12120 UCK111E Introduction to Aeronautics and Ethic
2011-2012 Fall Semester
Midterm Exam
23.12.2011
Problem 1: Which of the following expressions is correct?
(a)
(b)
(c)
(d)
(e)
Problem 2: Which of the following expressions is correct?
(a)
(b)
(c) D
(d)
(e)
Problem 3: Which of the following expressions is correct?
(a)
(b)
(c)
(d)
(e)
Problem 4: A 300 ton aircraft is cruising at a velocity of 850 km/h at a an altitude of 11500m. The lift
coefficient of the wing is 1,5. What is the total lift force acting on the aircraft?
(a) 3x105 N
(b) 4.5x105 N
(c) 2.9x106 N
(d) 4.5x106 N
(e) 4.4x106 N
Problem 5: For the aircraft in problem 4 the total drag force is 100.000 N. If the aircraft has two engines
what should the thrust force produced by each of the engines be?
(a) 2.0x105 N
(b) 1.0x105 N
(c) 1.0x106 N
(d) 1.0x104N
(e) 5.0x104 N
Problem 6: Define the following: airfoil, camber, thickness, mean camber line, chord line, leading edge,
trailing edge, angle of attack. Show it in a figure.
Problem 7: What is a VTOL aircraft?
Problem 8: Very shortly mention on material used in aircraft industries. Also write why it is preferred.
Problem 9: In your first homework assignment you were asked to acquire information about an aircraft of
any type (passenger aircraft, fighter, sailplane, etc.) you would choose from the literature. Which aircraft
did you choose? Give some details (the aircraft was built, country, technical specifications).
12120 UCK111E Introduction to Aeronautics and Ethics
2011-2012 Fall Semester
Final Exam
16.01.2012
Problem 1: Which of the following expressions is a unit of dynamic pressure?
(a) [q∞] = [kg·m·s-1] (b) [q∞] = [kg·m·s-2] (c) [q∞] = [kg·m-1·s-2] (d) [q∞] = [kg·m2·s-2]
(e) [q∞] = [kg·m-1·s-1]
Problem 2: Which of the following expressions is a unit of the lift coefficient of an airfoil?
(a) [cl] = [N·m-2] (b) [cl] = [N·m-1] (c) [cl] = [N·m] (d) [cl] = [N] (e) dimensionless
Problem 3: Which of the following expressions is a unit of the drag coefficient of an airfoil?
(a) [cd] = [N·m-2] (b) [cd] = [N·m-1] (c) [cd] = [N·m] (d) [cd] = [N] (e) dimensionless
Problem 4: Which of the following expressions is a unit of the moment coefficient of an airfoil?
(a) [cm] = [N·m-2] (b) [cm] = [N·m-1] (c) [cm] = [N·m] (d) [cm] = [N] (e) dimensionless
Problem 5: Define the following physical quantities: force, energy, work, power. What are the units of
these quantities?
Problem 6: Do you think there is a difference between the terms flow and flight? For example, can
"supersonic flow" be used instead of "supersonic flight" and vice versa? Explain.
Problem 7: A 300 ton aircraft is cruising at a velocity of 850 km/h at an altitude of 11500m. The air density
and temperature at this altitude are 0.337 kg/m3 and 216.66 K, respectively.
(a)
(b)
(c)
(d)
Calculate the temperature in degrees Celcius (ºC).
What is the cruising velocity in meters per second (m/s)?
The speed of sound at this altitude is 295 m/s, approximately. Is the cruising velocity subsonic?
If the wing area of the aircraft is 525 m2 calculate the lift coefficient (CL).
Problem 8: How does an turbojet engine produce thrust?
Problem 9: Choose two of the researchers mentioned below and briefly describe what their contribution to
aeronautics has been.
George Cayley
Otto Lilienthal
Orville Wright – Wilbur Wright
Leonardo da Vinci
Igor Sikorsky
Juan de la Cierva
Konstantin Eduardovitch Tsiolkovsky
Robert Hutchings Goddard
Frank Whittle
Hans von Ohain