Numerical simulations are used to study the aerodynamic inlet properties of three axisymmetric configurations of laser‐propelled Lightcraft vehicles operating at subsonic, transonic and supersonic speeds up to Mach 5. The 60 cm vehicles were sized for launching 0.1–1.0 kg nanosatellites with combined‐cycle airbreathing/rocket engines, transitioning between propulsion modes at roughly Mach 5–6. Results provide the pressure, temperature, density, and velocity flowfields around and through the three representative vehicle/engine configurations, as well as giving the resulting ram drag and total drag coefficients—all as a function of flight Mach number. Simulations with rotating boundaries were also carried out, since for stability reasons, Lightcraft are normally spun up before lift‐off. Given the three alternatives, it is demonstrated that the optimal geometry for minimum drag is the configuration with a parabola nose; hence, these inlet flow conditions are being applied in subsequent “direct connect” 2D laser propulsion experiments in a small transonic flow facility.
Inlet Aerodynamics and Ram Drag of Laser‐Propelled Lightcraft Vehicles
BEAMED ENERGY PROPULSION: 6th International Symposium ; 2009 ; Scottsdale (Arizona)
AIP Conference Proceedings ; 1230 , 1 ; 41-60
06.05.2010
20 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Inlet Aerodynamics and Ram Drag of Laser-propelled Lightcraft Vehicles
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