ToDo Calculator’s aerospace calculator is an essential tool for aerospace enthusiasts, engineers, and professionals. Tailored for aerodynamics, flight dynamics, propulsion systems, and orbital mechanics, it offers advanced features and accurate calculations. With a user-friendly interface, it’s accessible to all levels of expertise, making it indispensable for designing aircraft, planning mission trajectories, and studying aerospace concepts.
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.
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Problem 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.
pressure ratio, mach number, velocity,density,speed of sound,mach number 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 »
Problem Statement:Helium gas at 250 kPa and 100 ∘C flows through a rectangular duct of cross-section 40 cm × 50 cm, with a velocity of 500 m s−1.Determine the Mach number, stagnation temperature, stagnation pressure, and the mass flow rate. Assume helium to be an ideal gas. Equation 1: Speed Of Sound. Equation 2:Isentropic Relations
speed of sound,isentropic Relation, mach number,mass flow rate Read More »
Problem Statement:An aluminum pitot probe is placed in a supersonic air stream of temperature 30 ∘C. If the melting temperature of aluminum is about 660 ∘C, determine the flow velocity at which the probe will begin to melt. Assume air to be an ideal gas. Equation 1:speed of sound Equation 2:isentropic realtion Equation 3:energy Equation
speed of sound, isentropic realtion, energy Equation, velocity, temperature 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=mË™(V∞−V)T = \dot{m} (V_\infty –
Find the thrust developed by a propeller Read More »
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 »
