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 ?
Tenders are invited for Electro Hydraulic Thrustor For Conveyer At Heat Treatment Area: Electro Hydraulic Thrustor, 415V, 3 Phase, 50Hz, Net Thrust 34Kg, Stroke 50Mm, Type-Th3275, S.
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.
Thus, the net thrust is produced from the expansion of the combined plasma of the nuclear fusion and nuclear fission reactions through the nozzle.
Hence the net thrust from the net calculated energy through the main nozzle is estimated to be approximately [2.
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.
In addition to inlet recovery, minimizing inlet leakage and inlet bleed are key design issues because bleed and leakage losses are equal to 1 percent of ram drag, and the ram drag is about twice net thrust.
ring, the nozzle exit area can be independently controlled to achieve optimum expansion-area ratios and increased net thrust.