Aerospace01

Boundary layer

Compute the boundary layer thickness at the edge of the plate and the drag for

U∞ = 1m/s, Length = 0.5m, W idth = 1m,

Lifting Line Theory

Using lifting line theory, estimate the aerodynamic characteristics (CL, CDi

and e) of the SR22 wing planform

(ignoring the presence of the fuselage). Determine this using eight terms in the monoplane equation, assuming

symmetrical lift distribution. The aircraft is flying at an AOA of 5◦

, uses the NACA 65-415 aerofoil. Using

XFOIL, determine the zero lift angle and lift curve gradient. The wing has a root chord, of croot = 1.58m, a

taper ratio, λ = 0.5, and a semi-span of b = 5.84m

3D Finite Wing Analysis -

In this section you will develop your own code and explore the capabilities of the numerical panel method

known as the Vortex Lattice Method (VLM for short). The VLM approach to solving the thin lifting surface

problem in a potential flow framework will be explored in the tutorials to help you develop your own code.

There are two parts to this report: the first part deals with the development of the method, and a parametric

study on how wing geometry effects aerodynamic performance; and the second part deals with a design

problem. For the first part you should:

• Develop a functional vortex lattice solver using Vortex Ring elements. The requirements of your

program will be outlined below:

– The main program should run as a standalone script, which will be submitted independently of

the report, and tested by the marker.

– All subroutines, such as a vortex line solver, or geometric mesh program should be included at

the end of the main script

– The main program should be submitted with the inputs pre-declared at the top of the script, and

should solve the aerodynamic forces for the wing described in Section 1.2.

– The script should print to the terminal the total lift coefficient, CL, Induced drag coefficient, CDi

and the maximum (or peak) Circulation, Γmax

– The script should also produce two plots: one showi

Beceriler: Havacılık Mühendisliği, Hava-Uzay Mühendisliği, Makine Mühendisliği, Matlab ve Mathematica , Mühendislik

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Proje NO: #27956724