Hall Ticket No Course Code AAE004
INSTITUTE OF AERONAUTICAL ENGINEERING
(Autonomous)
Four Year B.Tech IV Semester CIE II, May 2018
Regulations: IARE-R16
LOW SPEED AERODYNAMICS
Time: 2 Hours Max Marks: 25
Answer all question from Part A
Answer any four questions from Part B
All parts of the question must be answered in one place only
PART A
1. Explain the importance of Kelvin's circulation theorem. Remember CO: 2 Marks:
Explain Biot-Savart Law. Understand CO: 2 Marks:
What is vortex panel method? Remember CO: 7 Marks:
What are the commonly used singularities to model potential flows over airfoils?
Remember CO: 9 Marks:
Write short notes on the general effects of the propeller slipstream on the wing and tail.
Understand CO: 11 Marks:
PART B
2. Describe the stalling of an airfoil and the related aerodynamic phenomena.
Understand CO: 4 Marks:
Consider a thin, symmetric airfoil at 1.5° angle of attack. From the results of thin airfoil theory,
calculate the lift coefficient Cl, and the moment coefficient about the leading edge, Cm,LE.
Understand CO: 4 Marks:
3. Consider a vortex filament of strength in the shape of a closed circular loop of radius R. Obtain
an expression for the velocity induced at the center of the loop in terms of and R.
Understand CO: 1 Marks:
The Piper Cherokee light, single-engine general aviation aircraft) has a wing area of 170 ft2
and a wing span of 32 ft. Its maximum gross weight is 2450 lb. The wing uses an NACA 65-415
airfoil, which has a lift slope of 0.1033 and Assume 0.12. If the
airplane is cruising at 120 mi/h at standard sea level at its maximum gross weight and is in
straight-and-level flight, calculate the geometric angle of attack of the wing.
Remember CO: 1 Marks:
4. Obtain the expression for induced drag and minimum induced drag for elliptic planform.
Understand CO: 8 |Marks:
A constant strength vortex panel of strength 50 units is located on the axis from X1=3.5 to
X2=6.65. Determine the influence of this vortex panel at a point P 4.5) to evaluate V
w). Develop the expressions used for determining velocity potential.
Understand CO: 8 |Marks:
Page 1 of 2
5. Explain the basic methodology to study potential axisymmetric flow past a slender body of
revolution, using the method of singularities. Understand CO: 8 Marks:
An aircraft weighing 40,000 lbs, has a wing area of 350 ft2 and a wing span of 50 ft. At sea-level,
the aircraft flies at 200ft/sec 600ft/sec. For the entire aircraft, determine the estimated
values of the induced drag and the associated drag coefficients for the two cases? Note that lift
weight in level flight. Also, assume Oswald efficiency factor of 0.85.
Understand CO: 8 |Marks:
6. Describe the method of singularities. How is it used to study potential flow over an arbitrary
body? Understand CO: 11 Marks:
Extend the source panel code for NACA0012 airfoil (at zero AOA) to generate the pressure
coefficient distribution. Plot the distribution. Understand CO: 11 Marks:
Page 2 of 2