Oxidizer feed-system coupled instabilities have been observed in several liquid and hybrid propellant rocket engines, although they are not likely to be catastrophic for the latter. However, severe pressure oscillation in hybrid rocket may result in a ...

A predictive numerical approach, based on Reynolds-averaged Navier–Stokes simulations including the effects of turbulence, chemistry, fluid/surface interaction, and radiation, has been developed for paraffin-wax/oxygen hybrid rocket engines. A recently ...

A numerical investigation of the performance of a supersonic combustor designed for a flight Mach 8 is presented. Numerical simulations are used to assess the characteristics and operational limits of the combustor at design and off-design conditions. The ...

It has been recognized in recent years that high-altitude atmospheric ice crystals pose a threat to aircraft engines in flight. It is believed that ice can accrete inside the core compressor, although the mechanism by which this occurs remains poorly ...

A liquid bipropellant rotating detonation rocket engine was successfully test fired. The 6.5-in.-diam engine operates on a mixture of rocket-grade hydrogen peroxide and triglyme. Ignition is accomplished hypergolically, with the addition of a promoter to ...

Iron oxide is the most common catalyst in solid rocket propellant. Increased performance of propellant by encapsulating iron oxide particles within ammonium perchlorate (AP) has been previously demonstrated, but only nanoscale particles were used, and ...

Hybrid rockets have several advantages with respect to current propulsion systems like simplicity, safety, reliability, environmental friendliness, and lower cost. To size the combustion chamber, it is fundamental to understand how the length, the ...

Three different heat exchangers (copper metal foam, copper disks, and stainless-steel disks) with lower effective surface areas than nominal catalysts used in thrusters were tested for nitrous oxide decomposition. These heat exchangers were preheated to ...

A novel diode laser-based ignition technique for hybrid propulsion systems has been developed. In an effort to determine the physical ignition mechanism, a test series was conducted in an optically accessible, slab-burning combustion chamber. High-speed ...

A high-power nested Hall thruster was operated with cathode flow fractions from 7 to 3% of the total anode flow rate in a two-channel operating configuration at 27 kW total discharge power. The thruster was operated with a state-of-the-art high-current ...

The effect of Tandem-Hole configuration on penetration and combustion in supersonic crossflow was studied using three injectors having two tandem holes of 0.7 mm diameter with a spacing of 5, 10, and 14 mm. A Single-Hole injector with the same injection ...

The combustion enhancement by ozone has been studied for single-component fuels in many different settings; however, the impact of ozone addition on a multicomponent fuel has been experimentally underexplored. This paper investigates the ozone-assisted ...

Flame behavior at conditions approaching boundary layer flashback was studied in fuel-lean premixed swirl flames with a central bluff-body flame holder. High-speed OH* chemiluminescence images were collected at over 450 different combinations of fuel ...

A pulsed electric thruster named Pulsed Electrogasdynamic (PEG) thruster was investigated. In this thruster, the propellant gas is accelerated gasdynamically to high exhaust velocities (10–15  km/s) by pulsed electric discharge. Laboratory models of the PEG thruster ...