The flowfield around five transonic inlet lips at high incidence is investigated for a variety of flow conditions around a design point representative of high incidence manoeuvring. Changes to the operating point are simulated by varying the angle of incidence and the mass flow rate over the lip, intended to mimic the effect of an increase in engine flow. For these inflow conditions, the flow on the lip is characterised by a supersonic region, terminated by a near-normal shock wave. Of particular interest is the effect of lip geometry and operating point on the boundary layer at the equivalent fan location.

The parametric investigation revealed a significant effect of lip shape on the position and severity of the shockwave-boundary layer interaction. From correlation studies, it appears that the extent of shock-induced separation is the main factor affecting the boundary layer state downstream of the normal shock wave-boundary layer interaction. Somewhat surprisingly, this was found to be independent of shock strength.