This paper reports the internal performance evaluation of S-duct diffusers with different entrance aspect ratios as part of a parametric investigation of a generic S-duct inlet. The generic S-duct diffusers studied had a rectangular entrance (aspect ratios of 1.5 and 2.0) transitioning S-duct diffuser in high-subsonic (Mach number > 0.8) flow. The test section was manufactured using rapid prototyping to facilitate the parametric investigation of the geometry. Streamwise static pressure and exit-plane total pressure were measured in a test-rig using surface pressure taps and a five-probe rotating rake, respectively. The baseline and a variant were simulated through computational fluid dynamics (CFD). The investigation indicated the presence of streamwise and circumferential pressure gradients leading to a three-dimensional flow in the S-duct diffuser and to distortion at the exit plane. The static pressure recovery increased for the diffuser with the higher aspect ratio. Total pressure losses and circumferential and radial distortions at the exit plane were higher than that of the podded nacelle type of inlet. An increase in the total pressure recovery was observed for the increase in the aspect ratio for the baseline area ratio (1.57) S-ducts, but without a clear trend for the other area ratio (1.8) ducts. The work represents the development of a database on the performance of a particular type of generic inlet. This database will be useful for predicting the performance of aero-engines and air vehicles in high-subsonic flight.
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Entrance Aspect Ratio Effect on S-Duct Inlet Performance at High-Subsonic Flow
Asad Asghar,
Asad Asghar
Department of Mechanical & Aerospace Engineering,
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
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Robert A. Stowe,
Robert A. Stowe
Weapons Systems Section,
Defence Research and Development Canada,
Québec, QC G3J 1X5, Canada
Defence Research and Development Canada,
Québec, QC G3J 1X5, Canada
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William D. E. Allan,
William D. E. Allan
Department of Mechanical & Aerospace Engineering,
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
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Derrick Alexander
Derrick Alexander
LR Martec Limited,
Halifax, NS B3J 3J8, Canada
Halifax, NS B3J 3J8, Canada
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Asad Asghar
Department of Mechanical & Aerospace Engineering,
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
Robert A. Stowe
Weapons Systems Section,
Defence Research and Development Canada,
Québec, QC G3J 1X5, Canada
Defence Research and Development Canada,
Québec, QC G3J 1X5, Canada
William D. E. Allan
Department of Mechanical & Aerospace Engineering,
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
Royal Military College of Canada,
Kingston, ON K7K 7B4, Canada
Derrick Alexander
LR Martec Limited,
Halifax, NS B3J 3J8, Canada
Halifax, NS B3J 3J8, Canada
Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 23, 2016; final manuscript received September 16, 2016; published online January 4, 2017. Editor: David Wisler.
J. Eng. Gas Turbines Power. May 2017, 139(5): 052602 (8 pages)
Published Online: January 4, 2017
Article history
Received:
June 23, 2016
Revised:
September 16, 2016
Citation
Asghar, A., Stowe, R. A., Allan, W. D. E., and Alexander, D. (January 4, 2017). "Entrance Aspect Ratio Effect on S-Duct Inlet Performance at High-Subsonic Flow." ASME. J. Eng. Gas Turbines Power. May 2017; 139(5): 052602. https://doi.org/10.1115/1.4035206
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