Module- 1

1. Give examples of two sub-sonic airplanes and two supersonic airplanes. - Rakshith
2. Identify the conditions for minimum thrust required. - Rakshith
3. Describe the relationship between thrust and drag in steady flight. - Rakshith
4. Draw an airplane and show the forces acting on it at steady level flight. - Rakshith
5. Draw the thrust required versus flight velocity for an airplane. - Rakshith
6. Write the equation for thrust available for a propeller driven airplane and explain the
significance of each term in the equation. - Rakshith
7. Differentiate between power required and power available of an airplane. - Rakshith
8. Describe the effect of altitude on power required of an airplane. - Rakshith
9. Describe the impact of drag on power required. - Rakshith
10. Identify the condition for minimum power required for an airplane in terms of
airplane aerodynamic parameters. - Rakshith
11. Illustrate the importance of thrust available for jet propelled aircraft. Derive the
maximum velocity equation for the same airplane and explain the factors affecting the
maximum velocity. - Pooja
12. Consider the gulf stream IV for twin-turbofan executive transport shown in figure .
Calculate and plot the thrust required curve at an altitude of 30000 ft, assuming a
weight of 73,000lb. Airplane data S= 950 ft2 , CD0 = 0.015 and K=0.08. - Bindhu
13. A jet engine propelled airplane is flying at a speed of V∞ at an altitude of h kilometer.
Derive an equation for Thrust Required in terms of V∞ and atmospheric density at that
altitude.- Janavi
14. An aircraft weighing 2,50,000 N has a wing area of 80 m2 and its drag equation is CD
= 0.016 + 0.04 CL2. Calculate minimum thrust required (Tmin) minimum power
required (Pmin) for straight and level flight at sea level. Assume sea level air density to
be 1.226 kg/m3. - Janavi
15. An aircraft with a wing area of 20m2 and drag given by CD0=0.015 and K=0.04 is
flying at an altitude of 6km, at its minimum drag speed. If the engine thrust is 2500N,
what is the speed and weight of the aircraft? - Bindhu
16. Illustrate how to estimate the maximum velocity of a jet airplane by graphical
approach with the help of a neat diagram -Hemalatha
17. An aircraft is powered by two engines, each engine is rated at maximum thrust of 60
kN at sea level. Assume thrust is constant with velocity. Calculate the maximum
velocity of the aircraft (Vmax) at sea level. Given that the weight of the aircraft is
40000 kg, wing area 88.5 m2 with CD0 of 0.015 and K of 0.08. -Hemalatha
18. Calculate and plot the thrust required curve and power required curve at 10 km
altitude (density of air is 0.413 kg/m3) for an executive twin jet aircraft at flight
speeds of 100 m/s, 200 m/s and 300 m/s. Aircraft Weight is 40000 kg, wing area 90
m2 with CD0 of 0.015 and K of 0.08. - Pooja
 Module-2
1. Discuss about Rate of Climb and its importance for an airplane. -Sayanth
2. Describe the factors affecting climb performance. -Sayanth
3. Write the difference between angle of climb and pitch of an airplane? -Sayanth
4. Write a brief note on the airplane velocity corresponding to best Rate of Climb. -
Sayanth
5. State the significance of best Rate of Climb and best Angle of Climb? -Sayanth
6. Differentiate the term absolute ceiling and service ceiling. -Sayanth
7. Why it is necessary to accurately calculate the absolute ceiling for each flight? -
Sayanth
8. Discuss about gliding flight. -Sayanth
9. What is gliding angle and its significance in case of power failure? -Sayanth
10. Describe rate of sink for a glider. -Sayanth
11. Draw the Hodograph diagram for climb performance of an airplane at a given altitude.
Explain how to obtain maximum rate of climb and maximum climbing angle using
this Hodograph.- Arjun
12. Derive the equation for Rate of Climb. Explain how to obtain Rate of Climb from the power
required versus power available curves for propeller-driven and jet-propelled airplanes using
neat diagrams.- Trisha
13. Derive an equation for maximum Rate of Climb for a propeller-driven airplane in
terms of wing loading and airframe aerodynamic characteristics.- Dharsan
14. An aircraft is powered by single engine rated at maximum thrust of 75 kN at sea level.
Assume thrust is constant with velocity. Aircraft Weight is 14000 kg. Airplane wing
area is 38 m2 having CD0 =0.012 and K=0.04. Find the Rate of Climb of this airplane
when it is flying at a speed of 200 m/s at sea level (air density 1.226 kg/m3). .- Arjun
15. An airplane is making an unaccelerated climb at an angle of 60 at a flight speed of 360
km/hr. The maximum weight of the airplane is 250 ton. Find out the thrust required
for this climbing flight. Assume zero thrust angle, a drag coefficient of 0.11, wing
area of 400 m2 and sea level atmospheric conditions.- Trisha
16. The Rate of Climb of an airplane is 40 m/s at sea level. The Rate of Climb for this
airplane is 30 m/s and 20 m/s at altitudes of 4 km and 8 km respectively. What will be
the approximate service ceiling of this airplane. -Sam
17. A jet airplane with a best L/D of 16 at 540 km/hr is initially at 10,000 m altitude
above the ground and suffers a complete power failure after a fuel leak causes it to run
out of fuel. Estimate the approximate gliding distance at the best glide airspeed and
how long will it take to reach the ground. -Sam
18. Write appropriate equations for sink rate and time to descent. .- Dharsan
19. A glider weighing 500 kg has a wing area of 25 m2 ,CDO = 0.012, AR = 16 and e =
0.87. Determine(i) the minimum angle of glide, (ii)minimum rate of sink – Keerthi
Priya.
20. For the Gulfstream Iv discussed in previous examples(Problem no.2.4), plot the
variation of (R/C)max versus altitude, and use this curve to graphically obtain the
absolute ceiling.Also Plot the variation of V(R/C)max versus altitude. - Ishwarya