subsonic flow sentence in Hindi
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- Supersonic flow behaves very differently from subsonic flow.
- In a subsonic flow the gas is compressible, and sound will propagate through it.
- Unlike in subsonic flow, the supersonic flow accelerates as it moves away from the throat.
- Because of the subsonic flow, there is no bow shock off the trailing hemisphere of Ganymede.
- For subsonic flow, the flaps are completely closed and for supersonic flow, the flaps are open.
- This subsonic flow then decelerates through the remainder of the diverging section and exhausts as a subsonic jet.
- Subsonic flows are often assumed to be incompressible, i . e . the density is assumed to be constant.
- In subsonic flow, steeply swept and narrow wings are inefficient compared to a high-aspect-ratio wing.
- For high subsonic flows, the Critical Mach number ( M 1cr ) is a characteristic value of considerable importance.
- Supersonic flow jumps over it by means of ramps, while subsonic flow is able to turn and exit through the gap.
- This means that a subsonic flow entering a duct with friction will have an increase in its Mach number until the flow is choked.
- If the gas within a scramjet goes below Mach 1 the engine will " choke ", transitioning to subsonic flow in the combustion chamber.
- The flow pattern is exactly the same as in subsonic flow, except that the flow speed at the throat has just reached Mach 1.
- In case of subsonic flows the disturbances will travel faster than the source and the argument of the \ arcsin ( ) function will be greater than one.
- Through the 1940s and 1950s he continued to develop this theory, and to use it to study the planar elliptic partial differential equations associated with subsonic flows.
- The Rayleigh flow model reaches maximum entropy at M = 1.0 For subsonic flow, the maximum value of H occurs at M = 0.845.
- At Brown, he began working on problems of fluid dynamics, and in particular on the two-dimensional subsonic flows associated with cross-sections of airfoils.
- Combining the above with the expression for Mach number gives an expression for TAS as a function of impact pressure, static pressure and static air temperature ( valid for subsonic flow ):
- For subsonic flow, pitot pressure is equal to the stagnation pressure ( or total pressure ) of the flow, and hence the term pitot pressure is often used interchangeably with these other terms.
- In more detail ( in the ZND model ) in the frame of the leading shock of the detonation wave, gases enter at supersonic velocity and are compressed through the shock to a high-density, subsonic flow.
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