Intake-airframe integration of tactical aircraft is reviewed. It is shown that the stream flow approaching a side-mounted inlet is substantially distorted by the presence of the fuselage in maneuvering flight. This flow distortion has a generally adverse effect on inlet total pressure recovery and inlet-engine compatibility. Supersonic maneuvering flight can lead to substantial performance degradation in a side-mounted leeward 2-D inlet due to flow separation at the inboard sideplate. Performance degradation in side-mounted half-axisymmetric inlets in supersonic maneuvers results from flow separation in the upper portion of the throat followed by choking of the rest of the throat. Flow field studies show dramatic potential performance advantages for shielding supersonic maneuvering inlets. Fuselage-shielding, however, is the only technique which retains all the advantages for 2-D inlets when alpha/Beta combinations were explored. Half-axisymmetric inlets show substantial performance advantages over 2-D inlets in supersonic wing-shielded flow fields when considering the entire maneuver envelope. Experiments demonstrate limited tailoting of top-mounted inlet flow fields through careful design of wing leading-edge strakes which control the vortex pattern over an aircraft's upper surface. Such designs may be able to facilitate an acceptable inlet environment for limited maneuver conditions.
Intake-Airframe Integration
1988
66 pages
Report
Keine Angabe
Englisch
Wind Tunnel Tests of the Model of Intake-Airframe Integration
British Library Conference Proceedings | 1993
|Engineering Index Backfile | 1957
|NTIS | 1972
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