RAVI L.
Name:
Designation: Project Engineer
Aircraft
Division,
Hindustan Aeronautics Ltd.,
Qualification: M.E. (Thermal Science &
Engg.)
ME
Dissertation work (2006):
“Flow Field around Aircraft Wing -- A Parametric CFD Analysis”
Synopsis:
The wings are the most
important lift-producing part of the aircraft. Wings vary in design depending upon
the aircraft type and its purpose. Most airplanes are designed so that the
outer tips of the wings are higher than where the wings are attached to the
fuselage. This upward angle is called the dihedral and helps keep the airplane
from rolling unexpectedly during flight. Wings also carry the fuel for the
airplane.
The wing, which is the
primary airfoil of an aircraft has a leading edge, a
trailing edge, a chord, and camber. The leading edge is the "front"
of the airfoil — the portion that meets the air first. The trailing edge is the
“back” of the airfoil — the place at which the airflow over the
upper surface of the airfoil joins the airflow over the lower surface of the
airfoil. The chord of an airfoil is the imaginary straight line drawn through
the airfoil from its leading edge to its trailing edge. The lift produced by
the wings is obtained from the dynamic action of the wing with respect to the
air.
The lift produced by the
wings can be increased by increasing the forward speed of the aircraft or by
increasing the angle of attack. The lift also depends on the angle of
incidence. The aim of any aircraft wing design is to maximize the lift force
and minimize the drag force under all operating/flight conditions. This
necessitates a study of flow field around aerofoil sections of the wing under
different angles of attack and flight velocities. The present project work was
taken up to address these issues. The study of flow field was carried out using
CFD approach. The wing geometry of the passenger aircraft “Boeing 737” was
considered in the present study.
The FLOTRAN module of the
front-end commercial software ANSYS was adopted in these investigations. The
flow field was modeled using FLUID141 element. A parametric study was carried
out by varying the angle of attack. Flow fields around three aerofoil sections
of the wing, one adjacent to the fuselage, the second one at the middle of the
wing and third one close to the free end of the wing were studied. The
following sections present the major conclusions drawn based on the results
obtained.
Conclusions:
1. The “Lift Force” and the “Lift Coefficient” gradually increase with increase in the angle of attack (a) and attain peak values at a = 12.6 and then onwards they decrease.
2. The “Drag Force” and the “Drag Coefficient” gradually increase with increase in the angle of
attack.
3. The circulation increases with increase in angle of attack.
Technical skills:
Programming
Languages: C
Software
Skills: AUTOCAD, GAMBIT, FLUENT
6.3, ANSYS 10.
Education:
1.
M.E. (Thermal Science)
from
2.
B.E. (Mechanical) from
Regional Engineering Collage,
3.
Diploma. (Mechanical)
from Nadgir Polytechnic,
Personal Details:
Father’s Name: Lakkanna
M; Date of Birth: 14th November, 1982; Sex: Male
Nationality: Indian; Languages known: English,
Hindi, Kannada
Contact Details:
Address: Ravi. L, S/O Lakkanna M,
C.P.D.O. Quarters, Hesserghatta, Bangalore
560088, India
Email: ravi_cpd@yahoo.co.in;
ravi_viki@rediffmail.com
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