Aircraft design calculators serve as specialized instruments within aerospace engineering and aircraft design. They enable professionals to conduct diverse calculations and simulations pertinent to aircraft design and performance. These tools are indispensable for aerospace engineers, designers, and researchers seeking to analyze and enhance various facets of aircraft design.
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 »
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 »
Problem Statement: Air from a reservoir at 10 atm and 80 ∘C is discharged through a convergent–divergent nozzle fitted to the reservoir. The thrust exerted by the jet issuing from the nozzle is 11.12 kN. If the backpressure is 1 atm, calculate the nozzle throat and exit areas and Mach number of the jet issuing
pressure ration, area formula, tempertaure, speed of sound, Read More »
Problem statement:A flow at 60 m s−1 enters a nozzle kept horizontal. The specific enthalpy at the nozzle inlet and exit is 3025 and 2790 kJ kg−1, respectively,Neglecting the heat loss from the nozzle, calculate (a) the flow velocity at the nozzle exit, (b) the mass flow rate through the nozzle, if the inlet area
Energy Equation , Mass flow Rate Read More »
problem statement: Helium gas from a storage tank at 1000 kPa and 310 K is flowing out through a convergent nozzle of exit area 3 cm2 to another tank.When the mass flow rate is 0.15 kg s−1, determine the pressure in the second tank. Solution Equations used: 2: Mach Number: 3:Pressure: 4: Isentropic Relations: Isentropic
Mass flow rate, mach number, pressure, Isentropic Relation Read More »
The speed of sound (a) is equal to the square root of the ratio of specific heats (g) times the gas constant (R) times the absolute temperature (T). The derivation of this equation is given on a separate page. Notice that the temperature must be specified on an absolute scale (Kelvin or Rankine). calculator developed by- Pawan Indalkar
speed of sound, mach number, isentropic relations Read More »
– D. Raymer – Aircraft Design. A Conceptual Approach (1992) Wf: Weight of the fuel required for the mission. Wo: Initial takeoff weight of the aircraft. Wx: Weight of the aircraft after completing the mission (excluding fuel weight). The factor 1.06 accounts for a typical 6% reserve and trapped fuel allowance.
Fuel-Fraction Estimation Calculator Read More »
