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 \[ {C_p} = 1 – {\left( {\frac{v}{{{v_\infty }}}} \right)^2}\]\[ = 1 – {\left( {\frac{{220}}{{100}}} \right)^2}\]\[ = 1 – 4.84\]\[ = – 3.84\]
The Cessna Cardinal, a single-engine light airplane, has a wing with an area of 16.2 m2 and an aspect ratio of 7.31. Assume that the span efficiency factor is 0.62.
Investigate the principles of aerodynamics in mechanical engineering, covering topics such as fluid flow around objects, lift and drag forces, and boundary layer phenomena.
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.
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?
