This preview has intentionally blurred sections. Sign up to view the full version.
View Full Document
Unformatted text preview: Fluids – Lecture 2 Notes 1. Airfoil Vortex Sheet Models 2. ThinAirfoil Analysis Problem Reading: Anderson 4.4, 4.7 Airfoil Vortex Sheet Models Surface Vortex Sheet Model An accurate means of representing the ﬂow about an airfoil in a uniform ﬂow is to place a vortex sheet on the airfoil surface. The total velocity V ( x, z ), which is the vector sum of the freestream velocity and the vortexsheet velocity, can be forced parallel to the airfoil surface γ ( s γ (s) V V V by suitably setting the sheet strength distribution ). A panel method is normally used to numerically compute γ ( s ). By using a suﬃcient number of panels, this result can be made as accurate as needed. The main drawback of such numerical calculations is that they give limited insight into how the ﬂow is inﬂuenced by changes in the angle of attack or the airfoil geometry. Such insight, which is important for effective aerodynamic design and engineering, is much better provided by simple approximate analytic solutions. The panel method can still be used for accuracy when it’s needed. Single Vortex Sheet Model In order to simplify the problem suﬃciently to allow analytic solution, we make the following assumptions and approximations: 1) The airfoil is assumed to be thin , with small maximum camber and thickness relative to the chord, and is assumed to operate at a small angle of attack, α ≪ 1. 2) The upper and lower vortex sheets are superimposed together into a single vortex sheet γ = γ u + γ ℓ , which is placed on the x axis rather than on the curved mean camber line Z = ( Z u + Z ℓ ) / 2. z z z γ (x) γ (x) γ (x) γ (x) l x x x Z(x) Z (x) u u Z (x) l Z(x) n 3) The ﬂowtangency condition ˆ V · n = 0 is applied on the xaxis at z = 0, rather than on the camber line at z = Z . But the normal vector ˆ n is normal to the actual camber line shape, as shown in the figure....
View
Full
Document
This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
 Fall '05
 MarkDrela

Click to edit the document details