Find pressure coefficient at a point on an airfoil where velocity is 220 ft/s, which is in a free stream flow of 100 ft/s.
pressure coefficient is given as \[ {C_p} = 1 – {\left( {\frac{v}{{{v_\infty }}}} \right)^2}\]\[ = 1 – {\left( {\frac{{220}}{{100}}} \right)^2}\]\[ = 1 – 4.84\]\[ = – 3.84\]
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
In a new temperature scale, the boiling and freezing points of water at one atm are 100 degree and 300 degree respectively. Correlate this scale with Centigrade scale. The reading of 0 degree in the centigrade will be ?
A gas mixture consists of 3 kg of oxygen, 5 kg of nitrogen and 12 kg of methane. What is the mass fraction and mole fraction of oxygen ?
A compressor delivers 4 m^3 of air having a mass of 5 kg. What is the specific weight and specific volume of air being delivered.
3 moles of an ideal gas is compressed to half the initial volume at a constant temperature of 300 K. What is the work done in the process?
