Discharge of water from a tank occurs through orifices, weirs, or pipes, influenced by gravity and pressure. Torricelli’s theorem states that the velocity of outflow is v = sqrt{2gh} discharge rate is given by Q=Av, considering flow area and velocity. Practical applications include reservoirs, irrigation, and drainage systems. formulae:
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If you know the density and the volume of the liquid, you can calculate its mass using this formula. For further queries:
Problem Statement: A perfect gas flows isentropically through a nozzle. If the ratio of the nozzle exit to the throat is 3.0, and the exit Mach number is also 3.0, find the specific heats ratio of the gas. Equation:01 Isentropic Relations: Equation 2:Mach Number Calculator Developed By: Pawan Indalkar.
isentropic area mach number relation Read More »
Probelm Statement: Compressed air at 40 ∘C and 145 kPa from a large tank is discharged to ambient atmosphere at 101 kPa, through a convergent nozzle of 10 cm2 exit area,Calculate the mass flow rate through the nozzle when the ambient atmosphere is at (a) 101 kPa, (b) 50 kPa, and (c) 30 kPa. Equations
pressure ratio, mach number, velocity,density,speed of sound,mach number Read More »
The thrust developed by a propeller is the force it generates to propel the aircraft forward. It depends on the mass of air being accelerated by the propeller and the difference in velocity of the air before and after it passes through the propeller. The formula for thrust is: T=m˙(V∞−V)T = \dot{m} (V_\infty –
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Propulsive efficiency (ηp\eta_pηp) is a measure of how effectively a propulsion system (like a propeller, jet engine, or rocket) converts the energy in the fuel or input energy into useful forward motion of the vehicle. It compares the useful power used to move the vehicle to the total power available from the propulsion system.
Finding the Propulsive Efficiency Read More »
The induced drag coefficient (CD,i)(C_{D,i})(CD,i) is a dimensionless number that represents the drag due to the generation of lift by a wing or other lifting surface. It is caused by the creation of wingtip vortices and the associated downwash, which increases the effective angle of attack of the wing, reducing its ability to produce lift
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