HW3solution

HW3solution - AAE 334 Fall 2011 Homework 3 SOLUTION Due...

This preview shows pages 1–2. Sign up to view the full content.

AAE 334, Fall 2011, Homework 3 SOLUTION Due Monday, August 29 at the beginning of class. Consider a pressure distribution near a leading edge of a symmetric airfoil. We will do this with the flow shown in Figure 3.22 of the text and solved on page 248. We will use and . 1 = V 1 . 0 = Λ 1. Plot the airfoil shape near the leading edge. Hints: a. define an angular position vector for points on the body: thbody = (0.2:0.01:1.8)*pi; % Theta coordinate (remember that thbody=0 is the x-axis, not the leading edge.) b. compute for radial coordinate of points on the body c. compute (x,y) from (r, θ ), and plot with plot( ) d. to set the correct aspect ratio in your plot, use: set(gca, 'DataAspectRatio' ,[1 1 1]) after the plot command. 2. Compute and plot separately a non-dimensional quantity 2 2 1 V V versus angle from the leading edge. Top and bottom surfaces in this symmetric flow will have the same result so expect to see only one curve in this plot. This 2 2 1 V V quantity is another mathematically correct formula for pressure coefficient () 2 2 1 = V p p c p ρ in an incompressible flow. 3. Where is there a favorable pressure gradient for the flow on the surface? That is, flow from higher pressure into lower pressure? 4.

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.

{[ snackBarMessage ]}

Page1 / 5

HW3solution - AAE 334 Fall 2011 Homework 3 SOLUTION Due...

This preview shows document pages 1 - 2. Sign up to view the full document.

View Full Document
Ask a homework question - tutors are online