Your statement implies that there's a net pressure differential between the contaniner and the outside air that results in 8 lbs of force at the fan. Also, there's no blowing, the ducted fan is acting as a compressor if it's output is going into a closed container. The pressure would be 8 lbs divided by the cross sectional area of the duct containing the fan. If the duct has a diameter of 4 inches, then the area of the duct is pi x r^2 = pi x (2)^2 = 12.566 in^2. Pressure would be 8 lbs / 12.566 in^2 ~= .636 psi.Subaru_STI said:If I have a RC electric ducted fan engine blowing at 8 lb of thrust into a closed container, what PSI would it be inside of the container, (when the engine is runny continuously)?
Thrust producing pressure is the force that is exerted by a propulsion system, such as a rocket or jet engine, to propel an object forward. This pressure is created by the expulsion of high-velocity gases from the back of the system, which creates a reactive force in the opposite direction.
Thrust producing pressure is calculated by multiplying the mass flow rate of the exhaust gases by their velocity. This is known as the thrust equation: F = ṁv, where F is the thrust force, ṁ is the mass flow rate, and v is the velocity of the exhaust gases.
Thrust producing pressure is affected by several factors, including the size and design of the propulsion system, the type and amount of propellant used, and the ambient conditions such as air density and temperature. The efficiency of the system also plays a role in determining the amount of thrust produced.
Yes, thrust producing pressure can be increased by increasing the mass flow rate of the exhaust gases or by increasing their velocity. This can be achieved by using a more powerful propulsion system, optimizing the design of the system, or using more efficient propellants.
In space travel, thrust producing pressure is used to overcome the gravitational pull of a planet or other celestial body and to propel spacecraft into orbit or to other destinations. It is also used for course corrections and to control the movement and orientation of the spacecraft during its journey.