CPL Aerodynamics · Mock exam

A 'laminar flow' aerofoil section is designed to:

• A.prevent boundary layer separation from the upper surface at high angles of attack near stall
• B.maximise the lift coefficient at low approach speeds to reduce the landing distance
• C.Maintain a laminar boundary layer over a large portion of the chord to minimise skin friction drag
• D.reduce wave drag at transonic Mach numbers by maintaining attached flow over the surface