The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K ,respectively.If the heating value of the fuel is 44 MJ/kg and specific heat at constant pressure for air and hot gases are 1.005 kJ/kg-K and 1.147 kJ/kg-K respectively,find the fuel to air ratio.
Consider an airplane in an accelerated climb. At a given instant in this climb, the specific excess power is 120 ft/s
Consider an airplane flying at 620 mi/h at 35,000 ft. Calculate its energy height.
For a turbojet-powered airplane with the altitude variation of thrust given by Eq. (3.19), show that as the altitude increases, the maximum velocity decreases.
The BD-5J is equipped with plain flaps. The airfoil section at the wing root is an NACA 64-212, and interestingly enough, it has a thicker section at the tip, an NACA 64-218.
For the BD-5J, calculate (a) The maximum value of CL/CD (b) The maximum value of CL^(1/ 2) /CD
Consider an incompressible two-dimensional viscous flow over a curved surface. Let the pressure distribution on the surface be \(p(s)=2+sin\left ( \frac{\pi}{2}+s \right )\;N/m^2\),where \(s\) is the distance along the curved surface from the leading edge. Find the distance from where the flow separates.
All the factors remaining constant, if the weight of an aircraft increases by \(30 \%\) then the take off distance will increase by approximately.
Consider a steady two-dimensional zero pressure gradient laminar flow of air over a flat plate as shown below. Find the ratio of displacement thickness to momentum thickness of the boundary layer at a distance of 2m from the leading edge.
Find the shock angle and the total temperature at point P.