AEE 341 – Aerodynamics
Project #2
“Calculation of Pressure Distribution on NACA 0012
using Source Panel Method”
Faculty of Aeronautics and Astronautics
The University of Turkish Aeronautical Association
Dr. Kürşad Melih Güleren
Instructions:
1. Pressure distribution on NACA 0012 airfoil needs to be calculated using a code
2.
3.
4.
5.
6.
7.
8.
written based on Source Panel Method.
Required files can be downloaded from
http://www.thk.edu.tr/~kmguleren/courses.html.
Please see the list of the angle of attack for student names. Each student is also
responsible of calculation the pressure distribution at zero angle of attack.
A matlab of fortran code should be written to calculate and plot the pressure
distribution along with the pressure data given on the web site.
Differences between the pressure distributions of source panel method and those of
data given on the web site have to be discussed.
Project reports and the code should be submitted via e-mail to Dr.Guleren no later
than 9th of December 2014 11.59 pm. Late submissions will not be accepted.
The project is not a bonus. It will affect 5 % of the overall grade.
Similar codes and reports as well as late submissions will be marked as ZERO.
Student ID
120121058
120121025
120121024
120121007
120121048
120121602
120121604
120121617
120121618
120121619
120121620
120121622
120121626
130121401
120121050
120121614
Name
Remzi Can
Oðuzhan
Kutay
Ahmet Serkan
Ali Volkan
Naveed
Habibul
Bereket Sitotaw
Mohamad Usama
Mohamed Addow
Rico
Ahmed
Idris
Osman Mirza
Meltem
Andi
Surname
YILMAZ
DEMİR
ÇETİN
ALTINOK
ŞAHİN
SULTAN
ABRAR
KIDANE
KUNNATHUR
MOHAMED
MORASATA
PRUŞEVİÇ
SAMAILA YAHAYA
DEMİRCAN
ŞAHİN
HOXHA

-8
-7
-6
-5
-4
-3
-2
-1
1
2
3
4
5
6
7
8
Download

AEE 341 – Aerodynamics Project #2