This preview shows pages 1–2. Sign up to view the full content.
AAE333 Fall 2010
Homework 10
Due: Mon Nov 15
10% bonus if turned in on Friday Nov 12
1)
Consider the potential
flow over a circular cylinder with circulation. The free
stream is along the positive x axis.
What circulation would be needed to put the
rear stagnation point 20deg below the positive x axis? What would the
corresponding values of Cl and Cd be?
2)
You are going to find the incompressible potential flow over an NACA 2418
airfoil at angle of attack using the source/vortex panel method described in class.
There are two matlab files you will need.
function
[U,V]=velfrompanel(x1,y1,x2,y2,xc,yc)
calculates the x & y velocity components (U,V) at a specified
point (xc,yc) induced by a unit strength source sheet connecting
specified points (x1,y1) and (x2,y2). (or, equivalently, the velocities
induced by a uniform strength vortex sheet)
The second is an example for a different airfoil:
airfoil_examp.m
Before doing anything for the NACA2418 airfoil, make sure you can
run the example, varying the angle of attack and the thickness/chord
This preview has intentionally blurred sections. Sign up to view the full version.
View Full Document
This is the end of the preview. Sign up
to
access the rest of the document.
This document was uploaded on 01/22/2012.
 Fall '09

Click to edit the document details