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Record Details

Record 45 of 20740
High Reynolds Number Investigation of a Flush Mounted, S-Duct Inlet With Large Amounts of Boundary Layer Ingestion
Offline Availability: Go to Request Form
Author and Affiliation:
Berrier, Bobby L.(NASA Langley Research Center, Hampton, VA, United States)
Carter, Melissa B.(NASA Langley Research Center, Hampton, VA, United States)
Allan, Brian G.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: An experimental investigation of a flush-mounted, S-duct inlet with large amounts of boundary layer ingestion has been conducted at Reynolds numbers up to full scale. The study was conducted in the NASA Langley Research Center 0.3-Meter Transonic Cryogenic Tunnel. In addition, a supplemental computational study on one of the inlet configurations was conducted using the Navier-Stokes flow solver, OVERFLOW. Tests were conducted at Mach numbers from 0.25 to 0.83, Reynolds numbers (based on aerodynamic interface plane diameter) from 5.1 million to 13.9 million (full-scale value), and inlet mass-flow ratios from 0.29 to 1.22, depending on Mach number. Results of the study indicated that increasing Mach number, increasing boundary layer thickness (relative to inlet height) or ingesting a boundary layer with a distorted profile decreased inlet performance. At Mach numbers above 0.4, increasing inlet airflow increased inlet pressure recovery but also increased distortion. Finally, inlet distortion was found to be relatively insensitive to Reynolds number, but pressure recovery increased slightly with increasing Reynolds number.This CD-ROM supplement contains inlet data including: Boundary layer data, Duct static pressure data, performance-AIP (fan face) data, Photos, Tunnel wall P-PTO data and definitions.
Publication Date: Sep 01, 2005
Document ID:
20060006399
(Acquired Feb 21, 2006)
Subject Category: AERODYNAMICS
Report/Patent Number: NASA/TP-2005-213766/SUPP, L-19131/SUPP
Document Type: Technical Report
Contract/Grant/Task Num: WBS 22-066-50-AE
Financial Sponsor: NASA Langley Research Center; Hampton, VA, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: HIGH REYNOLDS NUMBER; BOUNDARY LAYERS; STATIC PRESSURE; INGESTION (ENGINES); DUCTS; PHOTOGRAPHS
Miscellaneous Notes: See also NASA/TP-2005-213766, Document ID 20050229940, "High Reynolds Number Investigation of a Flush Mounted, S-Duct Inlet With Large Amounts of Boundary Layer Ingestion" Inlet Report
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