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Engineering assessment Task

1 Complete Aircraft Drag Build-Up
The Piper Warrior model was tested in the Low Speed 4x3 Wind Tunnel of the University of Sydney. Data is located here. Your job is use computational methods and the Drag Component Build-Up Method (DCBM) to estimate the complete aircraft Lift, Drag and Pitching Moment. Your tasks are as follows:
1. Using Lifting-Line Theory, estimate the 3D lift coefficient of the Piper Warrior and compare to the experimental data provided. You will need to consider the fuselage, and tail-plane.
2. Using the Induced Drag (wing) and Parasitic drag (aerofoil) obtained from your analysis of the lift coefficient and the DCBM approach to calculate the 3D drag coefficient of the Piper Warrior. As before, you are able to make simplifications to the geometry to match the model.
3. Update the drag coefficient of the Piper Warrior to include all the additional features on the real aircraft, including the propeller/antanne/landing gear/etc. Compare this to the wind tunnel model data.

2 Questions
2.1 Boundary Layer
The velocity profile of a laminar boundary layer on a flat plate at zero incidence of length L is approximated by:

20191031083337AM-953606461-859294288.png

Determine δ
∗, θ and cf . Compute the boundary layer thickness at the edge of the plate and the drag for

U∞ = 1m/s, Length = 0.5m, W idth = 1m, ρ = 103kg/m3 and ν = 10−6ms/s.

2.2 Lifting Line Theory
Select an appropriate aircraft and perform a lifting line theory study by applying all appropriate geometric
parameters.
3 3D Wind Tunnel Data - 15%
A series of NACA0012 wings have been tested in the Low Speed 4x3 Wind Tunnel of the University of Sydney. The wings varied in aspect ratio and sweep. With the wing mounted in the tunnel via two front blades and a rear sting to control angle of attack. The lift, drag and pitching moment were recorded over a range of angles of attack for a fixed wind tunnel speed. Process the results of the test for the various angles of attack looking at the effect of sweep and aspect ratio.
Note that the pitching moment readings are based around the mounting point of the wings, located at 1/3c. Apply all required corrections.
All data is located here.
4 Wing Design - 50%
A new concept aircraft is being proposed. The aircraft designated UXU is to fly using ground effects. Using a steady horseshoe vortex lattice approximation, design the wing for the following aircraft:
• Mach number 0.3
• Total Weight 60 T (assume the main wing will produce 90% of the lifting capacity)
• Loading distribution to be as close as possible to elliptical. Elliptical planform are not allowed due to excessive manufacturing costs. Consider dihedral, sweep, twist and taper.
• Root aerofoil NACA4412
• Tip aerofoil NACA0008
• For passenger comfort the maximum angle attack is restricted between 0?and 2? You should consider the following design consideration in final report
• Would winglets be beneficial?
• Effect of flying away from the ground. What are the height limits?
• Would an increase to Mach 0.4 be beneficial?

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  • Uploaded By : Keith
  • Posted on : October 31st, 2018

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