Inflow problems associated with inlets, whose axes are perpendicular to plane of wing, are studied in statically and at forward speed; emphasis is on distribution of velocity, total pressure loss, swirl and inflow-to-axis angles in inlet as function of inflow ratio and wing angle of incidence; inlet annulus distributions feature quasi-two-dimensional appearance with inflow velocities being highest in leading annulus sector; flow distortion is function of inflow ratio, inlet geometry, leading lip boundary layer separation and wing incidence angle; other findings; problems involved in starting fan while in flight and solutions.
Experimental studies of VTOL fan-in wing inlets
AGARDograph
1965
33 pages
Article (Journal)
English
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NTRS | 1946
|NTIS | 1945
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