface geometry.
Son, J., Son, C., & Yee, K. (2022). A Novel Direct Optimization Framework for Hypersonic Waverider Inverse Design Methods. Aerospace, 9(7), 348.
doi.org/10.3390/aerospace9070348
Kontogiannis, K., Sóbester, A., & Taylor, N. (2017). Efficient Parameterization of Waverider Geometries. J. Aircraft, 54(3).
doi.org/10.2514/1.C033902
Projects polynomial leading edge curves onto a conical shock structure and traces streamlines through the Taylor-Maccoll flow field to generate the compression surface. The leading edge is parameterized using nth order polynomials, providing intuitive control over the planform shape, as implemented in the Stability of Hypersonic Aerodynamic Derivatives Of Waveriders (SHADOW) framework by Adam Weaver.
Weaver, A. S. (2025). Investigating Stability of Cone Derived Hypersonic Waverider Vehicles via Design Space Exploration. Master's Thesis, Utah State University.
digitalcommons.usu.edu/etd2023/485
A browser based design tool. No installation, no registration.
Switch between Osculating Cones and Cone Derived generation per run.
Set Mach number and shock angle with automatic range validation and cone angle computation.
Polynomial coefficients (SHADOW) or Bezier sliders (Osculating Cones) with live design space validation.
Inspect waveriders from any angle. Toggle upper/lower surface, leading edge, wireframe, and CG.
Download as STEP or STL with coarse, medium, or fine mesh density settings.
Shock angle, cone half angle, post shock Mach, planform area, volume, and center of gravity.
The Waverider Designer is the starting point. Take your design further.
Quick geometry exploration.
Build intuition, compare configurations.
DSMC, CFD, aerothermal simulation.
From preliminary geometry to flight ready design.
No registration required. A starting point for your hypersonic design.