- #1
sid_galt
- 502
- 1
Applying the momentum equation to the control volume of a convergent nozzle for inviscid, incompressible, low speed flow, the thrust is
[tex]mV_{entry} - mV_{exit} + (P_{exit} - P_{ambient})A_{exit}[/tex]
where
[tex]m=A_{entry}*V_{entry}[/tex]mass flow per unit time
[tex]V_{entry}=[/tex]entry velocity from the front of the nozzle.
[tex]V_{exit}=[/tex]exit velocity of the nozzle air.
[tex]P_{exit}=[/tex]static pressure at exit
[tex]P_{ambient}[/tex]Ambient static pressure
[tex]A_{exit}=[/tex]exit area
For mass flow 4 mg, entry velocity 1 m/s, entry area 4 mm2, exit area 1mm2, exit velocity 4 m/s, the difference between exit and ambient static pressure is -9.225 Pa.
Thrust comes to 2.775E-6. Small but still there is thrust. Is it possible assuming the ideal conditions mentioned above?
[tex]mV_{entry} - mV_{exit} + (P_{exit} - P_{ambient})A_{exit}[/tex]
where
[tex]m=A_{entry}*V_{entry}[/tex]mass flow per unit time
[tex]V_{entry}=[/tex]entry velocity from the front of the nozzle.
[tex]V_{exit}=[/tex]exit velocity of the nozzle air.
[tex]P_{exit}=[/tex]static pressure at exit
[tex]P_{ambient}[/tex]Ambient static pressure
[tex]A_{exit}=[/tex]exit area
For mass flow 4 mg, entry velocity 1 m/s, entry area 4 mm2, exit area 1mm2, exit velocity 4 m/s, the difference between exit and ambient static pressure is -9.225 Pa.
Thrust comes to 2.775E-6. Small but still there is thrust. Is it possible assuming the ideal conditions mentioned above?