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.
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=m˙(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 »
Problem Statement: A rocket nozzle has an exit/throat area ratio of 3. The combustion gas mixture at 20 bar and 2500 K is expanded through the nozzle to an atmosphere at 1 bar.The molar mass of the gas mixture is 33.5 kg kmol−1 and 𝛾 =1.2. Assuming the flow process to be isentropic, estimate the
pressure ration, mass flow rate per unit area 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
To find the induced drag coefficient Read More »
