Project: Analyzing Flow in Micro Air Vehicle with Winglet Design

This project report details an analysis of flow in Micro Air Vehicles (MAVs) with winglets. The primary objective was to study the effect of winglets on MAV performance, specifically focusing on winglet configuration at a velocity of 15 m/s and angles of attack of 15 and 20 degrees. The project involved numerical analysis to study the impact of feather-like winglets on fixed-wing MAVs, with variations in winglet size and distance. The analysis focused on chord-wise pressure distribution and alterations near the wingtips. Key responsibilities included numerically analyzing flow, checking vehicle dimensions, and documenting features. Challenges encountered included design limitations related to gliding ratio and onboard equipment capacity, which were addressed by suggesting design improvements and lighter equipment. The project aimed to produce innovative work through collaborative task execution and regular follow-ups.

CE 3.1 Project Information
Name of the project: Analysis of Flow in Micro Air Vehicle in Winglets
Location of the project: Please fill
Project Duration: Please fill
Organization: Please fill
Role and Designation during the time: Team Member of the project
CE 3.2 Project Background
CE 3.2.1 Characteristics of the project
The project of Analysis of Flow in Micro Air Vehicle in Winglets was my third major
project in aeronautical engineering career. A proper numerical analysis was undertaken for
studying the significant effect of feathers such as the winglet configuration about the
performance of the fixed wings Micro air vehicle or MAV at the specific velocity of 15 m/s
and the angle of attacks of 150and 200. There was a baseline configuration with the four
different configurations of feathers where size and distance of feathers are varied. This
project focused on the chord wise pressure distribution for changing the span wise locations
and altering the pressure distributions near the wingtips.
CE 3.2.2 Objectives developed for the project
This particular project of Analysis of Flow in Micro Air Vehicle in Winglets
consisted of two important objectives. They are as follows:
 To study the effect of feathers on micro air vehicle.
 To check the winglet configuration for a specific velocity in MAV.

CE 3.2.3 My area of work
The project of Analysis of Flow in Micro Air Vehicle in Winglets was executed by
utmost sincerity and dedication. My major area of work was to numerically analyse the flow
over the fixed wings micro air vehicles with the biologically inspired winglets. I mainly
studied the effectiveness of these specific types of winglets for the overall performance of
any micro air vehicle or MAV. The complete features of the micro air vehicle were
documented by me. I even made the project report properly. The numerical analysis of the
project effectively and efficiently helped me in completing the project perfectly.
CE 3.2.4 Project Group
Figure 1: People involved in the project
CE 3.2.5 My responsibilities throughout the project
I had some of the major responsibilities in this particular project of Analysis of Flow
in Micro Air Vehicle in Winglets. My first important responsibility in this particular project
was to analyse the flow on the fixed wing micro air vehicle with the bio inspired winglets
numerically. My next responsibility was to check the dimension, endurance, airspeed and

payload for this micro air vehicle. Proper measurements were undertaken by me. The
readings were 150 mm, 15 to 20 meters per second and 20 to 60 minutes respectively. I even
noted the dimensional constraint forces, any micro air vehicle or MAV usually utilizes for the
low aspect ratio. The range identified by me was within 1. My next responsibility was to
design the wing profile by taking proper readings.
CE 3.3 Distinctive Activity
CE 3.3.1 Engineering knowledge and skills applied in the project
I had applied some of the major skills in this particular project. My aeronautical
engineering skills and knowledge were extremely important for the successful execution of
this project. The first and the foremost skill that I had utilized here was critical thinking. I
have applied logical as well as reasoning here for identifying the alternate options and
approaches to various issues. Moreover, the performance assessment and designing skills
were also applied in the project. The evaluation of systems was also done properly by me.
Furthermore, I even applied numerical analysis and system analysis for noting the changes
and alterations were checked by me. The aeronautical engineering and physics knowledge
were properly applied here.
CE 3.3.3 Comprehending the Theory of Project
The micro air vehicle or MAV is the smaller portable flying vehicle that is solely
designed for the performance of aircrafts. The type of micro air vehicle used in this specific
project was fixed wing. The urban traffic management is extremely easier with this type of
micro air vehicle. The power required for the flights of fixed wing micro air vehicle or MAV
was calculated in this project.

Figure 2: Power required for fixed wing MAV
The effectiveness and efficiency of the winglet over the MAV performance was
checked. The size of our project was restricted to 150 mm and this was considered as the
chord of the aerofoil section in MAV centre plane. The micro air vehicle comprises of the
wing profile, which is tapered as well as swept with the airfoil section in span. This micro air
vehicle comprises of the aspect ratio of 1 that lies in the range and the maximum chord or
span of 150 mm was checked. The isometric, side and top views of the 3D CAD model in this
project of micro air vehicles with the winglets were taken properly.
The feather configuration was done effectively in this project of Analysis of Flow in
Micro Air Vehicle in Winglets and the details are given below:
Configuration
Number
Feather size, mm Distance, mm Alpha
0 NA NA 15
1 16 4 15
2 16 8 15
3 8 4 15
4 8 8 15
5 NA NA 20
6 16 4 20

7 16 8 20
8 8 4 20
9 8 8 20
Table 1: Feature Configuration Used in the project
The size of domain was solely maintained similar to every tested configuration. The
specific mesh generated for 3D or three dimensional domain within the wing surface.
Moreover, a coarse mesh was also utilized in this particular project. The surface of the wing
of micro air vehicle with feather configuration was similar to the other configurations of 1
and 2.
Figure 2: 3D Domain considered for simulation
For the analysis part, we subdivided into few segments. The first segment was
boundary conditions. A specific symmetric boundary condition was applied to every face and
thus the computational requirements were reduced. The inlet velocity was 15 m/s and the
inlet pressure was 101325 Pa. Vertical plane was selected here. The second segment was
pressure distribution and here the pressure was decreased rapidly in the leading edge and thus
gaining or obtaining the values in the downstream direction was required. The third segment

was streamlines and there is a difference between the stream lines by introducing a gap
between them. For the fourth segment, the effects on the lift were checked and thus the effect
of wing tip configuration was noted, which was 150. The next segment was L/D or lift to drag
ratio. This parameter helped me in discussing the efficiency of the lift generation part. At
around 200, this configuration was 8, the maximum was CL= CD.
CE 3.3.4 Identified issues and their solutions
3.3.4.1 Issues
Some of the most significant issues or problems were identified in this project and
these technical issues were making our project suffer majorly. The first important issue that I
had faced in this project was while making the design of the MAV or micro air vehicle. Our
project was for fixed wings. The main problem was during the gliding ratio of this vehicle. A
maximum speed was not taken in our design and thus our project was suffering major
difficulties. Moreover, our design could not take up the onboard television equipments. This
mainly occurred for the reason of necessity for flying within the earth’s boundary layer. Since
the boundary layer is extremely turbulent, there occurred major problems. Our micro air
vehicle or MAV was extremely smaller and thus was not able to be solved by the application
of all advanced control systems that are combined with the higher manoeuvrable
aerodynamic configuration. These issues or problems were significantly important to be
resolved as soon as possible for the perfect execution of this particular project of Analysis of
Flow in Micro Air Vehicle in Winglets.
3.3.4.2 Solutions
To solve these above mentioned issues, I suggested some of the most important
solutions. For solving the first issue, identified in this project, I suggested to exhibit perfect
forward flight capabilities like the respective gliding ratio within the order of 8 and the

maximum speed within the order of 20 meters per second. I even suggested that the flight
duration should be in the order of less than one hour and the power loading within the order
of 13 kilograms per kilowatt. This would be helpful in keeping the flight at a steady level. For
the second important issue, I suggested to utilize lighter television equipments and thus our
design would be able to carry these equipments easily. Since, our project was for fixed wings
micro air vehicles, I gave the suggestion to use such a configuration that is of lower
manoeuvrable aerodynamic in nature. These solutions were extremely effective for this
project and thus all of the technical issues were solved with my intellect and knowledge.
CE 3.3.5 Plan to produce creative and innovative work
My plan was to produce innovative and creative work by working collaboratively. I
segregated my entire work properly and each task was executed properly and with utmost
sincerity. Moreover, regular follow-ups were taken, so that the project does not face any type
of problem.