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Both the experimental and computational results indicate that an accompanied gas jet can significantly enhance liquid jet penetration.
Simulation results also indicate that gas injection would cause additional total pressure losses.
originally posted by: Ninjastrikeforce
I saw and heard a few interesting things in the 1990s too.
originally posted by: Ninjastrikeforce
The other sighting was a high-altitude, pulsing light. I’d seen in multiple times from about 99-2005. It looked and moved much like a satellite, but blinked at about 2-second intervals as it crossed the sky. It was always very high and I assume very fast, silent, and going horizon-to-horizon in about 30 seconds. Maybe it was a tumbling satellite? I’d seen it a few times.
we in IRAQ saw fast light flying for many times and in deferent high speed and altitoud.its not UFO because it flashes when it passes like take a photo and this hapened in the end of 90s and until the last war in 2003 and there is no new flying of these (craft) since the end of war
it,s compared with fighters speed .and I did,t say that I saw aircraft ,what I talk about it is flying object with white light in the night flying in the in sky in different zone like aircraft and flasheing lihgt I see it for many times but all what I see it was in the night not in the daylight.the other things here that I ask some offesers in the Iraqi airforce in that time about these objactse and the answer was that they don,t know any thing about it and no detect from Iraqi radars for these objects . and not just me saw these objects but many people also saw this light and told me about it .may as you said it,s SR-71 taken out of retierment for this role but it,s uninvesible to radars.
Mixing and combustion characteristics in an ethylene fueled cavity-based scramjet combustor with different injection schemes are investigated experimentally and numerically in low equivalence ratio conditions, with inflow conditions of Ma = 2.52, stagnation pressure P0 = 1.65 MPa and stagnation temperature T0 = 1600 K. The wall-pressure distributions obtained by numerical simulations are in fairly good agreement with the experimental data. The numerical results also indicate that multiple-orifice cases have higher mixing efficiencies and combustion efficiencies than single-orifice cases. In addition, it is observed in the experiments that flamebases are not stabilized in a fixed position. In single-orifice cases, the flamebases oscillate dramatically between the cavity leading edge and trailing edge, and the oscillations are similar for different injection pressures. In multiple-orifice cases, the flamebases oscillate slightly in the cavity shear layer just downstream of the leading edge and the amplitudes with lower injection pressure are larger than those with higher injection pressure.
A 3D numerical model of a combustion chamber with continuous rotating detonation wave was performed. The ignition, onset and stabilization of a rotating detonation wave in combustion chambers of different shapes was investigated. The effect of additional oxygen injection on the onset of rotating detonation wave was studied. Formation of a stable detonation wave was investigated against different factors: internal body diameter, injectors number and diameter, pressure at the fuel and oxidizer orifices. The calculations were performed using specialized computer code designed by the Authors at the APK-5 super-computer system.
originally posted by: anzha
Three-dimensional modeling of rotating detonation in a ramjet engine
Authors:
Smirnov et al
Abstract:
A 3D numerical model of a combustion chamber with continuous rotating detonation wave was performed. The ignition, onset and stabilization of a rotating detonation wave in combustion chambers of different shapes was investigated. The effect of additional oxygen injection on the onset of rotating detonation wave was studied. Formation of a stable detonation wave was investigated against different factors: internal body diameter, injectors number and diameter, pressure at the fuel and oxidizer orifices. The calculations were performed using specialized computer code designed by the Authors at the APK-5 super-computer system.
www.sciencedirect.com...
A novel approach to improve the performance of supersonic and hypersonic intake systems with nano-particle injection has been studied. A parametric study using Mach number (M∞), Stokes number (Stk), particle Eckert number (Ecp), and thermal transport number (αt) was conducted across a quasi-1D converging-diverging (C-D) supersonic intake at idealized and single-shock compression cases. Gains in stagnation pressure recovery were achieved for both the cases. Gains were observed in the idealized compression case when: Ecp>0.25 and αt>0.5 for a Mach number of 2.5; and Ecp>0.5 and αt>0.7 for a Mach number of 5. The results also showed that a combination of cooling, momentum exchange, and particle size is required to enhance intake performance. A rectangular mixed-compression intake at Mach 3 was simulated using an unsteady compressible gas-particle CFD solver in OpenFOAM. CFD simulations with nano-particle injection predicted a 16% gain in the exit pressure recovery.