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specific thrust वाक्य

"specific thrust" हिंदी मेंspecific thrust in a sentence
उदाहरण वाक्यमोबाइल
  • Turbofan exhaust gases induce additional air into the ejector via an auxiliary air intake, thereby reducing the specific thrust / mean jet velocity of the final exhaust.
  • If, however, the afterburner is to be hardly used, a low specific thrust ( low fan pressure ratio / high bypass ratio ) cycle will be favored.
  • At a fixed total applied fuel : air ratio, the total fuel flow for a given fan airflow will be the same, regardless of the dry specific thrust of the engine.
  • It's linked to from a wikified table in that article, as an example of a propulsion type which would have very low specific thrust designed to be applied over decades.
  • When lit, prodigious amounts of fuel are burnt in the afterburner, raising the temperature of exhaust gases by a significant degree, resulting in a higher exhaust velocity / engine specific thrust.
  • An SST VCE would have to increase the engine airflow substantially at take-off, to reduce the jet velocity at a given thrust ( i . e . a lower specific thrust)
  • A low ( dry ) specific thrust engine has a low tailpipe temperature, which means that the temperature rise across the afterburner can be high, giving a good thrust boost in afterburning.
  • The total fuel flow ( main combustor plus afterburner ) is fixed by the temperature rise from air intake to nozzle and, for a given airflow, changes little with dry specific thrust.
  • Ivchenko Lotarev chose a very low specific thrust ( net thrust / airflow ) cycle for the DV-2, so a single stage fan is sufficient to develop the desired fan pressure ratio.
  • Military turbofans, however, have a relatively high specific thrust, to maximize the thrust for a given frontal area, jet noise being of less concern in military uses relative to civil uses.
  • Thus civil turbofans today have a low exhaust speed ( low " specific thrust " & mdash; net thrust divided by airflow ) to keep jet noise to a minimum and to improve fuel efficiency.
  • However, a high specific thrust turbofan will, by definition, have a higher nozzle pressure ratio, resulting in a higher afterburning net thrust and, therefore, a lower afterburning specific fuel consumption ( SFC ).
  • The lower the specific thrust of a turbofan, the lower the mean jet outlet velocity, which in turn translates into a high thrust lapse rate ( i . e . decreasing thrust with increasing flight speed ).
  • Therefore, a future SST might well benefit from a variable cycle engine, where the specific thrust ( and therefore jet velocity and noise ) is low at take-off, but is forced high during supersonic cruise.
  • If the aircraft burns a large percentage of its fuel with the afterburner alight, it pays to select an engine cycle with a high specific thrust ( i . e . high fan pressure ratio / low bypass ratio ).
  • However, the ideal Combat VCE would have the high reheat thrust / good reheat SFC associated with a high specific thrust engine, but would have the low SFC of a low specific thrust engine in dry power and throttled back.
  • However, the ideal Combat VCE would have the high reheat thrust / good reheat SFC associated with a high specific thrust engine, but would have the low SFC of a low specific thrust engine in dry power and throttled back.
  • Curve fitting the data resulted in the specific thrust of 20? �N / W, resulting in the apparent photon momentum multiplication factor of 2, 990?50 and the true OC mirror reflectance used in this demonstration of 0.99967?.00002.
  • A very low specific thrust ( i . e . very high bypass ratio ) turbofan is proposed for the aircraft . Engine handling and low jet noise are facilitated by the use of a variable area final nozzle, to rematch the fan.
  • Improved materials, and the introduction of twin compressors such as in the thermodynamic efficiency of engines, but they also led to a poor propulsive efficiency, as pure turbojets have a high specific thrust / high velocity exhaust better suited to supersonic flight.
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