Global ETD Search
Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.
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Showing 1 to 9 of 9 for “"Aerodynamic Interface Plane"”.
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Assessment of an Innovative Experimental Facility for Testing Diffusing Serpentine Inlets with Large Amounts of Boundary Layer Ingestion
… and 45%. The circumferential distortions at the aerodynamic interface plane of the serpentine inlet were also calculated, and ranged between 0.0042 for the lowest Mach number, to 0.0098 for the highest Mach number. Reynolds numbers for the tests ranged between 1.2 million and 2.4 million …
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Stereoscopic Particle Image Velocimetry Measurements of Swirl Distortion on a Full-Scale Turbofan Engine Inlet
… characterize complex distortion profiles at the aerodynamic interface plane, providing new information about airframe/engine integration.
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A numerical investigation of s-duct flows with boundary-layer ingestion
… center line, and distortion coefficient at the aerodynamic interface plane. Three computational grids, containing 6.5, 30.5, and 36.9 million nodes, were constructed for the numerical simulations. The three grids varied in solid modeling techniques and grid element packing. Time limitations …
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Full Scale Experimental Transonic Fan Interaction with a Boundary Layer Ingesting Total Pressure Distortion
… commercial transport aircraft will feature more aerodynamic architectures to accommodate stringent design goals for higher fuel efficiency, reduced cruise and taxi NOx emissions, and reduced noise. Airframe designs most likely to satisfy the first goal feature architectures that lead to the …
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Effectiveness of a Serpentine Inlet Duct Flow Control Scheme at Design and Off-Design Simulated Flight Conditions
… conditions. The total pressure distortion at the aerodynamic interface plane (AIP) was then used to predict the resulting stability for a compression system. This study was conducted using a model of a compact, low observable, engine inlet duct developed by Lockheed Martin. A flow control …
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Effect of BLI-Type Inlet Distortion on Turbofan Engine Performance
… a total pressure distortion profile at the aerodynamic interface plane (AIP) similar to NASA's Inlet A boundary layer ingesting inlet flow profile. Results of this investigation showed a 15.5% decrease in stream thrust and a 14% increase in TSFC in the presence of BLI-type distortion. Flow …
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The effects of micro-vortex generators on normal shock wave/boundary layer interactions
… recovery, and reducing flow distortion at the aerodynamic interface plane while adding minimal drag to the system. The investigation encompasses experiments in both small-scale and large-scale inlet testing, allowing multiple test beds for improving the characterization and understanding of …
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Active and hybrid flow control in S-ducts and diffusers
… endeavor conducted by the author in the field of aerodynamic flow control. The objectives were to develop flow control actuators, investigate their mechanism, and study their application on different flow-fields. Two flow control actuators - a pneumatic and a plasma-based one - were developed. On …
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Numerical and experimental investigation of VG flow control for a low-boom inlet
… and a large hub-side boundary layer at the Aerodynamic Interface Plane (AIP), which marks the inflow to the jet engine turbo-machinery. Supersonic VGs were investigated to reduce the shock-induced flow separation near the throat while subsonic VGs were investigated to reduce boundary layer …