Valentina Tereshkova

As these gases are pushed out in one direction, there is a reaction force that pushes the rocket in the other direction. This reaction force is called thrust.

The space shuttle launched like a rocket. But it landed like a glider airplane. The solid rocket boosters and the main engines on the orbiter helped the shuttle blast off from Earth like a rocket. The external tank dropped off the orbiter after it had used all the fuel in the tank.

6 Space Shuttles were built (although only 5 of them spaceworthy): Challenger, Enterprise, Columbia, Discovery, Atlantis & Endeavour. 4 of them are still around, in various museums. Disintegrated after launch, killing all seven astronauts on board.

Space shuttle, also called Space Transportation System, partially reusable rocket-launched vehicle designed to go into orbit around Earth, to transport people and cargo to and from orbiting spacecraft, and to glide to a runway landing on its return to Earth’s surface that was developed by the U.S. National Aeronautics …

As the world’s first reusable spacecraft to carry humans into orbit, the shuttle possesses a 60-foot-long payload bay and robotic arm that can carry several satellites into low Earth orbit on one flight, service them and even bring them back for future use.

Space Launch System

The most powerful rocket ever? If we use thrust as a measure, the SLS will be the most powerful rocket ever when it flies to space in 2021. The Block 1 SLS will generate 8.8 million pounds (39.1 Meganewtons) of thrust at launch, 15% more than the Saturn V.

The technology works by using a mechanically driven supercharger to deliver sea-level density air pressure to the engine as aircraft altitude increases. …

The idea behind the aerospike design is that at low altitude the ambient pressure compresses the exhaust against the spike. As the vehicle climbs to higher altitudes, the air pressure holding the exhaust against the spike decreases, as does the drag in front of the vehicle.

Atmospheric pressure restricts the expansion of the exhaust gas at low altitudes so the efficiency is much higher at low altitudes . It is also able to expand the engine exhaust to a larger effective nozzle area ratio, at high altitudes. The dual bell design is suitable for Single Stage to Orbit (SSTO) flight.

This type of flow is called perfectly-expanded flow or flow at design conditions. Dropping the back pressure ratio further results in a condition known as under-expanded flow. For this condition, the pressure at the exit is larger than the back pressure so the flow must continue to expand upon leaving the device.

For evaluating delivered performance parameter values, static tests or flight test of full-scale models are used. 2. What is another name for the nozzle area ratio? Explanation: Nozzle area ratio is defined as Ae/A*, where Ae denotes exit area and A* denotes throat area.

There are 5 basic spray pattern types: flat fan, solid stream, full cone, hollow cone and mist/fog. Various nozzle designs are deployed to create these patterns and details on each can be found in the sections below.

A rocket engine nozzle is a propelling nozzle (usually of the de Laval type) used in a rocket engine to expand and accelerate the combustion gases produced by burning propellants so that the exhaust gases exit the nozzle at hypersonic velocities.

Short answer: Yes. A convergent nozzle will not allow supersonic exit speeds of the combustion gasses, but due to their high temperature their speed of sound is considerably higher that that of the surrounding air.

The upstream stagnation conditions are assumed constant; the pressure in the exit plane of the nozzle is denoted by PE ; the nozzle discharges to the back pressure, PB . In such cases, the position of the shock moves downstream as PB is decreased, and for curve (iv) the normal shock stands right at the exit plane.

So the divergent section acts as a sub-sonic diffuser in which the pressure increases and velocity decreases. At throat, velocity is equal to sonic velocity. The divergent portion acts as a super-sonic nozzle with a continuous decrease in pressure and continuous increase in velocity.

The flow in the throat is sonic which means the Mach number is equal to one in the throat. Downstream of the throat, the geometry diverges and the flow is isentropically expanded to a supersonic Mach number that depends on the area ratio of the exit to the throat.

Gustaf de Laval

It is used to accelerate a hot, pressurized gas passing through it to a higher supersonic speed in the axial (thrust) direction, by converting the heat energy of the flow into kinetic energy. Because of this, the nozzle is widely used in some types of steam turbines and rocket engine nozzles.