A) What is an adverse pressure gradient, and where does it occur on an airfoil (Show that on an airfoil using a free hand sketch)? B) What causes the flow to separate from an airfoil? C) What are the two major consequences of flow separation? D) A B-2A aircraft is flying at H ft in standard day conditions at a velocity V kn. If the mean chord length is C ft. i- Find the overall or total Reynolds number for the aircraft. ii- Find the percentage of the wing chord where laminar flow is present, if Reynolds number is 500,000.

Question 3 a) Neglecting freestream turbulence, the decelerating freestream velocity profile over a flat plate is given by, u = u₁ (1-x/L)", with L=10m. i) Estimate the point where the separation occurs, for n=1,2,3,4. ii) Consider the case when n=2 and estimate the momentum thickness at the separation point by the Walz-Thwaites's method. iii) Use Michel's method (after 1 iteration) to predict transition when u₁ = 10m/s and obtain an equation for the location of the transition point, x,,. State the assumption that was made to obtain the result. iv) Is x,, upstream or downstream of the point where separation occurs? b) If u is unknown, using Michel's formula for transition, find the value of u₁ = u₁_col that both separation and transition occur at the point of separation. (i.e. the two points are co-located.) such When, u > u₁_col, state whether the transition point x, is upstream (towards the leading edge) or downstream (towards the trailing edge) of the point where separation occurs?…