computer drawing of a rocket nozzle with the equations for thrust thrust equals the exit computer drawing of gas turbine schematic showing the equations for pressure ratio temperature ratio most of us can relate to the geometry of a nozzle based on our experience with the common garden hose attachment used to increase the exit velocity of the computer drawing of a convergent divergent nozzle with equations that describe the operation computer drawing of a solid rocket engine with the equation for thrust thrust equals the computer drawing of a rocket nozzle with the equation for thrust thrust equals the exit a graphic showing the equations which describe the mass flow through a nozzle including compressibility effects a graphic showing the equations which describe the area ratio through a nozzle including compressibility effects nozzle exit the computed exit pressure must be compared to the given pressure to determine if the guess for p2 was correct these equations can be a graphic showing the equations which describe isentropic flow learning objectives this equation governs the shape of a nozzle or a diffuser in subsonic or supersonic isentropic a graphic showing the equations which describe the area ratio through a nozzle including compressibility effects computer drawing of a liquid rocket engine with the equation for thrust thrust equals the one dimensional steady flow in nozzles and diffusers computer drawing of a propulsion system with the math equations for thrust thrust equals the derivation of the ideal rocket equation which describes the change in velocity as a function of derivation of the ideal rocket equation which describes the change in velocity as a function of figure 20 main screen for the design conditions routine showing page one of three pages of nozzle equations computer drawing of a jet engine with the equation for thrust thrust equals the exit computer drawing of a ramjet engine with the equation for thrust thrust equals the exit learning objectives computer drawing of an afterburning turbojet engine with the equation for thrust thrust equals the for this design the area ratio ae a is known as the all important optimum expansion ratio the continuity equation computer drawing of a turbofan engine with the equation for thrust thrust equals the sum basic equations of fluid in motion bernoulli equation uses of bernoulli equation free jets convergent divergent nozzle schematic and variations of pressure along the length of the nozzle 15 de 7 thrust equation c effective exit velocity c f thrust coefficient c characteristic velocity ε nozzle area expansion ratio i sp 0 specific a high velocity nozzle is designed to operate with steam at 700 kpa and 300 the continuity equation this is only a preview pressure point 11 calculating flow rate from pressure measurements these fundamental equations can be used to derive diffeial equations that show how pressure density and velocity vary in relation to area 51 example 30 to first page preview article preview variation of fluid velocity with flow area de laval nozzle characteristics at several back pressures 36 equation for velocity figure imgf000016 0001 subsonic and supersonic flow in nozzles equation 2 16 1 2 16 2 2 16 3 jpg one dimensional steady flow in nozzles and diffusers image thumbnail