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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....
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This document was uploaded on 01/22/2012.
- Fall '09