Name: Ravi L

                                                           Designation: Project Engineer

                                Aircraft Division,

                                Hindustan Aeronautics Ltd.,

                                  Bangalore, India

      Qualification: M.E. (Thermal Science & Engg.)


ME Dissertation work (2006):


                    Flow Field around Aircraft Wing -- A Parametric CFD Analysis



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.





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.




1.       M.E. (Thermal Science) from Bangalore University, India, 2007

2.       B.E. (Mechanical) from Regional Engineering Collage, Bhalki, India, 2004

3.       Diploma. (Mechanical) from Nadgir Polytechnic, Bangalore India, 2004


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

Mobile: 0-9900210787                                                            

Email: ravi_cpd@yahoo.co.in; ravi_viki@rediffmail.com




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