What is the ratio of flight speed to the exhaust velocity for maximum propulsion efficiency ?
Propulsive efficiency for a jet engine is given as
\[\eta _{p}=\frac{2}{1+\frac{v_{e}}{U}}\]
Therefore from above we can see that maximum propulsive efficiency is obtained when flight speed should be equal to the exhaust velocity,the ratio should be equal to 1.
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
An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively ( specific gas constant is 287 J/kg-K), find the circulation on the airfoil.
A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and ratio of specific heats 1.2.The universal gas constant is 8314 J/kg-mol-K. What is the value of theoretical \(c^{*}\) in (m/s)?
Find the radial component and tangential component of the fluid's velocity.
The logarithmic decrement measured for a viscously damped single degree of freedom system is 0.125. What is the value of the damping factor in percent?
