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Performance of a V/STOL tilt nacelle inlet with blowing boundary layer controlA scale model of a V/STOL tilt nacelle fitted to a 0.508 m single stage fan was tested in the NASA Lewis low speed wind tunnel to determine the effect of diffuser blowing on the inlet aerodynamics and aeromechanical performance. The test was conducted over a range of freestream speeds (up to 120 knots) and angles-of attack (up to 120 deg). In general, diffuser blowing had a beneficial affect on all performance parameters. The angle-of-attack range for a separation-free flow substantially increased, and the fan face distortion reduced with a corresponding increase in total pressure recovery. Discrete narrow band blade stress peaks which were common to the nonblowing (baseline) configuration were eradicated with diffuser blowing.
Document ID
19790063334
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johns, A. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Williams, R. C.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Potonides, H. C.
(Grumman Aerospace Corp. Bethpage, N.Y., United States)
Date Acquired
August 9, 2013
Publication Date
June 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-1163
Meeting Information
Meeting: AIAA, SAE, and ASME, Joint Propulsion Conference
Location: Las Vegas, NV
Start Date: June 18, 1979
End Date: June 20, 1979
Sponsors: AIAA, ASME, SAE
Accession Number
79A47347
Distribution Limits
Public
Copyright
Other

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