answer that question

1. Calculate the calibrated stalling speed (ft/s, knots, and km/h) of an aircraft (Piper

Archer II, PA-28-181) weighing W=2,550 lbf (mass of 1,159 kg) if the maximum coefficient

of lift with flaps down is 1.65, wing surface area is 170 square feet and the sea-level air density is 0.002377 slug/ft . Use the lift equation:
L=W= ×r ´CAS2´S´c SL L,max

2. An Airbus A380 weighs W=1,200,000 lbf in flight and has wing surface area 2 S=8,000 ft . Calculate the wing loading (W/S), differential pressure acting on the wing (∆p), and how much lift is produced if airplane flies level at 500 KTAS (at 36,000 ft

3- Piper Warrior accelerates at a constant rate of 3 knots/second starting from zero.

How many seconds will pass for an airplane to reach 60 knots and what distance will be

covered in that period? Assume that gravitational acceleration of Earth is 32.2 ft/s2 or 9.81

2 m/s .

4- What will be the true airspeed (TAS) of an airplane flying at 10,000 ft whose airspeed indicator is showing 100 knots (KIAS) and the calibrated airspeed (KCAS) is 2 knots

faster than KIAS. If we assume that TAS increases by 2% of KCAS for every 1,000 ft altitude in lower atmosphere calculate KTAS.

5- If an airplane stalls at 60 KIAS in level flight and clean configuration, what will be the stalling speed in a level 60 degrees bank? What will be the load factor “n”?

6-Calculate the Turn-Radius (TR) in feet and the Rate-of-Turn (ROT) in angular degrees/second and in degrees/minute for an airplane flying at 100 knots indicated Airspeed (KIAS) and bank angle (φ) 45 degrees at 4,000 ft in zero-wind condition? Altimeter setting of 29.72 inch Hg and the outside air temperature is 15 degrees Celsius with the gravitational 22 acceleration of 32.2 ft/s or 9.81 m/s . v2 g´tanf TR = g ´ tanf ROT = v

7-If you are flying at indicated altitude of 5,000 ft with an altimeter setting of 30.22 inch Hg and air temperature of -5 degrees Celsius, what are the corresponding pressure altitude (PA) and density altitude (DA)?

8- How much drag (D) is airplane producing if engine produces 100 HP at a given density altitude and the propeller efficiency (ηp) is 80% for an airplane flying at constant un- accelerated 110 KTAS and level altitude?

THP=hp ´BHP=v´T =v´D

9- How much lift and drag is an airplane, having rectangular wing of wingspan 34 ft and average chord of 5 ft, producing at 100 KTAS if the air density is 0.0020 slug/ft3 and the coefficient of drag is 0.05 while the coefficient of lift is 0.5? Calculate aerodynamic efficiency (E), range efficiency, and the endurance efficiency at these conditions?