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engine
The engine current distribution along the duct is found for various values of a turbulent viscosity on the boundary of the gasdynamic boundary layer which affect the laminar-turbulent transition point.
      
Laboratory Simulation of Electric Current Formation in Aircraft Jet Engine Ducts
      
The electric current formation in aircraft jet engine ducts and the electric current flowing into the gas dynamic wake behind a heated blade have been simulated experimentally.
      
Two models were used in the experiments: a cylindrical metal channel through which a high-temperature gas flows and a metal blade (from a blade engine) in a high-temperature jet.
      
The dependence of the electric engine current on the air flow rate in the wake is given.
      
Theory of Disappearance of the Electric Signal Induced by an Aircraft Jet Engine in the Afterburner Regime
      
Electrical aspects of aircraft jet engine operation are considered.
      
A phenomenon previously observed experimentally, namely, the disappearance of the engine current and alternating electric signal induced by the engine jet in the afterburner regime, is explained.
      
As a result, the engine current circuit is closed on the internal duct walls and engine charging becomes insignificant.
      
Determining the Optimal Contour of a Three-Dimensional Supersonic Jet Engine Outlet System
      
The problem of determining the optimal contour of a two-dimensional jet engine outlet system was solved in [1] using the direct method of the calculus of variations.
      
Electric Charging of Soot Particles in Aircraft Engine Exhaust Plumes
      
These conditions correspond to the use of jet engines, including a bypass turbojet gas generator, operating in steady mode, as well as a pulsed detonation rocket engine, as the high-pressure gas source.
      
Distinctive Features of the Flow past a Flight Vehicle Integrated with an Air-Breathing Engine at High Supersonic Velocities
      
Numerical modeling of the formation of aerosol particles in jet engine plumes
      
The structure and the properties of the air flow developing when an intake system (in particular, a turbojet engine) operates near a surface are studied.
      
Electric Diffusion Processes on a High-Temperature Turbine Blade and Its Contribution to the Aircraft Engine Current
      
With a mass flow rate of 50 g/s, the engine may develop a propulsive force of 2000 N.
      
The Thermal Correction of the Inlet Diffuser of a Hypersonic Scramjet Engine
      
Shock-wave modes of flow at the inlet to the diffuser of a hypersonic scramjet engine: The effect of flight altitude and velocit
      
 

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