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Vortex generator installation studies on steady state and dynamic inlet distortion

Author
Gibb, James
Published
May 1996.
Physical Description
1 electronic document
Additional Creators
Anderson, Bernhard H.
Online Version

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Summary
The theoretical and experimental work carried out under the NASA/MOD Joint Aeronautical Program has shown that CFD vortex generator installations designs successfully managed inlet duct flow distortion and that significant benefits in flow unsteadiness at the engine face were also present. The main conclusions to date from the collaborative effort between NASA/Lewis and DRA/Bedford are as follows: (1) vortex generator installations can be designed to be effective over a wide range of inlet operating conditions using Computational Fluid Dynamics and formal optimization procedures, (2) reductions in steady state engine face distortion of up to 80% have been measured in the M2129 inlet S-duct using CFD designed vortex generator installations, (3) reductions in flow unsteadiness of up to 80% have been measured in the W129 inlet S-duct using CFD designed vortex generator installations, and (4) the Reduced Navier-Stokes code RNS3D is a useful tool to design vortex generator installations to manage engine face distortions over a wide range of inlet operating conditions.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19960027891.
Accession ID: 96N29033.
AIAA Paper 96-3279.
E-10252.
NASA-TM-107220.
NAS 1.15:107220.
Joint Propulsion Conference; 1-3 Jul. 1996; Lake Buena Vista, FL; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15650449