A 10,000-pound airplane stalls when its 300-ft2 wing reaches a maximum lift coefficient (CLmax) of 2.5. Calculate the airplane's stall airspeed (Vs) in knots during a standard day at sea level. To convert speed to knots, divide ft/sec by 1.69.
a- 22.7 kts
b- 42.7 kts
c- 62.7 kts
d- 82.7 kts
2. An airplane is flying at an altitude where the static pressure is 1760.0 lbs/ft2 and the ambient temperature is 44o. Its wing has a surface area of 100 ft2 and a lift coefficient (CL) of 0.8. How much lift (L) would the wing produce flying at 200 knots? Note: to convert speed to ft/sec, multiply knots by 1.69.
a- 7,299.16 lbs
b- 9,299.16 lbs
c- 12,299.16 lbs
d- 14,299.16 lbs
3. A 5,000-lb airplane is flying straight and level at 100 knots at an altitude where the air density is 0.002277 slugs/ft3. The wing's surface area is 120 ft2. Calculate the lift coefficient (CL). Note: to convert speed to ft/sec, multiply knots by 1.69.
a- 0.08
b- 1.28
c- 2.08
d- 3.28