In an unpowered glide of an aircraft having weight w, lift L and drag D, how will the equilibrium glide angle will be defined ?
For the un powered glide flight
\(L=Wcos\theta
\\D=Wsin\theta
\\\Rightarrow \frac{D}{L} =\frac{Wsin\theta}{Wcos\theta}
\\\Rightarrow tan\theta =\frac{D}{L}
\\\Rightarrow \theta =tan^{-1}\left ( \frac{D}{L} \right )\)
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?
