Minnesota State University Algebra Questionnaire

Dr. Nihad Daidzic, ATP, CFII, ProfessorAVIA201, Project 2
Minnesota State University, Mankato
Department of Aviation
AVIA 201, Theory of Flight
Individual Project 2
Airplane Performance Calculations
Open book individual project. Be clear, readable, and neat in your writing. Copying verbatim from
Internet or books is not allowed. This must be individual work. Use clean paper write your name and
page number on each page and STAPLE IT TOGETHER WITH THIS COVER PAGE. Do not forget to put
your name on each page and to be organized. Make illustrations if applicable/required.
Name: _______________________________________________ Grade/Score: ____________
Section: AVIA 201-______ Semester: _______________________ Date: ________________
TECH ID: ________________________ Signature: ____________________________________
1. (10 points) 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/ft3. Use the lift equation:
L W 
1
  SL  CAS 2  S  c L ,max
2
2. (10 points) An Airbus A380 weighs W=1,200,000 lbf in flight and has wing surface
area S=8,000 ft2. 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. (5 points) 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 m/s2.
4. (10 points) 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
© (2019), Dr. Nihad E. Daidzic, All rights reserved
1
Dr. Nihad Daidzic, ATP, CFII, Professor
AVIA201, Project 2
(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. (10 points) 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. (20 points) 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 acceleration of 32.2 ft/s2 or 9.81 m/s2.
TR 
v2
g  tan
ROT 
g  tan
v
7. (5 points) 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. (10 points) 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   p  BHP  v  T  v  D
9. (20 points) 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?
© (2019), Dr. Nihad E. Daidzic, All rights reserved
2