p9.118_solution

p9.118_solution - FLOWLAB SOLUTION 9.118 Use the clarky...

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

View Full Document Right Arrow Icon
9.118 Use the clarky template from FlowLab to investigate the effects of angle of attack, α , on the lift and drag coefficients, C L and C D . Alter the angle of attack from α = –5 ° to 10 ° , in increments of 5 ° . Assume that this airfoil section is part of the wing of an aircraft that is flying through incompressible, viscous air at U = 200 mph and an altitude of h = 15,000 ft in a standard atmosphere. Generate plots of C L and C D as functions of α similar to Figure 9.33 and explain the trends seen in both the lift and drag coefficients as α is increased. Problem Setup For this problem, the default geometry from FlowLab was used: The flow was set to Viscous and the Boundary Condition settings were altered to achieve the stated flight conditions. It is expected that the student will calculate the correct values for ambient pressure and temperature and the Mach number given the conditions in the problem statement. The 0º angle of attack settings are shown below. For all simulations, the medium mesh resolution was used for the grid setup. A sample of
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Image of page 2
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 03/27/2010 for the course ME 330 taught by Professor All during the Spring '08 term at University of Texas.

Page1 / 6

p9.118_solution - FLOWLAB SOLUTION 9.118 Use the clarky...

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

View Full Document Right Arrow Icon
Ask a homework question - tutors are online