net thrust

net thrust

[′net ′thrəst]
(aerospace engineering)
The gross thrust of a jet engine minus the drag due to the momentum of the incoming air.

net thrust

net thrustclick for a larger image
Two situations when there is neutral stability in atmosphere: (a) when environmental lapse rate (ERL) = dry adiabatic lapse rate (DALR) and air is dry and (b) when ELR = saturated adiabatic lapse rate (SALR) and air is saturated.
The gross thrust of a jet engine minus the drag as a result of the momentum of the incoming air.
References in periodicals archive ?
In this scenario, it is defined as the net thrust as a result of engine number 1 and engine number 4 dynamics, while the amounts of thrust generated by remaining engines are kept equal and fixed as shown in (12) to balance the associated torque/moment values.
According to the authors, for a specific thrust rating, the corrected thrust (defined as the ratio between the net thrust and the pressure ratio) was a function of Mach number.
Net thrust measurement of propellantless microwave thrusters.
According to Bill Webb, an FRDC retired vice president, the resulting installation of six large bleed ducts running from just aft of the fourth stage of the nine-stage compressor to the afterburner resulted in a 22 percent increase in airflow, a 19 percent increase in net thrust, and a 20 percent advantage in fuel consumption at cruise supersonic flight conditions.
An important technical point (which was missed in the first Hawker stol performance predictions) is that the thrust vectored is gross thrust, equal to net thrust (direct from the manufacturer's brochure) plus intake momentum drag, the product of engine mass flow and aircraft velocity.
However, the resulting net thrust will be the same as before.
Since the +y and -y pintles are moved equally, the thrust in the y-axis is eliminated and no net thrust will be generated.
Thus, the net thrust is produced from the expansion of the combined plasma of the nuclear fusion and nuclear fission reactions through the nozzle.
Initial conditions on the object, such as velocity, height, range, and simulation start time, can also be set, as can net thrust and normal force.
The bleed and leakage, while still the same percentage of ram drag as at Mach 2.4, have less impact at Mach 2.0, because at that speed, ram drag is roughly equal to net thrust.
ring, the nozzle exit area can be independently controlled to achieve optimum expansion-area ratios and increased net thrust.