hw10 - of the length, the fields are quite different. Try...

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
AAE333 Fall 2011 Homework 10 Due: Mon Nov 7 1) Consider a single line segment extending from (x,y)=(.3,0) to (.4,0). a. Find the velocity field (u,v) induced by a constant unit strength source density along the line segment. Plot the velocity field (don’t get too close to the ends of the segment- the velocities get very big there. b. Find the velocity field (u,v) induced by a constant unit strength vortex density along the line segment. Plot the velocity field (don’t get too close to the ends of the segment- the velocities get very big there. These fields are one example of the fields used to do a source/vortex panel method for an airfoil. c. Note that if you look pretty far from the line segment (ie at distances big compared to the length of the segment) the velocity fields look like that of a point source and point vortex respectively. If you look at it on the scale
Background image of page 1
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: of the length, the fields are quite different. Try to sketch the streamline patterns for each case 2) QFLR5 is a reasonable user friendly airfoil analysis code that employs a panel method to find the pressure distribution. It has the ability (albeit limited) to model the boundary layers as well, if you choose to include them. In this first exposure to it, I am asking that you exercise it for a simple NACA 2410 airfoil for inviscid flow over a range of angles of attack from -5 to 10deg. Find the pressure distributions (cp vs x/c) and plot the lift coefficient vs aoa. Resources for QFLR5 are included in this folder We will revisit this code later on and see how it relates to the analysis methods discussed in class....
View Full Document

This document was uploaded on 01/22/2012.

Ask a homework question - tutors are online