group
What campus are you from?
Daytona Beach
Authors' Class Standing
Mary Zoeller, Senior Rachael Mahan, Senior Braeden Caropresso, Senior Aleko Khundadze, Sophomore Johnathan Sayles, Senior Kevin Nadolne, Senior Jonah Ortwein, Sophomore Jose Demedeiros, Senior Alex Lanpher, Senior
Lead Presenter's Name
Mary Zoeller
Faculty Mentor Name
William Engblom
Abstract
This study presents a delta wing body for the UCAH Undergraduate Hypersonic Flight Design Competition, optimized for maximum low altitude range while meeting strict requirements on Mach number, stability, thermal survivability, size, mass, and maneuver capability. The configuration blends a blunted diamond nose with a moderately swept delta planform to harness vortex lift, preserve internal volume for structure and controls, and manage aeroheating through appropriate leading edge radius and skin thickness. Capability targets include sustained flight between Mach 5 and Mach 8 and a minimum 15 g turn, with a maximum diameter of 20 centimeters, a maximum mass of 45 kilograms, and a payload mass of 9 kilograms. Aerodynamic performance is screened with modified Newtonian and local inclination methods with viscous corrections, then refined using compressible turbulent CFD across the operating envelope to establish forces, moments, and stability margins. A first order aeroheating assessment informs material selection suitable for low altitude operation. A six degree of freedom trajectory model enforces the altitude ceiling and reports downrange performance to guide control surface allocation and mass distribution. The symposium presentation will summarize key trade studies in sweep, thickness, leading edge shaping, and control sizing, and outline validation plans using CFD, trajectory analysis, and wind tunnel or gun launch testing.
Did this research project receive funding support from the Office of Undergraduate Research.
No
High-Range Delta-Winged Hypersonic Projectile Concept for Low-Cost Production
This study presents a delta wing body for the UCAH Undergraduate Hypersonic Flight Design Competition, optimized for maximum low altitude range while meeting strict requirements on Mach number, stability, thermal survivability, size, mass, and maneuver capability. The configuration blends a blunted diamond nose with a moderately swept delta planform to harness vortex lift, preserve internal volume for structure and controls, and manage aeroheating through appropriate leading edge radius and skin thickness. Capability targets include sustained flight between Mach 5 and Mach 8 and a minimum 15 g turn, with a maximum diameter of 20 centimeters, a maximum mass of 45 kilograms, and a payload mass of 9 kilograms. Aerodynamic performance is screened with modified Newtonian and local inclination methods with viscous corrections, then refined using compressible turbulent CFD across the operating envelope to establish forces, moments, and stability margins. A first order aeroheating assessment informs material selection suitable for low altitude operation. A six degree of freedom trajectory model enforces the altitude ceiling and reports downrange performance to guide control surface allocation and mass distribution. The symposium presentation will summarize key trade studies in sweep, thickness, leading edge shaping, and control sizing, and outline validation plans using CFD, trajectory analysis, and wind tunnel or gun launch testing.